Aircraft performance from flight test Part 1: derivation of a mathematical model
ESDU 15001 considers the derivation, from flight test, of an aerodynamic model for the purpose of aircraft performance prediction. The analysis is limited to rigid fixed-wing aircraft (aeroplanes) of a conventional "aft-tailed" configuration with an all moving tail and one, or more, turbojet/fan engines. However, the principles are readily extended to less conventional configurations and propeller driven aircraft.
The analysis requires a test aircraft fitted with three accelerometers mounted orthogonally within the airframe and a means of determining rotational rates and accelerations about the three axes. Precise air data are also required so that Mach number, airspeeds, altitude and angles of attack and sideslip can be determined.
This Item is the first in a series devoted to the prediction of aircraft performance from flight test analysis.
- Engines (in Aircraft)
- Flight Instrumentation
- Flight Testing
|Data Item ESDU 15001|
- Aircraft Noise
- Fatigue - Endurance Data
- Fatigue - Fracture Mechanics
- Fluid Mechanics, Internal Flow
- Fluid Mechanics, Internal Flow (Aerospace)
- Heat Transfer
- Physical Data, Chemical Engineering
- Stress and Strength
- Transonic Aerodynamics
- Vibration and Acoustic Fatigue
- Wind Engineering