Computational Study of Shock-Wave and Transitional Boundary-Layer Interactions in Supersonic and Hypersonic Flows
Shock-wave/boundary-layer interactions (SWBLIs) are very important in any high speed flight occurring on aircraft, space/launch vehicles and projectiles. These interactions are of special importance in supersonic/hypersonic flows, where aerodynamic heating is a major factor. The generation of shock waves by various surfaces of a vehicle or aircraft engine, as seen in Fig. 1, and the impingement of those shocks on other surfaces can greatly amplify the local heat transfer.
Figure 1. The flow structure of shock-wave/boundary-layer interactions (SWBLIs) with M> 1 inflow (M = Mach Number)
Research topic of SWBLIs has been carried out internationally, particularly in Europe and the United States. The proposed research provides an opportunity to carry out an investigation on a relatively simple geometric configuration but able to reveal complex, unanswered but very important questions on transitional supersonic/hypersonic SWBLIs. For the purpose of the fundamental research, a computational/numerical approach using CFD method was used and extremely beneficial for the proposed research. It is able to provide detailed information to assist the experimental design and to investigate the flow field regions and/or parameters that are beyond the reach of the experiments, and also to be used for validation purposes.
The computational results are compared with experimental results from NASA. SWBLI computations have been carried out in the present work that cover a wide range of flow conditions, but here only at M = 7.73 case is presented. The agreement with experimental data at M = 7.73 in Fig. 2a is relatively fair. In particular, the interaction appears to commence further upstream than noted experimentally and the wall heat-fluxes in the reattachment region in Fig. 3 are under-predicted by computations. These preliminary results have been presented at a national conference and will be presented in an international conference as well as in journals.
Figure 2. M = 7.73 at a wedge angle of 5o
Future work will be directed to further investigate the effect of the interactions if the incoming flow is laminar and then undergoes transition or the incoming flow is purely turbulent. These kinds of interactions have many applications in the design of future high speed vehicles or engines.
Principal Investigator: Dr. Romie Oktovianus Bura
Research Group: Flight Physics, Faculty of Mechanical and Aerospace Engineering
Funding Source: Fundamental Grant 2009 (Year 1), Department of National Education