IHS ESDU Datasheets for Standards and Technical Documents
Standards and technical documents includes standards, codes, regulation, handbooks, manuals, comprehensive guides and other formal publications. Standards, codes, and regulation establish uniform specifications, procedures or technical criteria.
Standards and Technical Documents: Learn more
| Product Name | Notes |
|---|---|
| A computerized method for estimating exhaust noise spectra from a database is provided. The variables considered in the interpolation/extrap olation routine make the procedure particularly applicable to estimating noise from... | |
| A computerized method for estimating near-field exhaust noise spectra from a database is provided. The variables considered in the interpolation/extrap olation routine make the procedure particularly applicable to estimating noise... | |
| A simplified model of forces due to idling power, aerodynamic drag and rolling resistance is obtained from speed and acceleration data in ground testing on the Falcon 20. The model... | |
| Accurate prediction of transitional flow in straight pipes is one of the most challenging CFD applications. While it is not advisable to design fluid equipment to operate in transitional flow... | |
| After a brief description of modes of failure, the estimation of loads is considered together with the determination of allowable stresses and safety factors. The need to idealise a real... | |
| An investigation has been carried out into currently available flight data excluding cases of highly perturbed flow and large pressure gradients. Data have collapsed well on the basis of non-dimensional... | |
| Conversion factors between various unit systems for liquid flow parameters. | |
| Conversion factors, units. Includes some useful data for air and water. Also sea level data for the International Standard Atmosphere. | |
| Data from ground-rolling tests through water with a Canberra aircraft are analysed in the context of the modelling developed in ESDU 10015. Because spray from the main-wheels of the aircraft... | |
| ESDU 93015 introduces a Fortran program for aerofoils and wings without high-lift devices. For aerofoils the method of ESDU 84026 is used, which itself relies on the prediction of lift-curve... | |
| ESDU 93016 introduces a computer program that implements the method of ESDU 90006 but modified to take into account the residual gain and phase variation effects of modes whose resonant... | |
| ESDU 93017 contains liquid thermal conductivity data for twenty two straightchain, three branched chain alkanoic acids and eleven alkenoic acids. Experimental results drawn from the literature for each pure compound... | |
| ESDU 93018 presents Nusselt number data in laminar flow for conditions of either uniform wall temperature or uniform heat flux in fully-developed flow, flow that is thermally-developing (where the heated... | |
| ESDU 93019 presents an empirical method that depends on determining the increment for an aerofoil representative of the wing and applying factors to allow for three-dimensional and part-span effects. ESDU... | |
| ESDU 93020 is ancillary to and is for use in conjunction with ESDU 88025, which provides a definitive method for deriving primary air-data parameters in hypersonic flight with excellent precision,... | |
| ESDU 93021 deals with one method of optimisation of a complete sortie, applied as an example to a subsonic transport and used to demonstrate the penalties incurred by constraints imposed... | |
| ESDU 93022 introduces a FORTRAN program (ESDUpac A9322) for ejectors in which the primary and secondary flows are of non-reacting miscible liquids. Inlet conditions for both primary and secondary flows... | |
| ESDU 93023 uses second segment climb measurements to provide simple examples of statistical significance testing and confidence levels. Certification trials of a twin turbo-prop aircraft established that second segment climb... | |
| ESDU 93024 summarises situations where vortex generators have been used to control shock-induced separation. It is suggested that their use should be considered at the design stage and not only... | |
| ESDU 93025 provides a step-by-step procedure for the geometric design of a co- or counter-rotating array of vortex generators. A criterion is first given to determine whether effective control is... | |
| ESDU 93026 illustrates by case studies the use of the information in Parts 1 and 2 on the use of vortex generators to control shock-induced separation. The examples are the... | |
| ESDU 93027 discusses methods of testing structural elements, designed to represent features of the full-size structure, using random-amplitude narrow-band loading to simulate response to acoustic loading. A wide range of... | |
| ESDU 93028 presents vapour pressure data for 36 hydrocarbons and Carbazole. The data were obtained by a critical evaluation of experimental results in the literature. Where the data were less... | |
| ESDU 93029 tabulates density and molar volume for 30 compounds in units of kg/cu m and cu cm/mol respectively from near the melting point to the critical point (although for... | |
| ESDU 93030 introduces a computer program, ESDUpac A9330, that calculates the stress concentration factors from polynomial equations that were fitted to a wide range of finite element calculations and reproduce... | |
| ESDU 93031 introduces a program, ESDUpac A9331, that directly accounts for the mutual coupling between internal pressure and flow conditions, and the stresses and structural motion of the pipework. The... | |
| ESDU 93032 illustrates the application to a real situation of the ESDU data on drag due to cavities, grooves, steps, ridges and control gaps, and the drag magnification factor applied... | |
| ESDU 93033 presents data that compare the behaviour of long and short cracks which are longer than the typical microstructural dimension but are not substantially larger than the radius of... | |
| ESDU 93034 presents graphical data at taper ratios of 0, 0.5 and 1 applying at Mach numbers of 0.5 and below, and at Mach numbers of 0.8 and 0.95. They... | |
| ESDU 94001 presents vapour pressure data for 21 compounds. The data were obtained by a critical evaluation of experimental results in the literature. The data available were limited but using... | |
| ESDU 94002 tabulates density and molar volume for 20 compounds in units of kg/cu m and cu cm/mol respectively from near the melting point to about 0.9 of the critical... | |
| ESDU 94003 gives formulae for the in-plane and flexural stiffnesses of laminated flat plates built-up from thin orthotropic layers that may have different material properties, thicknesses, and orientations of their... | |
| ESDU 94004 gives equations for the strains and stresses, and curvatures where appropriate, in laminated flat plates as a result of either loading actions or the differential contractions and expansions... | |
| ESDU 94005 introduces a Fortran program, ESDUpac A9405, that calculates the buckling load for the plate for uniform, in-plane uniaxial or biaxial direct loading with or without shear. The program... | |
| ESDU 94006 introduces a Fortran program, ESDUpac A9406, for calculating the buckling loading of composite plates for which in both the direct and flexural stiffness matrices the first two terms... | |
| ESDU 94007 introduces a Fortran program, ESDUpac A9407, that calculates the buckling value of a uniform in-plane axial loading on the panel, with or without an additional circumferential loading due... | |
| ESDU 94008 presents a method for calculating values of lubricant film thickness in the contact region between a disc cam and a follower (where the contact can be described as... | |
| ESDU 94009 examines the process of determining the structural strength requirements for an aircraft in steady manoeuvring flight. To evaluate the shear force, bending moment and torque across the wing... | |
| ESDU 94010 gives equations obtained from a critical evaluation of experimental data in the literature for the variation along the saturation line with temperature, for both the liquid and the... | |
| ESDU 94011 presents a method for calculating values of compressive contact stress in the contact region between a disc cam and a domed or flat-faced follower at regular intervals during... | |
| ESDU 94012 explains in broad terms the method of optimisation used by such techniques and emphasises that numerical optimisation will not locate an absolute minimum but requires the user to... | |
| ESDU 94013 presents the coordinates for the cowl external profile as originally defined and now taken as a 'standard', together with the lip radius. When second divided differences of the... | |
| ESDU 94014 presents charts for 20 cowls of the coefficient computed from finite difference solutions to the Euler equations for inviscid compressible flow. Computed shock waves are smeared over a... | |
| ESDU 94015 presents charts for 20 cowls of the distributions computed from finite difference solutions to the Euler equations for inviscid compressible flow. Computed shock waves are smeared over a... | |
| ESDU 94016 gives a further study to that in ESDU 93021 of optimising a complete sortie. The aircraft is the same as used in ESDU 93021, and fuel required (and... | |
| ESDU 94017 presents information on the selection of suitable materials, manufacturing methods (including profile generation and surface treatment) and lubricants for cam mechanisms. A pair of design procedures (presented as... | |
| ESDU 94019 introduces a Fortran program (ESDUpac A9419) that calculates the through-thickness radial and shear stresses in a specially-orthotropi c section subjected to a bending moment, and radial and tangential... | |
| ESDU 94020 primarily applies when there is a continuous lubricant film as in hydrodynamic or hydrostatic bearings, but also has application in boundary lubrication. It does not treat greases. Classes... | |
| ESDU 94021 gives data for all four monohalomethanes, 6 dihalo-, 11 trihalo-, and 11 tetrahalomethanes together with four azeotropic mixtures. Experimental results drawn from the literature for each compound were... | |
| ESDU 94022 contains liquid thermal conductivity data for sixty one halogenated ethanes. Experimental results drawn from the literature for each pure compound were fitted with a four-term polynomial equation in... | |
| ESDU 94023 contains liquid thermal conductivity data for ninety four halogenated higher alkanes comprising: twenty one propanes, nineteen butanes, twelve pentanes, twelve hexanes, four heptanes, nine octanes, four nonanes, seven... | |
| ESDU 94024 gives data for 7 haloethylenes, 4 halopropenes, 3 chlorobutenes, chloroprene and 1-chlorobuta-1,3-die ne. Experimental results drawn from the literature for each compound were fitted with a four-term polynomial... | |
| ESDU 94025 tabulates the viscosity of 34 aliphatic ketones and 4 cycloalkanones at saturation pressure, for temperatures from just above the melting temperature, where known to approximately 0.9 of the... | |
| ESDU 94026 discusses the behaviour of the lift-curve of an aerofoil depending on its thickness/chord ratio, and the effects on that behaviour of the deployment of high-lift devices. It provides... | |
| ESDU 94027 presents an estimation method based on first approximations from the theory for a thin hinged plate modified using empirical correlation factors to account for the geometry of practical... | |
| ESDU 94028 presents an estimation method based on first approximations from the theory for a thin hinged plate modified using empirical correlation factors to account for the geometry of practical... | |
| ESDU 94029 presents an estimation method based on first approximations from the theory for a thin hinged plate modified using empirical correlation factors to account for the geometry of practical... | |
| ESDU 94030 presents an estimation method based on the theory for a thin hinged plate modified using empirical correlation factors to account for the geometry of practical aerofoils and high-lift... | |
| ESDU 94031 presents an estimation method based on the theory for a thin hinged plate modified using empirical correlation factors to account for the geometry of practical aerofoils and high-lift... | |
| ESDU 94032 provides evaluated thermophysical properties data for refrigerant32 (difluoromethane). Equations, based on a critical evaluation of experimentaldata in the literature are given for the variation with temperature along the... | |
| ESDU 94033 introduces a Fortran program which gives (i) the detailed distribution of deflection and either the moments and in-plane forces, or the stresses, or the strains, throughout the plate... | |
| ESDU 94034 introduces a computer program (ESDUpac A9434) to calculate stresses in point contacts that occur in rolling element bearings, gears, cams and other engineering components. Both normal and combined... | |
| ESDU 94035 introduces a Fortran program to calculate a difference spectrum between the measured and free-field spectra either at discrete frequency noise levels at constant intervals or at one-third band... | |
| ESDU 94036 introduces a Fortran program for calculating either a difference spectrum between a source and a point close to the ground or, knowing the spectrum at one point, the... | |
| ESDU 94037 gives an expression for calculating the total theoretical leading-edge suction force using the lift-curve slope and the lift-dependent drag factor which can be obtained respectively from ESDU 70011... | |
| ESDU 94038 introduces a Fortran program, ESDUpac A9438, that calculates the total theoretical leading-edge suction and its normalised spanwise distribution for wings from the tabulated values for the distribution given... | |
| ESDU 94039 gives simple formulae for the effect of small changes in thrust, power (for propeller-driven aircraft), weight and drag (assuming a parabolic drag law) at constant airspeed and, when... | |
| ESDU 94040 discusses how the maximum cabin pressure differential and the rate of change of cabin pressure affect rates of climb and descent, particularly of civil aircraft. The cabin pressure... | |
| ESDU 94041 provides correlations in vapour shear-controlled annular and gravity-controlled stratified flows for the local heat transfer coefficient at a specified vapour mass flow fraction. A flow regime map defines... | |
| ESDU 94042 extends the information in ESDU 92013 which, when a shell-and-tube exchanger is found appropriate and is costed, provides the results for a datum design with fixed average values... | |
| ESDU 94043 extends the information in ESDU 92013 which, when an air-cooled exchanger is found appropriate and is costed, provides the results for a datum design 40 ft (12.2 m)... | |
| ESDU 94044 is based on manufacturer's estimated values for a large number of aircraft as manufactured and provides a guide to standards that have been achieved and a method to... | |
| ESDU 94045 uses for an aircraft of classical configuration at constant incidence the data identified in ESDU 94009 for aerodynamic load and mass of the components of a wing-fuselage-nacell e... | |
| ESDU 94046 introduces a program (ESDUpac A9446) for ejectors in which the primary and secondary flows are non-reacting gases that can be modelled as real. Three procedures are provided: a... | |
| ESDU 95001 and the associated computer program presents methods for the calculation of the pressure angle, the radius of curvature of the cam profile, the radius of curvature of the... | |
| ESDU 95002 presents vapour pressure data for 22 glycols and 6 cyclic diols (molecules from C2 to C6). The data were obtained by a critical evaluation of experimental results in... | |
| ESDU 95003 tabulates density and molar volume for 19 glycols and 3 cyclic diols (molecules from C2 to C6) in units of kg/cu m at 5 degree C intervals and... | |
| ESDU 95004 presents vapour pressure data for 10 C3 to C8 monoalkyl ethers (6 cellosolves and 4 carbitols) and 6 C4 to C10 dialkyl ethers (2 cellosolves, 2 carbitols, triglyme... | |
| ESDU 95005 tabulates density and molar volume for 10 C3 to C8 monoalkyl ethers (6 cellosolves and 4 carbitols) and 6 C4 to C10 dialkyl ethers (2 cellosolves, 2 carbitols,... | |
| ESDU 95006 introduces the theory of linear cumulative damage, the Palmgren-Miner Rule that hypothesises that the damage inflicted by any cycle in a variable amplitude loading sequence is the same... | |
| ESDU 95007 extends the information in ESDU 92013 so providing updated budget cost estimates for gasketed and semi-welded plate-and-frame exchangers obtained from an analysis of results obtained using costing methods... | |
| ESDU 95008 gives data for 20 compounds. Experimental results drawn from the literature for each compound were fitted with a four-term polynomial equation in reduced temperature. The coefficients were also... | |
| ESDU 95009 presents a theoretical method, based on slender-body theory, for estimating the change in lift and aerodynamic centre position resulting from moving a wing from a centrally-mounted position to... | |
| ESDU 95010 introduces two Fortran computer programs, ESDUpacs A9510 and B9510, that use lifting-surface theory based on the Multhopp-Richardson solution. Both programs calculate the distributions of local lift and pitching... | |
| ESDU 95011 derives a mean-value set for representation of a non-uniform flow of a calorically-perfect gas at a duct section. A thermodynamically-ri gorous, uniform reference-mean flow is derived by extending... | |
| ESDU 95012 provides guidance on obtaining viscometric data necessary for estimating pressure drop in pseudohomogeneous (non-settling) fluids. ESDU 95012 briefly reviews the classification of fluids according to their rheological type,... | |
| ESDU 95013 provides evaluated thermophysical properties data for methanol.Equations, based on a critical evaluation of experimental data in the literature are given for the variation with temperature along the saturation... | |
| ESDU 95014 gives graphs, for a range of dimensions (relative to the span) of the rectangular section, of the spanwise variation of the interference upwash along the leading- and trailing-edges... | |
| ESDU 95015 provides information for use with ESDU 71026 in the selection of the appropriate data for tyre-runway friction. For runways for which texture depth measurements were available, cumulative probability... | |
| ESDU 95016 presents vapour pressure data for 37 ethers from C2 to C10 obtained by a critical evaluation of experimental results in the literature. The limited data available were extrapolated... | |
| ESDU 95017 tabulates from near the melting point to the critical point density in kg/cu m at 5 degree C intervals and molar volumes in cu cm/mol at 5 K... | |
| ESDU 95018 contains liquid thermal conductivity data for fifty five straight chain dialkyl ethers and eighteen branched chain dialkyl ethers. Experimental results drawn from the literature for each pure compound... | |
| ESDU 95019 tabulates the viscosity of twenty-six aliphatic ethers at saturation pressure for temperatures from just above the melting point to approximately 0.9 of the critical temperature. Experimental data extracted... | |
| ESDU 95020 tabulates the viscosity of twenty carboxylic (alkanoic) acids at saturation pressure, for temperatures from just above the melting point to approximately 0.9 of the critical temperature. Experimental data... | |
| ESDU 95021 presents an empirical method that depends on determining the increment for an aerofoil representative of the wing and applying factors to allow for three-dimensional and part-span effects. ESDU... | |
| ESDU 95022 presents graphical data for centre of pressure position of delta and rectangular wings of aspect ratio 0.25 to 4 for angles of attack up to 90 degrees. They... | |
| ESDU 95023 introduces a computer program (ESDUpac A9523) that provides a dynamic simulation of the rotor/bearing system through a cycle of run-up at constant acceleration, a period at constant operating... | |
| ESDU 95024 uses the case of a small military subsonic aircraft with compensated pressure sensing head fitted to a nose boom to illustrate methods of collecting and correlating data within... | |
| ESDU 95025 applies to wings of straight taper with transition near the leading edge. It uses a semi-empirical correlation to derive the attainable leading-edge suction from the theoretical leading-edge suction... | |
| ESDU 95026 introduces two computer programs for calculating the surface strains in a sandwich panel with isotropic faceplates and a bevelled edge that allows for a solid edge strip around... | |
| ESDU 95027 presents methods, based on existing correlations of experimental data, that apply in laminar, transition and turbulent flow. A full derivation of the expressions for friction factor and Nusselt... | |
| ESDU 95028 introduces a Fortran program, ESDUpac A9528, to calculate the through-thickness stresses at and near the free edges of laminated plates. A quadratic average stress failure criterion is suggested... | |
| ESDU 96002 presents the equations used in the program of ESDU 96011 (ESDUpac A9611) for calculating the important performance indicators used in the design of internal and external Geneva mechanisms. | |
| ESDU 96003 provides an empirical method for predicting, in two separate parts, the non-linear lift curve up to, and including, maximum lift of aerofoils and wings with high-lift devices deployed... | |
| ESDU 96011 introduces a computer program, ESDUpac A9611, for analysing the performance of either external or internal Geneva mechanisms. Starting with either the centre distance between the crank and wheel... | |
| ESDU 96012 provides an empirical graphical method derived from a correlation of wind-tunnel data for the prediction separately of boat-tail and base pressure drag that applies at all Mach numbers... | |
| ESDU 96013 provides over 4000 values of plane strain fracture toughness for 23 US standard material specification aluminium alloys. The data are presented in tabular form, providing details of test... | |
| ESDU 96014 presents data relating to joints fabricated from seven different structural steels with tensile strengths ranging from 400 to 867 MN/sq m (58E3 to 126E3 lbf/sq ft) secured, with... | |
| ESDU 96015 describes a program for either the selection of a material or the analysis of the performance of a known material. It applies to either journal or thrust bearings... | |
| ESDU 96016 presents vapour pressure data for 74 esters from C2 to C19 obtained by a critical evaluation of experimental results in the literature. The limited data available were extrapolated... | |
| ESDU 96017 tabulates from near the melting point to the critical point density in kg/cu m at 5 degree C intervals and molar volumes in cu cm/mol at 5 K... | |
| ESDU 96018 contains liquid thermal conductivity data for fourteen alkyl methanoates, fourteen alkyl ethanoates, fourteen alkyl propanoates, fourteen alkyl butanoates, thirteen alkyl pentanoates, thirteen alkyl hexanoates, twelve alkyl heptanoates, thirteen... | |
| ESDU 96020 tabulates the viscosity of 95 straight chain aliphatic esters comprising: 10 methanoates, 10 ethanoates, 10 propanoates, 10 butanoates, 10 pentanoates, 10 hexanoates, 10 heptanoates, 10 octanoates, 3 decanoates,... | |
| ESDU 96021 presents vapour pressure data for 41 esters from C4 to C10 obtained by a critical evaluation of experimental results in the literature. The limited data available were extrapolated... | |
| ESDU 96022 tabulates from near the melting point to the critical point density in kg/cu m at 5 degree C intervals and molar volumes in cu cm/mol at 5 K... | |
| ESDU 96023 contains liquid thermal conductivity data for branched chain alkyl alkanoates comprising: four methanoates, four ethanoates, twelve propanoates, twelve butanoates, four pentanoates, four hexanoates, four octanoates, four decanoates, four... | |
| ESDU 96024 presents as an illustration of the use of the Bivariate Normal Distribution an analysis of data for the length and width of a sample of paved runways from... | |
| ESDU 96025 gives a programmed method for the prediction of drag due to lift for planar and non-planar swept wings, alone or in combination with a body under conditions that... | |
| ESDU 96026 provides an empirical method applying to a spoiler on one wing panel. The drag increment is considered as the sum of a profile drag component and an induced... | |
| ESDU 96027 provides a program for calculating the unsteady local lift coefficient on an aerofoil section of the blade in subcritical flow. This forms part of the data input required... | |
| ESDU 96030 describes the nature of the lateral response to vortex shedding of structures of circular or of polygonal cross section with more than eight sides. A method is developed... | |
| ESDU 96031 provides guidance on the use of a module for Microsoft Excel for calculation of response of structures to vortex shedding. The basis of the calculation method is described... | |
| ESDU 96032 provides an empirical method developed from that for aerofoil sections in ESDU 94027 to 94031. It applies to leading-edge flaps, drooped leading edges, slats and vented Krueger flaps,... | |
| ESDU 96033 presents an empirical method applying to cylindrical bodies with or without conical boat-tails, at angles of attack up to 25 degrees and Mach numbers up to 5. The... | |
| ESDU 96034 provides evaluated thermophysical properties data for hydrogensulphide. Equations, based on a critical evaluation of experimental data in theliterature are given for the variation with temperature along the saturation... | |
| ESDU 96035 provides examples illustrating the use of ESDU 96002. The first two examples are primarily intended to show the use of the program, ESDUpac A9611, and so low speed... | |
| ESDU 96036 introduces a computer program, ESDUpac A9636, to determine a set of orthotropic layer thicknesses to withstand given in-plane loads and bending moments effectively. It assumes perfect bonding between... | |
| ESDU 96037 introduces some of the fundamental concepts relating to the effects of structural flexibility for aeroplanes of classical configuration (aspect ratios greater than 4 and sweep angles less than... | |
| ESDU 97002 provides an introductory review of those Items in the Aerodynamics Series that deal with the changes in lift, pitching moment and drag of a two-dimensional aerofoil or a... | |
| ESDU 97003 provides an empirical method to allow for the fuselage interference effects on the lift, pitching moment and drag coefficient increments predicted for the isolated wing due to deflection... | |
| ESDU 97006 is one of a group of Data Items relating to the selection and costing of heat exchangers. Its objective is to provide the process engineer with a simple... | |
| ESDU 97007 introduces a computer program, ENTRANS (see ESDU 00041 for guidance on the use of this program), which generates approximate designs and cost estimates for shell-and-tube exchangers with plain... | |
| ESDU 97008 contains liquid thermal conductivity data for seventeen alkanals, seventy one alkanones, two alkenals, one alkenone, alkandione and one alkoxyalkanone. Experimental results drawn from the literature for each pure... | |
| ESDU 97009 provides an empirical method for estimating delta C sub L0tw, the increment in lift coefficient at zero angle of attack due to the deployment of full-span or part-span... | |
| ESDU 97010 gives data for 17 primary, 5 secondary and 5 tertiary amines and one alkenyl amine. Experimental results drawn from the literature for each compound were fitted with a... | |
| ESDU 97011 provides an empirical method for estimating delta C sub L0tw, the increment in lift coefficient at zero angle attack due to the deployment of full-span or part-span plain... | |
| ESDU 97012 presents vapour pressure data for 39 aliphatic amines to C18, 1 alkenylamine and 6 cycloalkylamines obtained by a critical evaluation of experimental results in the literature. The limited... | |
| ESDU 97013 tabulates from near the melting point to the critical point density in kg/cu m at 5 degree C intervals and molar volumes in cu cm/mol at 5 K... | |
| ESDU 97014 presents vapour pressure data for 32 secondary alkylamines to C18 and 16 tertiary alkylamines obtained by a critical evaluation of experimental results in the literature. The limited data... | |
| ESDU 97015 tabulates from near the melting point to the critical point density in kg/cu m at 5 degree C intervals and molar volumes in cu cm/mol at 5 K... | |
| ESDU 97016 summarises several drag estimation methods as illustrative examples of the range of techniques and the levels of sophistication that exist. The methods rely on the summation of contributions... | |
| ESDU 97017 describes the aerodynamic design of swept wings intended primarily for transonic flow; it is concerned with the application of Computational Fluid Dynamics (CFD) but not with the choice... | |
| ESDU 97019 introduces a computer program that determines the equilibrium temperatures and heat flow rates in a network of heat conducting and dissipating parts. The thermal network analysis implemented by... | |
| ESDU 97020 gives a method for predicting the linear viscous lift-curve slope of symmetric and cambered aerofoils in subcritical compressible flow. The VGK program (see ESDU 96028 and 96029 in... | |
| ESDU 97021 provides a graphical semi-empirical method based on a correlation of calculations made using a trailing horseshoe-vortex model to represent a straight-tapered wing with plain flaps over a range... | |
| ESDU 97022 gives a method for estimating the increment in (jet off) base drag, over that for the body alone given by ESDU 79022, due to stabilising fins on axisymmetric... | |
| ESDU 97024 introduces two Fortran programs, ESDUpacs A9724 and W9724, for the consistent derivation of an S-N curve from a set of fatigue data. The method on which the programs... | |
| ESDU 97025 gives similarity rules for pressure coefficient. For subsonic and supersonic two- and three-dimensional flow over thin sections and for axisymmetric flow they are derived from linearised (potential) flow... | |
| ESDU 97027 tabulates the viscosity of 23 primary alkylamines, 12 secondary alkylamines and 7 tertiary alkylamines at saturation pressure, for temperatures from just above the melting point to approximately 0.9... | |
| ESDU 97028 provides evaluated thermophysical properties data for sulphur hexafluoride on the saturation line, in the ideal gas and dilute gas state, in thesingle phase gas and supercritical region. The... | |
| ESDU 97029 derives a mean-value set for representation of a non-uniform flow of a thermally-perfect gas at a duct section. A thermodynamically-ri gorous, uniform reference-mean flow is derived by extending... | |
| ESDU 97030 describes the use of VGK, which applies only when the boundary layer is attached, to estimate a separation boundary, in terms of lift coefficient and Mach number, using... | |
| ESDU 97031 is concerned with the prediction of the wind conditions downstream of the fences. It enables predictions to be made of the change in local wind speed and turbulence... | |
| ESDU 97032 gives a formal analysis of the equilibrium behaviour of a flexible aeroplane of classical configuration in trim or in a quasi-steady pull-out manoeuvre. The aeroplane has a swept... | |
| ESDU 97033 describes the most commonly used methods of prediction for structures and structures coupled to fluids. It provides guidelines for choosing an appropriate method for a given application. Various... | |
| ESDU 97034 is one of the group of ESDU Data Items on the flow Characteristics of non-Newtonian fluids, and provides an introductory guide to the identification, classification and characterisation of... | |
| ESDU 98001 considers only the drag due to skin-friction which acts on surfaces that are more or less aligned with the aircraft fore-and-aft axis and is the primary source of... | |
| ESDU 98002 gives data for six aliphatic amino-alcohols, five diamines and eight nitro compounds. Experimental results drawn from the literature for each compound were fitted with a four-term polynomial equation... | |
| ESDU 98003 provides a description and overview of the effectiveness (E) - number of heat transfer units (NTU) method for the thermal analysis of two-stream heat exchangers and illustrates its... | |
| ESDU 98004 provides graphically a wide range of comparative thermal performance data (effectiveness-NTU and maximum effectiveness) for crossflow (including serpentine), shell-and-tube and plate-type exchanger geometries, extracted from the extensive data... | |
| ESDU 98005 provides graphical and tabular effectiveness - NTU data for a wide range of practical heat exchanger configurations. The data are presented in "family groups" based on exchanger types,... | |
| ESDU 98006 provides a series of case studies covering the selection, thermal design and thermal performance of heat exchangers. The case studies follow the calculation procedures laid out in ESDU... | |
| ESDU 98007 describes finite element based numerical and algebraic techniques used to relate effectiveness, number of heat transfer units (NTU) and stream thermal capacity ratio to derive the data presented... | |
| ESDU 98008 provides a means of estimating the noise generated by fans or compressors in turbojet and turbofan engines, with and without inlet guide vanes. Sound pressure levels in one-third... | |
| ESDU 98010 provides a guide to the design and operation of falling film evaporators under steady state conditions with pure component fluids. Correlations derived from an analysis of experimental data... | |
| ESDU 98011 gives a method for predicting the viscous zero-lift incidence of aerofoils. The method applies to aerofoils with simple or complex camber lines and accounts for the effect of... | |
| ESDU 98012 introduces a Fortran program, ESDUpac A9812, that computes the bolt loads and flexibilities, and joint extension and flexibility of a multi-bolt, single row, lap joint loaded in either... | |
| ESDU 98013 describes how winglets function and the aerodynamic principles governing their design. At subsonic speeds the aerodynamic efficiency of a wing (without winglets) is ultimately constrained by its span. | |
| ESDU 98014 presents vapour pressure data for 31 halogenated benzenes obtained by a critical evaluation of experimental results in the literature. The limited data available were extrapolated using a correlation... | |
| ESDU 98015 tabulates from near the melting point to the critical point density in kg/cu m at 5 degree C intervals and molar volumes in cu cm/mol at 5 K... | |
| ESDU 98016 introduces Fortran programs (ESDUpacs A9816 and B9816, provided in compiled form) for calculating the initial buckling (local, flexural, torsional or torsional-flexural) loads for flat rectangular panels and struts... | |
| ESDU 98018 contains liquid thermal conductivity data for forty four halogenated aromatic hydrocarbons (benzenes, toluenes and naphthalenes). Experimental results drawn from the literature for each pure compound were fitted with... | |
| ESDU 98020 provides a computerized method for the estimation of transmission and reflection efficiencies of coupled plates. The plates are assumed to be thin, isotropic and coupled in an arbitrary... | |
| ESDU 98021 tabulates the viscosity of 7 halogenated propanes, 11 halogenated butanes, 5 halogenated pentanes, 4 halogenated hexanes, 4 halogenated heptanes, 4 halogenated octanes, 4 halogenated nonanes, 4 halogenated decanes,... | |
| ESDU 98023 gives worked examples to provide insight into the basic analysis and design of planar linkage mechanisms using OSMEC. Example 1 describes in detail how OSMEC is used to... | |
| ESDU 98024 presents a quaternion representation of the conversion of the attitude and motion characteristics of an aeroplane measured in flight to those relative to the earth. Flight measurements from... | |
| ESDU 98026 provides an example of the use of similarity rules in the correlation of measured data for a complex aerodynamic case in a relatively simple way. The particular case... | |
| ESDU 98031 presents an extended VGK program (termed VGKE) and describes the method of using it to provide values of the various parameters needed for the estimation of the excrescence... | |
| ESDU 99003 introduces a series of low-drag aerofoils designed at Glasgow University and a Fortran program for generating their geometry and their inviscid flow characteristics. The low-drag NACA 6- and... | |
| ESDU 99004 predicts for aerofoils the position of the centre of the incremental lift based on thin-aerofoil theory with empirical correction. This is combined with the predicted increment in aerofoil... | |
| ESDU 99005 presents values of the properties of the vapours of inorganic compounds at or below atmospheric pressure. The data for thermal conductivity and viscosity result from the correlation of... | |
| ESDU 99007 presents vapour pressure data obtained by a critical evaluation of experimental results in the literature for 43 halogenated alkylbenzenes and 4 halogenated styrenes.. The data available were limited... | |
| ESDU 99008 tabulates from near the melting point to the critical point density in kg/cu m and molar volumes in cu cm/mol, both at 10 K intervals, for 41 halogenated... | |
| ESDU 99010 provides a graphical method for predicting supersonic base drag of a cylindrical body at zero angle of attack with a central circular propulsive jet. The graphs plot base... | |
| ESDU 99011 presents values of the properties of the vapours of alkanes at or below atmospheric pressure. The data for thermal conductivity and viscosity result from the correlation of experimental... | |
| ESDU 99012 contains liquid thermal conductivity data for nine aliphatic oxalates, nine aliphatic malonates, nine aliphatic succinates, nine aliphatic glutarates, nine aliphatic adipates, nine aliphatic pimelates, nine aliphatic suberates, nine... | |
| ESDU 99013 contains liquid thermal conductivity data for eight glycols, six aliphatic diols, glycerol and aqueous solutions of four glycols, one diol and glycerol. Experimental results drawn from the literature... | |
| ESDU 99014 predicts for aerofoils the centre of lift position based on thin-aerofoil theory with empirical correction. This is combined with the predicted increment in aerofoil lift coefficient from ESDU... | |
| ESDU 99016 is the first of a series of examples of the application of a method for representing - and, if necessary, relating - the braking performances of aircraft and... | |
| ESDU 99017 is the second of a series of examples of the application of a method for representing - and, if necessary, relating - the braking performances of aircraft and... | |
| ESDU 99020 presents three examples of the application of the constrained multivariate optimisation technique CODAS to minimisation of drag of aerofoil sections at fixed Mach number and lift coefficient by... | |
| ESDU 99021 presents an example of the application of the constrained multivariate optimisation technique CODAS to minimisation of aerofoil drag coefficient at multiple design points. ESDU 99020 illustrates the use... | |
| ESDU 99022 tabulates the viscosity of 21 halogenated benzenes, 13 halogenated toluenes, 2 halogenated ethylbenzenes, 1 halogenated isopropylbenzene and 3 halogenated naphthalenes at saturation pressure, fortemperatures from just above the... | |
| ESDU 99032 presents a slightly extended version of VGK (termed VGKD) for generating the camber form to be applied to an aerofoil profile having a specified thickness distribution, such that,... | |
| ESDU 99033 presents the formal equations of a normal mode analysis of the symmetric static aeroelasticity of a flexible aeroplane in steady trimmed flight or in a quasi-steady symmetric manoeuvre. | |
| ESDU A1 gives a complete list of the contents of the Fluid Mechanics, Internal Flow Series to assist users of the Aerodynamics Series to locate information of interest there. | |
| ESDU A2 gives a complete list of the contents of the Wind Engineering Series to assist users of the Aerodynamics Series to locate information of interest there. | |
| ESDU AERO 00.01.06 gives graphs of temperature, an enthalpy parameter, speed of sound, specific entropy and specific heat capacity as functions of pressure ratio and specific enthalpy assuming that the... | |
| ESDU AERO 00.01.07 gives graphs of dynamic viscosity, thermal conductivity, Prandtl number and the product of density and dynamic viscosity, as functions of pressure and specific enthalpy, for air assumed... | |
| ESDU AERO 00.01.08 gives graphs of the ratio of specific heat capacities (gamma) at one atmosphere pressure for air, argon, carbon dioxide and monoxide, helium, hydrogen, nitrogen, oxygen and steam... | |
| ESDU AERO 00.01.09 gives theoretical expressions, obtained by consideration of the behaviour of a diatomic molecule, in terms of the characteristic vibrational temperature for the ratio of specific heat capacities,... | |
| ESDU AERO 00.01.11 introduces a large Mollier chart available separately that gives curves of speed of sound, pressure, density, temperature and real gas factor as functions of specific enthalpy and... | |
| ESDU AERO 00.01.12 introduces a large Mollier chart available separately that gives curves of speed of sound, pressure, density, temperature and real gas factor as functions of specific enthalpy and... | |
| ESDU Aero 00.02.05 provides data derived from correlation of experimental data that apply to conditions of uniform heat flux or uniform wall temperature, but may be used for other boundary... | |
| ESDU AERO 00.03.05 gives expressions for the variation with the ratio of pressure to stagnation pressure of the following ratios: the temperature to the stagnation temperature, the density to the... | |
| ESDU Aero 00.03.26 provides equations and graphs that allow the determination of the gas or wall temperature distribution along a pipe for subsonic flow of a perfect gas under forced... | |
| ESDU AERO 00.03.28 gives equations for the downstream Mach number, and the ratios across the shock of static pressure, total pressure, density and temperature, all as functions of upstream Mach... | |
| ESDU AERO 00.03.30 gives a single curve, based on an approximate solution of the oblique shock wave equations, that allows the static pressure difference across the shock to be evaluated... | |
| ESDU AERO 00.03.31 gives curves, based on a hypersonic similarity solution to the Prandtl-Meyer expansion relations that allow the static pressure difference across the expansion to be evaluated knowing only... | |
| ESDU Aero A.02.03.02 provides equations for calculating the theoretical transonic drag rise of a wing-body combination of optimum area distribution. They apply to configurations having two mutually perpendicular planes of... | |
| ESDU Aero A.06.01.00 gives brief details of the methods provided in the Series for the estimation of rolling moment aerodynamic derivatives due to sideslip, rolling and yawing. The methods rely... | |
| ESDU Aero A.06.01.01 presents graphs plotting the rolling moment derivative as a function of aspect ratio, quarter-chord sweep angle, section lift-curve slope at the required Mach number, and Prandtl-Glauert compressibility... | |
| ESDU Aero A.06.01.03 gives curves for the variation with freestream Mach number, quarter-chord sweep angle, and section two-dimensional lift-curve slope, of the dihedral contribution to the derivative. The section lift-curve... | |
| ESDU Aero A.06.01.09 gives curves for the variation with freestream Mach number, quarter-chord sweep angle, and section two-dimensional lift-curve slope, of the dihedral or anhedral contribution to the derivative. The... | |
| ESDU Aero A.07.01.00 gives brief details of the methods provided in the Series for the estimation of yawing moment and sideforce aerodynamic derivatives due to sideslip, rolling and yawing. The... | |
| ESDU AERO A.08.01.05 gives a curve that allows the ratio of the chordwise position of the aerodynamic centre in incompressible flow (h0) to that in incompressible inviscid flow (h0T) to... | |
| ESDU AERO A.08.01.09 uses a criterion of similarity for conditions of uniform velocity and temperature distributions within and outside the jet to extend data for a cold jet to apply... | |
| ESDU Aero A.S.01.03.02 gives graphs derived from linearised supersonic flow theory for the lift-curve slope of a lifting surface as a function of aspect ratio, mid-chord sweep angle (which may... | |
| ESDU Aero A.S.02.03.01 indicates that the basis of the area rule is the fact that, within certain limitations, the flow around a wing-body combination at zero incidence may be represented... | |
| ESDU Aero A.S.06.03.01 presents graphs plotting the rolling moment derivative at zero lift for rigid uncambered wings with streamwise tips as a function of aspect ratio, mid-chord sweep angle and... | |
| ESDU Aero A.S.06.03.02 presents graphs plotting the ratio of the rolling moment derivative for wing alone to that for the wing in the presence of a body as a function... | |
| ESDU Aero A.S.06.03.03 presents a graph plotting a factor to be applied to the derivative, obtained from ESDU Aero A.S.06.03.01 for a pair of planar half wings, to correct for... | |
| ESDU Aero A.S.06.03.04 gives graphs derived from linearised supersonic flow theory for the centre of pressure position of a lifting surface as a function of aspect ratio, mid-chord sweep angle... | |
| ESDU Aero B.S.02.03 12 presents empirically derived curves of base pressure coefficient (based on conditions outside the boundary layer at the base of the body) for a boat-tailed body with... | |
| ESDU Aero B.S.02.03.01 introduces the concept of dividing the drag into inviscid wave drag, skin friction drag, viscous form drag and base drag. ESDU data for estimating skin friction and... | |
| ESDU Aero B.S.02.03.02 give curves plotting the wave drag coefficient of circular cross section ducted or pointed forebodies and truncated or pointed afterbodies as a function of freestream Mach number,... | |
| ESDU Aero B.S.02.03.08 gives curves for the interference wave drag, as a function of freestream Mach number and body geometry, that results from the disturbance to the flow over an... | |
| ESDU Aero C.01.01.01 gives graphs for the lift-curve slope derived by correlating results of wind-tunnel tests on models without simulated propeller slipstream. The lift-curve slope is based on an effective... | |
| ESDU Aero C.01.01.03 gives two graphs. The first plots the theoretical (in inviscid flow) rate of change of lift coefficient with control deflection against control chord to wing chord ratio... | |
| ESDU Aero C.01.01.04 states that the rate of change of the lift coefficient curve with control deflection for a surface with a control with a gap is given by the... | |
| ESDU Aero C.04.01.00 introduces methods given in the series for estimating the linear change in hinge moment due to a change in angle of attack or due to a control... | |
| ESDU Aero C.04.01.01 derives the slope of the hinge moment coefficient curve against incidence for a special series of aerofoils having straight upper and lower surfaces over the rear 10... | |
| ESDU Aero C.04.01.02 derives the slope of the hinge moment coefficient curve against control deflection for a special series of aerofoils having straight upper and lower surfaces over the rear... | |
| ESDU Aero C.04.01.03 provides graphs from which the effect of a nose balance on the rates of change of hinge moment coefficient with incidence and with control deflection may be... | |
| ESDU Aero C.04.01.04 gives graphs based on a correlation of experimental data that allow the increments to the slopes of the hinge moment curves against incidence and control deflection to... | |
| ESDU Aero C.04.01.06 gives equations for the rates of change of hinge moment coefficient with incidence and with control deflection which include a spanwise integration of their respective values in... | |
| ESDU Aero C.04.01.08 gives the rate of change of control hinge moment with deflection of a sealed tab in subsonic flow. A graph plots that quantity against the ratio of... | |
| ESDU Aero C.08.01.01 gives curves of rate of change with control deflection of pitching moment coefficient at constant lift coefficient in inviscid flow plotted against thickness/chord ratio for various values... | |
| ESDU Aero F.01.01.08 has been superseded by ESDU 93019 but is retained because other documents still current in the Series make reference to it. It is restricted to full-span single-slotted... | |
| ESDU Aero F.01.01.09 has been superseded by ESDU 95021 but is retained because other documents still current in the Series make reference to it. It is restricted to full-span flaps... | |
| ESDU Aero F.02.01.06 has been superseded by ESDU 08013 but is retained because it is used in the worked examples of ESDU 81013, ESDU 82011 and ESDU 84002. ESDU 08013... | |
| ESDU Aero F.02.01.07 gives curves that provide factors to correct the profile drag increment due to deflection of a full-span flap to give the increment for a part-span flap with... | |
| ESDU Aero F.05.01.01 provides data for the estimation of air loads on flaps and controls. For flaps it is found that the maximum normal load coefficient is substantially independent of... | |
| ESDU Aero S.00.01.10 gives curves of the ratios of static pressure/stagnation pressure, static temperature/stagnati on temperature, local velocity/speed of sound for stagnation conditions, local kinetic pressure/stagnation pressure, and local flow... | |
| ESDU AERO S.00.03.06 defines some of the expressions and quantities that occur frequently in calculations related to high-speed flow and summarises the basic thermodynamic concepts. Equations for such quantities as... | |
| ESDU Aero S.00.03.07 gives curves for the ratios of static pressure/stagnation pressure, static temperature/stagnati on temperature, local velocity/speed of sound for stagnation conditions and local kinetic pressure/stagnation pressure. The curves... | |
| ESDU AERO S.00.03.08 treats the two-dimensional supersonic flow expanding about a solid boundary in which the Mach waves are straight and the flow velocity and direction are constant along any... | |
| ESDU AERO S.00.03.09 provides properties of an attached plane shock that forms when a supersonic flow meets a sharp two-dimensional object. Graphs show the Mach number behind the shock and... | |
| ESDU AERO S.00.03.13, which is one of a group of four, presents data for the surface pressure coefficient on a sharp-nosed right-circular cone. The data are given in graphical form... | |
| ESDU AERO S.00.03.14 gives a table of the first- and second-order Busemann coefficients (and their ratio) that appear in the equation for the pressure coefficient in terms of the deflection... | |
| ESDU AERO S.00.03.15 provides curves of the ratios of total pressure across the shock ahead of the tube and of the static pressure upstream of the shock to the total... | |
| ESDU AERO S.00.03.16 provides graphs plotting against Mach number the value of the nose angle of a cone and of a two-dimensional wedge at which the nose shock is just... | |
| ESDU AERO S.00.03.22 gives equations for the enthalpy and the static pressure in the equilibrium zone behind the shock, and the density ratio across the shock, as functions of the... | |
| ESDU AERO S.00.03.23 gives curves of shock angle plotted against flow deflection angle for various values of the density ratio across the shock. When the shock angle is known the... | |
| ESDU AERO S.00.03.27 outlines, for each of the two calculations, the background theory which provides a basis for a worked example using the charts. For the isentropic expansion from rest... | |
| ESDU Aero W.00.03.01 gives theoretically-derive d curves of critical Mach number plotted against thickness/chord ratio for a range of lift coefficients from zero to 0.5, and for an elliptic cylinder... | |
| ESDU Aero W.01.01.01 has been superseded by ESDU 70011, which presents graphs of correlated lifting-surface theory results, but is retained in the Series because values from it must be used... | |
| ESDU Aero W.01.01.04 presents curves of the ratio of the wing or tailplane lift-curve slope with cut-out to that without cut-out plotted against cut-out span as a fraction of wing... | |
| ESDU AERO W.01.01.05 is retained in the Series because it is referred to and used in a number of ESDU documents in Aerodynamics. To obtain values of the slope of... | |
| ESDU AERO W.01.01.07 gives curves of maximum lift coefficient of symmetrical aerofoils at Mach numbers of 0.60, 0.70 and 0.75 as a function of the trailing-edge included angle and the... | |
| ESDU AERO W.02.04.00 introduces a number of ESDU documents dealing with the drag of aerofoils. ESDU AERO W.02.04.01 gives the drag of a flat plate for use with ESDU AERO... | |
| ESDU AERO W.02.04.01 gives curves of the drag of a flat plate (based on half wetted area) plotted against Reynolds number based on the length of the plate for various... | |
| ESDU AERO W.02.04.02 gives curves of form factor as a function of thickness/chord ratio and transition position on three types of aerofoils: conventional sections like the RAF or NACA four... | |
| ESDU AERO W.02.04.03 gives curves of form factor as a function of thickness/chord ratio and transition position on three types of aerofoils (representative of low-drag aerofoils such as the NACA... | |
| ESDU Aero W.02.04.09 plots against Reynolds number (based on l) values of the ratio l/k above which the location of the transition point is not affected. Here l is the... | |
| ESDU Aero W.02.04.11 plots curves of h/b against Reynolds number for various values of l/b. Here h is the height of the crest of the wave above the undistorted profile... | |
| ESDU Aero W.05.01.01 gives graphs of two parameters: wake thickness (measured normal to the freestream) divided by root chord and the kinetic pressure in the median plane of the wake... | |
| ESDU Aero W.S.00.03.04 tabulates formulae for the lift, wave drag and pitching moment coefficients and aerodynamic centre position of symmetric and non-symmetric double-wedge aerofoils and of biconvex aerofoils in terms... | |
| ESDU Aero W.S.00.03.05 presents curves for obtaining by the shock-expansion method the distribution of pressure coefficient around an aerofoil in supersonic flow with an attached nose shock wave. The curves... | |
| ESDU Aero W.S.00.03.18 provides a graph of the stagnation temperature in air taking into account the variation of the specific heat capacity at constant pressure of the air with temperature. | |
| ESDU Aero W.S.02.03.02 states that at low incidence the lift-dependent drag coefficient of a wing in supersonic flow can be written as the product of the incidence and the lift... | |
| ESDU Aero W.S.02.03.07 gives methods for turbulent or laminar boundary layers at the trailing edge. In the former case curves are given for two empirically determined contributions to the base... | |
| ESDU Aero W.S.02.03.09 presents a graph, using parameters defined by transonic similarity laws, of the variation of the wave drag coefficient at zero lift as a function of Mach number,... | |
| ESDU Aero W.S.02.03.10 gives curves of wave drag coefficient plotted against freestream Mach number for a two-dimensional parallel-sided section with leading edge formed by a semi-ellipse with its axis of... | |
| ESDU Aero W.S.02.04.12 gives curves for the skin friction drag coefficient of a flat plate plotted against the fraction of the plate for which the boundary layer is laminar for... | |
| ESDU Aero W.S.02.04.13 gives curves of profile drag of biconvex aerofoils plotted against transition position as a fraction of chord for values of freestream Mach number of 1.5, 2.5 and... | |
| ESDU Aero W.S.05.03.01 gives empirically-derived curves of static pressure as a fraction of the stagnation pressure behind a normal shock plotted against the ordinate of the nose measured from the... | |
| ESDU Aero W.S.08.03.02 gives curves of the derivatives plotted for straight-tapered wings with streamwise tips as a function of the wing aspect ratio, the sweep angle of the mid-chord line... | |
| ESDU B.S.05.03.01 gives the theoretically derived pressure distribution on pointed tangent ogive forebodies, and pointed parabolic arc and conical afterbodies, plotting at the nose or tail (as appropriate), at the... | |
| ESDU CFD-BPG 09010 provides the Best Practice Guidelines recommended by ESDU for the CFD modelling of friction losses and flow characteristics in circular straight pipes with smooth walls. These Guidelines... | |
| ESDU CFD-BPG 11010 provides the Best Practice Guidelines recommended by ESDU for the CFD modelling of pressure loss, discharge coefficient and flow characteristics in square- and knife-edged orifice plates. These... | |
| ESDU Fat A.00.01 introduces an R-M diagram which relates the alternating and mean stresses for some endurance. A number of such curves are plotted, each characterised by a value of... | |
| ESDU Fat A.00.02 shows how the R-M diagram for a notched specimen is obtained from one for a plain test piece of the same material. If elastic conditions existed the... | |
| ESDU Fat A.05.02 gives a method of estimating the endurance of pin joints from fatigue data on other types of specimen. From the results of photoelastic tests, curves are given... | |
| ESDU Fat E.05.01 presents three curves of alternating stress against endurance obtained from an analysis of 230 constant amplitude fatigue tests: a mean curve, a curve for an upper limit... | |
| ESDU Fat E.05.06 presents curves of alternating stress against endurance obtained from an analysis of 280 constant amplitude room temperature tests of joints with adherends 0.033 to 0.082 in (0.08... | |
| ESDU Fat E.05.07 presents curves of alternating stress against endurance obtained from an analysis of 130 constant amplitude room temperature tests of joints in sheet 0.128 in (3.3 mm) thick... | |
| ESDU Fat E.07.01 gives graphs showing the results of some 3500 constant amplitude tests on smooth machined or polished circular section specimens tested in reversed bending, as a rotating cantilever... | |
| ESDU Fat E.07.02 discusses the relevance of the data for plain specimens in ESDU Fat E.07.01, obtained under bending, to conditions of axial loading and concludes that the main cause... | |
| ESDU Fat E.07.03 provides graphs derived from the R-M diagram of ESDU Fat A.00.01 showing alternating stress plotted against endurance for a range of values of mean stress/tensile strength, each... | |
| ESDU FMI 2 provides the non-specialist with background information on the principles for calculating pressure gradients in two-phase flow. It also gives guidance on the statistical methods employed in ESDU... | |
| ESDU FMI1 provides guidance on simplified methods of calculating pressure losses in internal flow systems. It assists in the use of a series of Data Items in Volumes 1-4 of... | |
| ESDU ME1 provides an introduction to the use of ESDU 76005, a boxfile of transparent graphs that allows, for the complete range of four-bar planar linkages, the analysis of an... | |
| ESDU ME2 provides derivations of the basic kinematic relationships, as background information for users of the data on cam design. It covers the design of a disc cam with a... | |
| ESDU ME3 treats the relationships used in the performance analysis of internal and external Geneva mechanisms driven by a crank rotating at constant or varying speed and transmitting power using... | |
| ESDU PD MEMO 0301 describes procedures for the evaluation and correlation of vapour pressure data. Consideration is restricted to the evaluation of data for the vapour pressures of substances that... | |
| ESDU Perf ED1/1 gives graphs of power and thrust coefficient for propellers with activity factors of 350 and zero-lift angle at 0.7 radius of 3.1 degrees; guidance is given on... | |
| ESDU Perf ED1/2 gives curves of power and thrust coefficient as a function of total activity factor and blade angle at 0.7 radius. ESDU Perf ED1/1 provides information on the... | |
| ESDU Perf EG5/1 gives simple formulae for estimating the distance and the time in ground run, transition and climb out. It is suggested that the forces should be evaluated at... | |
| ESDU Perf EG6/2 discusses determining the speed for three types of approach: visual, instrument and carrier. For each case a recommendation is made for speed based on stall and using... | |
| ESDU Perf EG6/4 gives the equation for the ground run and suggests it may be solved approximately by assuming the decelerating force is constant at its value at a speed... | |
| ESDU Perf EG8/1 gives equations and a graph for estimating performance in a true-banked turn at a constant angle of climb or descent and with a constant angle of bank. | |
| ESDU Perf EG8/2 considers the manoeuvre of generating a rate of roll and then bringing it back to zero when a certain angle of bank has been attained. It gives... | |
| ESDU Perf RG2/1 gives simple methods for the incremental adjustment to a desired standard or datum condition of distances and speeds measured in tests. It applies to conventional aircraft and... | |
| ESDU Perf RJ1/2 discusses the problems of applying graphical methods to flight measured rate of climb results. Ideally a fixed relationship should be chosen between equivalent airspeed and weight and... | |
| ESDU Perf RJ2/0 discusses the incremental correction to standard atmosphere and aircraft conditions of flight measured data for level speed, range and endurance. It presents the relationships for thrust, fuel... | |
| ESDU Perf RJ2/1 gives two formulae for the incremental correction to standard atmosphere and aircraft conditions of flight measured data, one applying at constant pressure and one at constant temperature. | |
| ESDU PERF RP 1/0 gives the basis for a method developed for large piston engines with geared superchargers for the correction of flight-measured results to conditions of temperature and weight... | |
| ESDU PERF RP 1/1 gives formulae derived using the method of ESDU PERF RP 1/0 for the incremental correction of flight measured level speed data to temperatures and weights differing... | |
| ESDU Perf RP 1/2 gives formulae derived using the method of ESDU PERF RP 1/0 for the incremental correction of flight measured rate of climb data to temperatures and weights... | |
| ESDU PERF RP 1/3 gives formulae derived using the method of ESDU PERF RP 1/0 for the incremental correction of flight measured fuel consumption data to standard conditions. Tests may... | |
| ESDU PERF RP 2/0 provides a method for the incremental correction of flight-measured data to standard conditions at constant pressure height. Unlike the method in the group ESDU PERF RP... | |
| ESDU Perf RT 1/0 discusses the application of a graphical presentation of flight measured data to allow determination of aircraft performance at different atmospheric, aircraft weight and engine speed conditions... | |
| ESDU PERF RT 1/1 illustrates, through a worked example, the correction of flight measured level speed data to conditions of aircraft weight, engine speed and atmosphere different from those at... | |
| ESDU PERF RT 1/2 illustrates, through a worked example, the correction of measured rate of climb data to conditions of aircraft weight, engine speed and atmosphere different from those at... | |
| ESDU PERF RT 1/3 illustrates, through a worked example, the correction of flight measured range and fuel flow data to conditions of aircraft weight, engine speed and atmosphere different from... | |
| ESDU Struct 00.06.00 introduces a group of documents in the Structures Series that deal with the distribution of stresses in beams subjected to bending loads calculated under the assumption that... | |
| ESDU Struct 00.06.01 gives a graphical iterative method for determining the stress distribution corresponding to a bending moment, or the bending moment corresponding to a maximum strain for a reinforced... | |
| ESDU Struct 00.06.04 gives a graph that allows the distance of the shear centre from the centre-line of the wall of a circular-arc section, measured along the axis of symmetry... | |
| ESDU Struct 00.06.05 gives a graph that allows the distance of the shear centre from the centre-line of the web of a D-section to be readily determined. It plots that... | |
| ESDU Struct 00.07.00 introduces a group of documents in the Structures Series that deal with the behaviour of beams of thin-walled open cross section under torsion. It defines the torsion... | |
| ESDU Struct 00.07.01 gives graphs for the torsion constant of a bulb angle section with legs of equal thicknesses, and for the secondary warping constant of a bulb angle section... | |
| ESDU Struct 00.07.04 gives a graph for the primary warping constant of a Z-section either with bulbs on both flanges or without bulbs. The constant is a function of the... | |
| ESDU Struct 01.00.01 provides graphs, and the formulae from which they were calculated, for the moment of inertia of uniform thickness sections non-dimensionalised by the section area squared. For the... | |
| ESDU Struct 01.01.01 provides theoretically derived curves that treat the overall (flexural) buckling of struts in which the cross-section translates normal to the strut axis; the data include the effects... | |
| ESDU Struct 01.01.08 provides a graph from which the stress for initial local buckling of the web or flange of closed or open section struts can be obtained. Plasticity is... | |
| ESDU Struct 01.01.10 provides an equation from which the stress may be calculated at which initial torsional buckling occurs of a strut of any section in which the sides meet... | |
| ESDU Struct 01.01.19 introduces two methods for calculating the elasto-plastic local buckling stress and crippling stress of rectangular tube section struts.The first method is provided in the form of a... | |
| ESDU Struct 01.01.23 provides graphs from which the flexural buckling load on a composite strut of two components may be determined for all combinations of simply-supported and clamped end conditions... | |
| ESDU Struct 01.01.24 provides a series of theoretically derived graphs from which the buckling load can be determined, each graph being for a particular value of a stiffness parameter. The... | |
| ESDU Struct 02.00.00 gives yielding and failure criteria applying to materials subjected to combined loadings which may be compared to the results obtained from uniaxial tension testing in determining failure... | |
| ESDU Struct 02.01.02 provides curves from which the stress in the long edges of the plate can be determined from a knowledge of its dimensions, Young's modulus of the material,... | |
| ESDU Struct 02.01.03 gives a graph of the average stress (load divided by cross-sectional area) plotted against the edge stress in the direction of loading applicable to values of the... | |
| ESDU Struct 02.01.08 provides a graph that allows the edge stress to be determined at which sheet in compression buckles between the rivets. The method relies on the equation given... | |
| ESDU Struct 02.01.09 makes use of the curves in ESDU Struct 02.01.08 to construct a graph from which the edge stress at which the sheet between the rivets buckles may... | |
| ESDU Struct 02.01.10 provides a graph from which the buckling stress coefficient may be obtained for a slightly curved plate loaded along its axis with the edges clamped but subjected... | |
| ESDU Struct 02.01.11 provides graphs relating the average stresses to the stresses in the unloaded edges of a slightly curved plate loaded along its axis with the other edges clamped... | |
| ESDU Struct 02.01.16 provides values of the ratio of the edge stress in the panel at failure to the failure stress of the stiffener alone flexing in a direction normal... | |
| ESDU Struct 02.01.17 gives a nomogram that represents the method of ESDU Struct 02.01.16 for the determination of the edge stress at failure of a stiffened panel under compression. The... | |
| ESDU Struct 02.01.22 gives a graph plotting the buckling stress coefficient against plate length to width ratio for a plate loaded along its length under uniform compression, each curve relating... | |
| ESDU Struct 02.01.23 gives two graphs plotting, for various values of elastic lateral restraint applied to the long edges of a plate loaded in uniform compression along its length, the... | |
| ESDU Struct 02.01.24 provides data that allow the stiffness ratio to be determined of a plate under uniform compressive load applied parallel to its length. The edges of the plate... | |
| ESDU Struct 02.01.46 gives a graph from which the buckling coefficient of the plate may be obtained. Four curves are plotted against the ratio of the plate length to its... | |
| ESDU Struct 02.01.47 gives a graph from which the buckling stress coefficient of the panel may be obtained. Five curves are plotted against the ratio of the panel length to... | |
| ESDU Struct 02.01.48 gives graphs from which the buckling stress coefficient of a plate symmetrically tapered in plan may be obtained for all four cases of a pair of opposite... | |
| ESDU Struct 02.01.49 gives graphs from which the buckling stress coefficient of a plate tapered in thickness along its length may be obtained for all four cases of a pair... | |
| ESDU Struct 02.01.50 considers elastic buckling of a plate without initial irregularities loaded by uniform axial and circumferential stresses, the latter assumed to be due to internal or external pressure. | |
| ESDU Struct 02.04.01 applies to flat or curved rectangular plates and gives an empirical graph plotting a compressive stress ratio against a shear stress ratio. The former is the ratio... | |
| ESDU Struct 02.04.02 applies to an elastic plate loaded longitudinally in uniaxial compression combined with shear and having simply-supported edges. The plate is assumed to have an aspect ratio of... | |
| ESDU Struct 02.04.04 gives a graph from which the initial buckling may be predicted of a simply-supported isotropic rectangular plate under a linearly varying direct stress on one pair of... | |
| ESDU Struct 02.04.05 gives a graph from which the initial buckling may be predicted of a simply-supported isotropic rectangular plate under shear combined with a linearly varying direct stress on... | |
| ESDU Struct 03.06.06 provides a graph plotting the variation around the circumference of the frame of the ratio of the bending moment to the applied couple. A number of curves... | |
| ESDU Struct 03.06.07 provides a graph plotting the variation around the circumference of the frame of the ratio of the bending moment to the product of the applied tangential load... | |
| ESDU Struct 03.06.08 provides a graph plotting the variation around the circumference of the frame of the ratio of the bending moment to the product of the applied radial load... | |
| ESDU Struct 03.06.09 provides a graph plotting the variation around the circumference of the frame of the ratio to the applied couple of the product of the direct force in... | |
| ESDU Struct 03.06.10 provides a graph plotting the variation around the circumference of the frame of the ratio of the direct force in the frame to the tangential load. A... | |
| ESDU Struct 03.06.11 provides a graph plotting the variation around the circumference of the frame of the ratio of the direct force in the frame to the applied radial load. | |
| ESDU Struct 03.06.12 provides a graph plotting the variation around the circumference of the frame of the ratio to the applied couple of the product of the shear force in... | |
| ESDU Struct 03.06.13 provides a graph plotting the variation around the circumference of the frame of the ratio of the shear force in the frame to the applied tangential load. | |
| ESDU Struct 03.06.14 provides a graph plotting the variation around the circumference of the frame of the ratio of the shear force in the frame to the applied radial load. | |
| ESDU Struct 03.06.15 provides three sets of three graphs; each set of three graphs shows the variation around the circumference of the frame of a deflection due to an applied... | |
| ESDU Struct 03.06.16 gives three graphs showing the variation around the circumference of the frame of the shear flow from the shell to the frame. Each graph applies to one... | |
| ESDU Struct 03.06.17 provides, for a stringer stiffened skin supported by a frame, curves of effective skin-frame stiffness ratio (involving the equivalent frame spacing) plotted against actual skin-frame stiffness ratio. | |
| ESDU Struct 07.03.01 considers the transverse stiffness of a symmetrical sandwich panel in which the core and identical face-plates are of the same material. The corrugated core cross-section (that is,... | |
| ESDU TM 119 provides the theoretical background for the calculation of area and moment properties of planar shapes. The Memorandum supports ESDU 02007 that introduces a computer program, AMOPS, that... | |
| ESDU TM 151 gives details of the stresses in the tread material of an unloaded inflated tyre. This Memorandum supports ESDU 10015. | |
| ESDU TM 161 provides a background to part of a larger study that deals with the performance of aircraft tyres rolling or braking on dry and precipitate runways. | |
| ESDU TM 167 reports on an evaluation of the Mumeter Mk 6, a continuous friction measuring device. The memorandum briefly describes the device and provides an analysis of test data... | |
| ESDU TM 168 contains analysis which provides the derivation and substantiation of equations given in ESDU 76003 for the geometric properties of straight-tapered and multi-panel wings.Firstly, this Technical Memorandum presents... | |
| ESDU TM 169 provides a brief background to the development of the compressible form of the Helmbold-Diederich equation for wing lift-curve slope, a simple analytical equation which was in common... | |
| ESDU TM 96 considers the operation of an aircraft tyre on a surface covered in slush. The Item examines the physical characteristics of snow and slush, describing slush as water-saturated... | |
| ESDU W.S.00.03.03 discusses the flow around an aerofoil in inviscid flow and explains how the velocity and pressure distributions, and hence the forces on the aerofoil, can be obtained from... | |
| Example 1 demonstrates the analysis of an external Geneva mechanism in an existing machine, in which the crank angular velocity varies during each rotation. The external torque driven by the... | |
| Expressions for the contact force between a cam and a follower and for the radius of curvature of the cam profile at the contact point are required in ESDU 93001,... | |
| Expressions for the velocity of entrainment of a lubricant film between a disc cam and both a translating follower and swinging arm follower are derived. The follower types include domed,... | |
| For aerofoils, the method of ESDU 98009 predicts the centre of lift position based on thin-aerofoil theory with empirical correction to obtain agreement with extensive experimental data. This is combined... | |
| For aerofoils, the method of ESDU 98017 predicts the centre of lift position based on thin-aerofoil theory with empirical correction to obtain agreement with extensive experimental data. This is combined... | |
| In this Technical Note, the ESDU CFD validation studies are presented for the prediction of friction losses and flow characteristics in straight circular pipes with smooth walls. Accurate prediction of... | |
| Many varied methods exist for the derivation of optimum aerofoil shapes by the combined use of numerical optimisation techniques (optimisers) and Computational Fluid Dynamics (CFD). Some are capable of optimisation... | |
| No abstract available for this Item. | |
| Policy statement on the notation and units used throughout the Performance Series. | |
| Produced in support of ESDU 76027. | |
| Provides methods for aerofoil lift-curve slope, zero-lift incidence, zero-lift pitching moment, position of aerodynamic centre. | |
| Statistical Energy Analysis (SEA) is a method for estimating the approximate dynamic response of coupled, mechanical or acoustical, elements at high frequencies. The underlying theory behind SEA is fundamentally different... | |
| Superseded by Item Nos 98009, 98017, 99004, 99014 and 01013. See also Item Nos 97002, 00029 and 03017. | |
| The construction of the input file for the program, which is based on twenty-two existing Data Items, is described. The program applies to aerofoils, wings and wing-fuselage combinations with or... | |
| The fundamental definition of a pressure loss coefficient implicitly assumes that the flow at the reference sections is uniform or one-dimensional. In contrast, the interpretation of measurements from experiment or... | |
| The three standard loading sequences described in this Data Item are: TWIST (and Mini-Twist), FALSTAFF (and ENSTAFF) and Helix/Felix.The TWIST (Transport WIng STandard) loading sequence was developed to be representative... | |
| This CFD Guide provides Best Practice Guidelines recommended by ESDU for the modelling, using Computational Fluid Dynamics (CFD), of pressure and flow characteristics in circular pipes with sudden contractions in... | |
| This CFD Guide provides reliable benchmark data for the validation of CFD predictions in circular pipes with sudden contractions in incompressible flow. Input geometrical and flow parameters for sharp-, round-,... | |
| This CFD Guide provides reliable benchmark data for the validation of CFD predictions in straight pipes in incompressible flow. Input geometrical and flow parameters for circular straight pipes with smooth... | |
| This Data Item describes the installation details, hardware requirements and configuration details for OSMEC, a general-purpose mechanism designprogram. The configuration details of associated printers and plotters is also provided. OSMEC... | |
| This Data Item provides a method for representing - and, if necessary, relating - the braking performances of aircraft and ground-test machines in wet conditions. The method is essentially statistical... | |
| This Data Item provides a user manual for OSMEC, a general-purpose linkage design program, which can model plane mechanisms composed of links, pivoted and sliding joints, gear trains, springs and... | |
| This is a brief introduction to the content of the Series relating to beams, struts and shafts, considering buckling of and safety factors for struts and allowable stresses in beams... | |
| This is the first in a sequence of Data Items to accompany the VGK method for two-dimensional aerofoil sections. VGK is a CFD (computational fluid dynamics) method coded in Fortran... | |
| This is the second in a sequence of Data Items to accompany the VGK method for two-dimensional aerofoil sections. VGK is a CFD (computational fluid dynamics) method coded in Fortran... | |
| This Memorandum describes a computation procedure for the estimation of natural frequencies and mode shapes of isotropic and orthotropic rectangular plates under static in-plane loading. The static in-plane loading, uniformly... | |
| This Technical Note describes the CFD studies conducted by ESDU for the validation of the predictions of pressure loss and flow characteristics in sharp-, round- and chamfer-edged sudden contractions, in... | |
| This Technical Note discusses the studies conducted by ESDU for the CFD validation of the predictions for pressure loss, discharge coefficient and flow characteristics in square-edged orifice plates. These studies... | |
| This Technical Note provides a review of the data in the literature for incompressible flow through orifice plates published prior to 2006. These data include measurements and numerical predictions of... |
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