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 combination. It is assumed there that the incidence and pitch angle are small enough for load estimation to be made by linear superposition. The wing shear force, bending moment and torque variations along the span are determined relative to a flexural axis for both an unswept high aspect ratio wing and for a swept, medium to high aspect ratio wing. In the former case a straight flexural axis is defined perpendicular to the aircraft plane of symmetry; a load applied to that axis will cause bending only, while a torque applied about it (in a plane normal to it) will cause only twist about it. In the latter case two types of flexural axis are considered: a straight axis parallel to the sweep line of the wing (an effective root chord is thereby defined that is not parallel to the aircraft plane of symmetry) about which the wing is assumed to bend and a curved axis along the span when the wing is assumed to bend and twist in a plane parallel to the aircraft plane of symmetry. For the fuselage the forces and moments are taken along the aircraft centre line in the plane of symmetry and only shear forces and bending moments are determined.
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-nacelle combination. It is assumed there that the incidence and pitch angle are small enough for load estimation to be made by linear superposition. The wing shear force, bending moment and torque variations along the span are determined relative to a flexural axis for both an unswept high aspect ratio wing and for a swept, medium to high aspect ratio wing. In the former case a straight flexural axis is defined perpendicular to the aircraft plane of symmetry; a load applied to that axis will cause bending only, while a torque applied about it (in a plane normal to it) will cause only twist about it. In the latter case two types of flexural axis are considered: a straight axis parallel to the sweep line of the wing (an effective root chord is thereby defined that is not parallel to the aircraft plane of symmetry) about which the wing is assumed to bend and a curved axis along the span when the wing is assumed to bend and twist in a plane parallel to the aircraft plane of symmetry. For the fuselage the forces and moments are taken along the aircraft centre line in the plane of symmetry and only shear forces and bending moments are determined.
