Author
Nan Xiang
Bio: Nan Xiang is an academic researcher. The author has contributed to research in topics: Mach number & Inlet. The author has an hindex of 1, co-authored 1 publications receiving 2 citations.
Topics: Mach number, Inlet
Papers
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Journal Article•
TL;DR: In this article, a 2D curved compression with controlled pressure rise law is used to design a 2-D hypersonic inlet with wide operation range of Ma 2-7 at design point of Ma 6 for RBCC engine.
Abstract: Design method of 2-D curved compression with controlled pressure rise law is used to design a 2-D hypersonic inlet with wide operation range of Ma 2-7 at design point of Ma 6 for RBCC engine.A sweep forward side wall is used to reduce internal contraction ratio of inlet,and air bleeding slots are placed on top wall to expand operation range of inlet below Ma 4.Three dimensional numerical simulation is conducted in the range of Ma 1.5-7.The numerical results show that the new-type 2-D inlet with curved compression has less shock waves,good flow field structure and excellent performance in the range of Ma 4-7.With air bleeding on top wall,it can operate well in the range of Ma 1.5-4,and the air bleeding mass ratio is below 15%.Analysis turns out the curved compression inlet has high performance above Ma 4,but low mass capture capability below Ma 4.
2 citations
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TL;DR: A comprehensive and systematical review of the research progress on the inlets for RBCC engines in different countries and different historical periods is presented in this paper, where a number of key technical and scientific issues are sorted out, including inlet design and optimization, inlet/embedded rocket/combustor matching and control, dynamic operation, etc.
16 citations
01 Jan 2020
TL;DR: In this paper, the concave curved shock wave described in this book greatly improves the concept of the above linear shock wave, thus opening a completely new design platform from pneumatic design to geometric design.
Abstract: In the research history of supersonic-hypersonic inlet, the concept of isentropic compression with zero inviscid loss is not new. The wedge + isentropic curved compression or cone + isentropic curving cone compression has been successfully applied to all kinds of aircrafts, the relatively simple design method of which has become mature, and the head wave of this compression method is just a typical plane oblique shock wave or linear cone shock wave. The concave curved shock wave described in this book greatly improves the concept of the above linear shock wave, thus opening a completely new design platform from pneumatic design to geometric design. In recent years, the concept of high speed flow being compressed on the curvature controllable continuous curved surface has gradually been understood and accepted by many organizations and researchers in China, and many design methods have been developed and applied to the pneumatic design of inlets of aircrafts. From the perspective of the development trend of hypersonic inlet, curved compression has become an inevitable trend.