Complex flow field structure, which is induced by the leading edge of V-shaped cowl-lip in hypersonic inward turning inlet, causes severe thermal load. The V-shaped cowl-lip is simplified as the V-shaped leading edge. Both wind tunnel tests and numerical simulations are applied to study the flow field structures. And numerical simulation is used to investigate the heat flux. The result shows that the V-shaped leading edge, compared with blunt body and slender body, presents complex shock wave interaction and suffers from critical aerodynamic heating. The shape parameter of the V-shaped leading edge, angle θ of the leading edge, is not a sensitive parameter of the heat flux. It does not effectively reduce the maximum of the heat flux. Another shape parameter, ratio (R/r) of rounded radius and blunted radius, has obvious effect on the peak value of the heat flux. The heat flux does not decrease necessarily with increasing R/r when R/r<2. It reduces significantly with increasing R/r when 2<R/r<6. The heat flux does not change much with changing R/r when R/r>6.
Lewis MA. Hypersonic propulsion airframe integration overview. In: 39th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit, Huntsville, AL USA, 20–23 July 2003, AIAA Paper No. 03-4405.
3.
WuYCHeYHeW. Progress in airframe-propulsion integration technology of air-breathing hypersonic vehicle. Acta Aeronaut Astronaut Sin2015; 36: 245–260.
4.
YouYCet al.Overview of the integration of three-dimensional inward turning hypersonic inlet and waverider forebody. Adv Mech2009; 39: 513–525.
5.
Kothari AP, Tarpley C, Mclaughlin TA, et a1. Hypersonic vehicle design using inward turning flow fields. In: 32nd AIAA/ASME/SAE/ASEE, joint propulsion conference and exhibit, Lake Buena Vista, FL, USA, 1–3 July 1996, AIAA Paper No. 96-2552.
Billig FS. Design and analysis of streamline traced hypersonic inlets. In: 9th international space planes and hypersonic systems and technologies conference, Norfolk, 1999.
8.
Malo-Molina FJ and Gaitonde DV. Numerical investigation of an innovative inward turning inlet. In: 17th AIAA computational fluid dynamics conference, Toronto, ON, Canada, 2005.
9.
DongHWangC-P. Experimental and numerical investigation of hypersonic JAWS inlet. Mod Phys Lett B2010; 24: 1409–1412.
10.
YouYCLiangDW. Design concept of three-dimensional section controllable internal waverider hypersonic inlet. Sci China Ser E-Tech2009; 52: 2017–2028.
11.
SmartMK. Experimental testing of a hypersonic inlet with rectangular-to-elliptical shape transition. J Propul Power2001; 17: 276–283.
12.
SmartMKTrexlerCA. Mach 4 performance of hypersonic inlet with rectangular-to-elliptical shape transition. J Propuls Power2004; 20: 288–292.
13.
Walker HS. Hypersonic Collaborative Australia/United States Experiment (HYCAUSE). AIAA-2005-3254, 2005.
14.
Tam CJ, Robert AB and Gary DS. Numerical analysis of streamline-traced hypersonic inlets. AIAA-2003-13, 2003.
15.
LiuXLiangJWangY. Research on the effect of cowl-lip lip angle on the accelerating start process of a two-dimensional hypersonic inlet. Proc IMechE, Part G: J Aerospace Engineering2016; 230: 2615–2627.
16.
MahapatraDJagadeeshG. Shock tunnel studies on cowl-lip/ramp shock interactions in a generic scramjet inlet. Proc IMechE, Part G: J Aerospace Engineering2008; 222: 1183–1191.
17.
Edney B. Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Technical Report, FFA 115, Aeronautical Research Institute of Sweden, 1968.
18.
EghlimaZMansourKFardipourK. Heat transfer reduction using combination of spike and counterflow jet on blunt body at high Mach number flow. Acta Astronaut2017; 143: 92–104.
19.
Fuchs L and Hallqvist T. Numerical study of impinging jets with heat transfer-inlet conditions effects. In: AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition, 2009. Reston, VA: AIAA.
20.
ChangJTBaoW. Effects of wall cooling on performance parameters of hypersonic inlets. Acta Astronaut2009; 65: 467–476.
21.
ZhouWWangDBaoWet al.Experimental method study on heat flux measurement on sharp leading edge. Proc IMechE, Part G: J Aerospace Engineering2014; 228: 2055–2065.
22.
WangWGuoR. Influence of hypersonic inlet cowl lip on flowfield structure and thermal load. J Propul Power2015; 30: 1–8.
23.
MahapatraDJagadeeshG. Experimental investigation of cowl-lip shape and location on inlet characteristics at hypersonic Mach number. IEEE Trans Neural Netw Learn Syst2009; 26: 1493–1502.
24.
ZhangYTanHZhuangYet al.Influence of expansion waves on cowl shock/boundary layer interaction in hypersonic inlets. J Propul Power2014; 30: 1183–1191.
25.
LuHBYueLJChangXY. Flow characteristics of hypersonic inlets with different cowl-lip blunting methods. Sci China-Phys Mech Astron2014; 57: 741–752.
26.
BaoWZongY. Effects of strut swept angle on the drag of scramjet. Proc IMechE, Part G: J Aerospace Engineering2012; 226: 455–466.
27.
BaoWZongYChangJet al.Effect of structural factors on maximum aerodynamic heat flux of strut leading surface. Appl Therm Eng2014; 69: 188–198.
28.
ZhangCQinJYangQet al.Indirect measurement method of inner wall temperature of scramjet with a state observer. Acta Astronaut2015; 115: 330–337.
29.
Xiao FS. Research on flow characteristics of some typical hypersonic shock wave interactions. Doctor Thesis, University of Science and Technology of China, China, 2016.
30.
Duquesne N and Roquefort TAd. Numerical investigation of a three-dimensional turbulent shock/shock interaction. AIAA-98-0774, 1998.
