| Citation: | ZHANG Lin, ZHANG Kun-yuan, WANG Lei, LIU Yuan. Computational investigation of hypersonic curved shock two-dimensional inlet with compression surface constant Mach number gradient[J]. Journal of Aerospace Power, 2013, 28(4): 752-758. |
| [1] |
Curran E T.Scramjet engines:the first forty years[J].Journal of Propulsion and Power,2001,17(6):1138-1148.
|
| [2] |
Connors J F,Woollett R R.Performance characteristics of several types of axially symmetric nose inlets at Mach number 3.85 [R].NACA RM E52I15,1952.
|
| [3] |
Sorensen N E,Smeltzer D B.Study of two axisymmetric inlets for Mach 3.5 [R].AIAA-1976-0204,1976.
|
| [4] |
Trexler C A.Performance of an inlet for an intergraded scramjet concept[J].Journal of Aircraft,1974,11(9):588-591.
|
| [5] |
Mölder S,Szpiro J.Busemman inlet for hypersonic speeds[J].Journal of Spacecraft and Rockets,1966,3(8):1303-1304.
|
| [6] |
Smart M K.Design of three-dimensional hypersonic inlets with rectangular to elliptical shape transition [R].AIAA-98-0960,1998.
|
| [7] |
金志光,张堃元.二维非常规压缩型面超/高超声速进气道的设计概念[J].推进技术,2004,25(3):226-229. JIN Zhiguang,ZHANG Kunyuan.Concept of a two-dimensional supersonic/hypersonic inlet with a non-conventional compression wall[J].Journal of Propulsion Technology,2004,25(3):226-229.(in Chinese)
|
| [8] |
PAN Jin,ZHANG Kunyuan.Experimental and numerical investigation of a curved compression system designed on constant pressure gradient [R].AIAA-2009-5270,2009.
|
| [9] |
南向军,张堃元,金志光,等.压升规律可控的高超声速内收缩进气道设计[J].航空动力学报,2011,26(3):518-523. NAN Xiangjun,ZHANG Kunyuan,JIN Zhiguang,et al.Investigation on hypersonic inward turning inlets with controlled pressure gradient[J].Journal of Aerospace Power,2011,26(3):518-523.(in Chinese)
|
| [10] |
NAN Xiangjun,ZHANG Kunyuan.Numerical and experimental investigation on hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise [R].AIAA-2011-2270,2011.
|
| [11] |
张林,张堃元,王磊,等.新型高超弯曲激波二维进气道初步研究[J].航空动力学报,2011,26(11):2556-2562. ZHANG Lin,ZHANG Kunyuan,WANG Lei,et al.Preliminary study on hypersonic curved shock two-dimensional inlet[J].Journal of Aerospace Power,2011,26(11):2556-2562.(in Chinese)
|
| [12] |
向有志,张堃元,王磊,等.壁面压升可控的高超轴对称进气道优化设计[J].航空动力学报,2011,26(10):2193-2199. XIANG Youzhi,ZHANG Kunyuan,WANG Lei,et al.Optimization design of hypersonic axisymmetric inlet with controllable law of wall pressure rise[J].Journal of Aerospace Power,2011,26(10):2193-2199.(in Chinese)
|
| [13] |
Anderson B H.Design of supersonic inlets by a computer program incorporating the method of characteristics .NASA TN D-4960,1969.
|
| [14] |
金志光,张堃元.高超侧压式进气道M6高焓脉冲风洞实验[J].推进技术,2005,26(4):319-323. JIN Zhiguang,ZHANG Kunyuan.Test of a generic sidewall compression scramjet inlet in the high-enthalpy impulse wind tunnel[J].Journal of Propulsion Technology,2005,26(4):319-323.(in Chinese)
|
| [15] |
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[J].推进技术,2005,26(6):508-512. JIN Zhiguang,ZHANG Kunyuan.Experimental and numerical investigation of a forward sweep sidewall compression scramjet inlet with forebody compression[J].Journal of Propulsion Technology,2005,26(6):508-512.(in Chinese)
|