Numerical and Test Investigation on an Aircraft Inlet Distortion

Abstract

Subscale wind tunnel test of an aircraft vehicle is performed at different Mach number, mass-flow and angle of attack. CFD model, corrected by test results, is also presented to predict inlet performance and total pressure distortion. The result shows total pressure recovery decreases and distortion level rises when Mach number increases from subsonic to supersonic speed, AOA is negative and mass-flow value is too large or too small. Compared linear interpolation based on test result of discrete probes, numerical simulation has advantages in showing inlet flow field predicting actual surface distortion level in AIP plane. Swirl distortion is induced by vortex near the fuselage and adjustable ramp and can strengthen total pressure distortion in AIP at negative AOA. And appropriate suction mass-flow coefficient (1.7% to 3%) is beneficial for inlet performance and total pressure distortion control.

Approach for an Optimized Evaluation of Pressure and Swirl Distortion in S-Shaped Engine Inlet Con[|#12#|]figurations

“…It exemplarily resulted from experiments by Zhang et al 9 that 30 probes in the AIP lead to a misinterpretation of the distortion pattern in that specific case. A nearly endless amount of data can be obtained by the use of a traversable device.…”