A computational study was performed to explore the aerodynamic performance of a streamline-traced, external-compression inlet designed for Mach 1.664 at off-design conditions of freestream Mach number, angle-of-attack, and angle-of-sideslip. Serious degradation of the inlet performance occurred for negative angles-of-attack and angles-of-sideslip greater than 3 degrees. At low subsonic speeds, the swept leading edges of the inlet created a pair of vortices that propagated to the engine face. Increasing the bluntness of the cowl lip showed no real improvement in the inlet performance at the low speeds, but did improve the inlet performance at the design conditions. Reducing the inlet flow rate improved the inlet performance, but at the likely expense of reduced thrust of the propulsion system. Deforming the cowl lip for low-speed operation of the inlet increased the inlet capture area and improved the inlet performance.
Off-Design Performance of a Streamline-Traced, External-Compression Supersonic Inlet
International Symposium on Air Breathing Engines (ISABE) ; 2017 ; Manchester, United Kingdom
2017-09-03
Conference paper
No indication
English
Vortex Generators in a Streamline-Traced, External-Compression Supersonic Inlet (AIAA 2017-1383)
British Library Conference Proceedings | 2017
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