Characteristic analysis of unstart performance for hypersonic side-wall inlet model

Nanjing Hangkong Hangtian Daxue Xuebao/Journal of Nanjing University of Aeronautics and Astronautics

Volumn 36, Issue 6, 2004, Pages 683-687

  Yuan, Hua Cheng ^a   Liang, De Wang ^a  

^a NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS   (China)

Author keywords

Hypersonic side wall inlet; Numerical simulation; Unstart

Indexed keywords

COMPUTER SIMULATION; FLOW PATTERNS; PRESSURE DISTRIBUTION; SHOCK WAVES; THREE DIMENSIONAL; WALLS (STRUCTURAL PARTITIONS);

HYPERSONIC SIDE-WALL INLET; SHOCK ANGLE; SHOCK STRUCTURE; UNSTART;

AIRCRAFT PARTS AND EQUIPMENT;

EID: 12744278756     PISSN: 10052615     EISSN: None     Source Type: Journal    
DOI: None     Document Type: Article

References (9)

1. Emami S, Trexler A, Auslender H, et al. Experimental investigation of inlet-combustor isolators for a dual-mode scramjet at a Mach number of 4[R]. NASA-TP-3502.
2. Holland D. Wind-tunnel blockage and actuation systems test of a two-dimensional scramjet inlet unstart model at Mach 6[R]. NASA-TM-109152.
3. Van Wie D M, Kwok F T, Walsh R F. Starting characteristics of supersonic inlets[R]. AIAA-96-2914, 1996.
4. Holland D. Schlieren photographs and internal pressure distributions for three-dimensional sidewall-compression scramjet inlets at a Mach number of 6 in CF4[R]. NASA TM-4479.
5. Holland D. Internal aerodynamics of a generic three-dimensional scramjet inlet at Mach 10[R]. NASA TP-3476.
6. Holland D. Experimental investigation of generic three-dimensional sidewall-compression scramjet inlets at Mach 6 in tetrafluoromethane [R]. NASA TM-4497.
7. Kussoy M I, Horstman K C, Horstman C C. Hypersonic crossing shock-wave/turbulent-boundary-layer interactions[J]. AIAA Journal 1993, 31(12): 2197-2203.