IHS ESDU The correction of flight-test anemometric data. 83029

ESDU 83029 gives a comprehensive and systematic procedure for the correction of sensed anemometric data. It is directed particularly to measurements made during flight tests on prototype or test aircraft for speeds up to Mach 6 and altitudes to 120 000 ft (35 000 m). After outlining the geometric data and sensor calibration data required in the correction process, the quantities to be measured are indicated, and the preliminary processing to obtain average values explained. Four flowcharts guide the user through the possible calculation procedures in the correct sequence. For some corrections alternative methods are given whose usage depends on the available input data. Not all corrections are necessary for all classes of aircraft. Once the various individual corrections to the data sensed by the pitot and static pressure systems and the temperature sensing system have been derived (including static pressure error), the true values of the following quantities are obtained: (i) pitot and ambient static pressures, pressure height, Mach number, calibrated and equivalent airspeeds, and kinetic and total pressures; (ii) ambient temperature, density, viscosity, true airspeed and Reynolds number; (iii) specific excess power.