[1] William H H, David T P. Hypersonic air breathing pro-pulsion. AIAA: AIAA Education Series, 1994. [2] McClinton C R, Rausch D R. Hyper-X program status. AIAA-2001-1910, 2001. [3] Marshall L A, Bahm C, Corpening G P. Overview with results and lessons learned of the X-43A Mach 10 flight. AIAA-2005-3336, 2005. [4] Hank J M. Air force research laboratory hypersonic propulsion research programs. AIAA-2007-5371, 2007. [5] Boudreau A H. Hypersonic air-breathing propulsion efforts in the air force research laboratory. AIAA-2005-3255, 2005. [6] Emami S, Trexler C A, Auslender A H. Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4. NASA Technical Paper 3502, 2010. [7] Witte D W, Huebner L D, Trexler C A. Propulsion airframe integration test techniques for hypersonic air breathing configurations at NASA Langley Research Center. AIAA-2003-4406, 2003. [8] Bakos R J, Tsai C Y, Rogers R C, et al. Hyper-X Mach 10 engine flow path development: fifth entry test conditions and methodology. AIAA-2001-1814, 2001. [9] Li P, Guo R W. Investigation of a hypersonic inlet with rectangular-to-circular shape transition and forebody. Acta Aeronautica et Astronautica Sinica, 2009, 30(4): 625-629. (in Chinese) 李璞, 郭荣伟. 一种带前体的高超声速矩转圆形进气道研究, 航空学报, 2009,30(4): 625-629. [10] Li L G, Tan H J, Sun S, et al. Signal characteristics and prediction of unstarting process for two dimensional hypersonic inlet. Acta Aeronautica et Astronautica Sinica. 2010, 31(12): 2324-2331. (in Chinese) 李留刚, 谭慧俊, 孙姝, 等. 二元高超声速进气道不起动状态的信号特征及预警. 航空学报, 2010, 31(12): 2324-2331. [11] Huebner L D, Rock K E, Witte D W. Hyper-X engine testing in the NASA Langley 8-foot high temperature tunnel. AIAA-2000-3605, 2000. [12] Davis M C, Sim A G. Wind tunnel results of the B-52B with the X-43A stack. AIAA-2006-3850, 2006. [13] Yuan H C. Designing methodology and flow characteristic of hypersonic variable geometry inlet with rectangular section. Nanjing: College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, 2008. (in Chinese) 袁化成. 矩形截面高超声速变几何进气道设计方法及气动特性研究. 南京: 南京航空航天大学能源与动力学院, 2008. [14] Yuan H C, Guo R W. Design and experimental verification of hypersonic inlet with rectangular section. Journal of Nanjing University of Aeronautics & Astronautics, 2009, 41(4): 423-428. (in Chinese) 袁化成, 郭荣伟. 矩形截面高超声速进气道气动设计及试验验证. 南京航空航天大学学报, 2009, 41(4): 423-428. [15] Yuan H C, Guo R W. High enthalpy wind tunnel tests of hypersonic inlets with rectangular section. Journal of Aer-ospace Power, 2010, 25(12): 2748-2755. (in Chinese) 袁化成, 郭荣伟. 矩形截面高超声速进气道高焓风洞试验. 航空动力学报, 2010, 25(12): 2748-2755. |