F/A inlet calculations at 60-deg angle of attack and 10-deg sideslip

Podleski, Steve D.

doi:10.2514/3.23823

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2013

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“…Inlet total pressure distortion affects on aircraft propulsion systems at high angle of attack (AOA) and angle of sideslip (AOSS) [1][2][3]. Under inlet distortion, not only surge and rotating stall of compressor pose a threat to aeroengine safety, but also forced response of fan and compressor blades may cause structure failure [4][5][6].…”

Section: Introductionmentioning

confidence: 99%

Numerical and Test Investigation on an Aircraft Inlet Distortion

Zhang

Hou

Chen

et al. 2013

Int. J. Turbo Jet-Engines

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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.

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Section: Introductionmentioning

confidence: 99%