Numerical and Test Investigation on an Aircraft Inlet Distortion
-
Zhang Zhang
,
Yinxiu Chen
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.
©[2013] by Walter de Gruyter Berlin Boston
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Articles in the same Issue
- Masthead
- Fatigue Reliability Analysis of Turbine Disk Alloy Using Saddlepoint Approximation
- Numerical and Test Investigation on an Aircraft Inlet Distortion
- Aero-acoustic Properties of Eroded Airfoils of Compressor Blades for Use in Non-invasive Diagnostics
- Performance of a Turboprop Engine with Heat Recovery in Off-Design Conditions
- Experimental Study on DDT Characteristics in Spiral Configuration Pulse Detonation Engines
- Thrust Estimates of a Partially Filled Multi-Cycle Pulse Detonation Rocket Engine
- Investigation of Tip Leakage Flow and Stage Matching with Casing Treatment in a Transonic Mixed-Flow Compressor
- Design and Performance Study of an Ocean Current Turbine Generator
- Review on the Recent Development of Multi-mode Combined Detonation Engine
