Three-Dimensional Mixing Flow Field in Supersonic Flow Induced by Injected Secondary Flow through a Traverse Circular Nozzle
Shock wave/turbulent boundary layer interaction regions induced by gaseous secondary flows injected into supersonic flows through circular nozzles have been experimentally and computationally investigated.
In the experiments the flowfields are visualized by the Schlieren method, oil flow technique, surface pressure; spatial total pressure distributions are measured in the whole interaction region. The total pressure ratio, P c /Po, (P c - total pressure of injected secondary flow, P0: total pressure of freestream) are varied and the changes of the flowfleld are investigated for circular injection. The detailed flow structures in three-dimensional mixing flow structures have been revealed. Especially, the surface oil patterns show a quite complicated flow in the interacting region with primary and secondary separations. Also, quite interesting Pitot pressure fields are revealed. The same flowflelds have been simulated by solving Navier-Stokes equations with turbulent modelling. Surface pressure and spatial Pitot pressure distributions show quite good agreement with experiments. The results suggest that the numerical code is quite useful for supersonic mixing flows.
Key wordsMixing flow SCRAM -jet engine Shock-boundary layer interaction
Unable to display preview. Download preview PDF.
- Anderson GY (1987) An outlook on hypersonic flight. AIAA Paper 87–2074Google Scholar
- Aso S, Okuyama S, Kawai M, Ando Y (1991a) Experimental study on mixing phenomena in supersonic flows with slot injection. AIAA Paper 91–0016Google Scholar
- Aso S, Okuyama S, Ando Y (1991b) Experimental study on interacting secondary flow through a slot nozzle into supersonic flow. The Memoirs of the Faculty of Engineering, Kyushu University, 51, 1: 53–62Google Scholar
- Baldwin BS, Lomax H (1978) Thin layer approximation and algebraic model for separated turbulent flows. AIAA Paper 78–0257Google Scholar
- Clark SW, Chan SC (1992) Numerical investigation of a transverse jet for supersonic aerodynamic control. AIAA Paper 92–0639Google Scholar
- King PS, Thomas RH, Schetz J A (1989) Combined tangential-normal injection into a supersonic flow. AIAA Paper 89–0622Google Scholar
- Rhie CM, Syed SA (1990) Critical evaluation of three-dimensional supersonic combustor calculations. AIAA Paper 90–0207Google Scholar
- Rizzetta DP (1992) Numerical simulation of slot injection into a turbulent supersonic stream. AIAA Paper 92–0827Google Scholar
- Thompson DS (1989) Numerical solution of a two-dimensional jet in a supersonic crossflow using an upwind relaxation scheme. AIAA Paper 89–1869Google Scholar
- Yee HC (1987) Upwind and symmetric Shock-Capturing Schemes. NASA-TM-89464Google Scholar
- Young CT, Barfield BF (1972) Viscous interaction of sonic transverse jets with supersonic external flows. AIAA J. 10Google Scholar