[1] Kantrowitz A, Donaldson C D. Preliminary investigation of supersonic diffusers. NACA Report ACR L5D20, 1945. [2] Barber T J, Hiett D, Fastenberg S. CFD modeling of the hypersonic inlet starting problem. AIAA-2006-123, 2006. [3] van Wie D M, Kwok F T, Walsh R F. Starting characteristics of supersonic inlets. AIAA-1996-2914, 1996. [4] Hagenmaier M A, Tam C J, Chakravarthy S. Study of moving start door flow physics for scramjet. AIAA-1999-4957, 1999. [5] Wang Y, Fan X Q, Liang J H, et al. Experimental investigation on the starting characteristics of a hypersonic inlet with moving entrance door. Journal of Aerospace Power, 2008, 23(6): 1014-1018. (in Chinese) 王翼, 范晓樯, 梁剑寒, 等.开启式高超声速进气道启动性能试验.航空动力学报, 2008, 23(6): 1014-1018. [6] Huebner L D, Rock K E, Ruf E G, et al. Hyper-X flight engine ground testing for X-43 flight risk reduction. AIAA-2001-1809, 2001. [7] Falempin F, Wendling E, Goldfeld M, et al. Experimental investigation of starting process for a variable geometry air inlet operating from Mach 2 to Mach 8. AIAA-2006-4513, 2006. [8] Colville J R, Lewis M J. An aerodynamic redesign of the SR-71 inlet with application to turbine based combined cycle engines. AIAA-2004-3481, 2004. [9] Maru Y, Tanatsugu N, Tetsuya S, et al. Multi-row disk arrangement concept for spike of axisymmetric air inlet. AIAA-2004-3407, 2004. [10] Kobayashi H, Tanatsugu N, Tetsuya S, et al. Experimental study of multi-row disk inlets for hypersonic air breathing propulsion. AIAA-2004-861, 2004. [11] Gruhn P, Gülhan A. Experimental investigation of a hypersonic inlet with and without sidewall compression. Journal of Propulsion and Power, 2011, 27(3): 718-728. [12] Luo X C, Zhou C S, Ju Y T. Numerical investigation on performance improvement of two-dimensional fixed-geometry inlet at low Mach numbers. Journal of Propulsion Technology, 2010, 31(4): 390-393. (in Chinese) 骆晓臣, 周长省, 鞠玉涛.提高固定几何二元进气道低马赫数性能的仿真研究.推进技术, 2010, 31(4): 390-393. [13] Jin Z G, Zhang K Y. Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression. Journal of Propulsion Technology, 2005, 26(6): 508-512. (in Chinese) 金志光, 张堃元.带前体压缩的前掠侧压式进气道实验及数值研究.推进技术, 2005, 26(6): 508-512. [14] Jin Z G, Zhang K Y. Test of a generic sidewall compression scramjet inlet in the high-enthalpy impulse wind tunnel. Journal of Propulsion Technology, 2005, 26(4): 319-323.(in Chinese) 金志光, 张堃元.高超侧压式进气道M6高焓脉冲风洞实验.推进技术, 2005, 26(4): 319-323. [15] Ding H H, Wang F M. Hypersonic inlet start characteristics numerical study. Journal of Astronautics, 2007, 28(6): 1482-1487. (in Chinese) 丁海河, 王发民.高超声速进气道起动特性数值研究.宇航学报, 2007, 28(6): 1482-1487. |