Example of analysis and representation of static pressure correction data in steady flight.
Abstract: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 a theoretical framework to provide static pressure corrections as a functional relationship over the flight envelope. The pressure transducer had a precision of 1 lbf/sq ft at a 95 per cent confidence level and so only the most significant parameters were considered. Data were obtained from low-speed wind-tunnel testing, low-speed flights past an accurate barometer on a tower, and high-speed flights in formation with a calibrated aircraft. Those last results were reduced by use of transonic similarity. From that relatively modest set of data a valid calibration is derived and is shown through a statistical analysis to be precise to within 0.2 lbf/sq ft and the correlation is effected with a confidence interval of 1.1 lbf/sq ft.
|Data Item ESDU 95024|
- 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
Aerospace Materials Data
Additional Engineering References