32th Congress of the International Council of the Aeronautical Sciences

05 - Propulsion

A DESIGN METHOD OF AN AXISYMMETRIC HYPERSONIC INLET INTERGRATED WITH A LONG FOREBODY

S.C. Xu¹, Y. Wang¹, Z.G. Wang¹, X.Q. Fan¹, B. Xiong¹; ¹National University of Defense Technology, China

This study focuses on the design method of an axisymmetric hypersonic inlet integrated with a long forebody. A novel flowfield of streamline-on-lip is proposed and solved to design the integrated forebody/inlet configuration. Results show that the obtained model has advantages on both aerodynamic performances and volume capacity.


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