Abstract
Shock wave/boundary layer interaction (SWBLI) is a highly critical problem that occurs in aircraft in transonic or supersonic flow. This study performed CFD analysis of the supersonic ramp flow of freestream Mach number 2.79. To secure reliability of the CFD analysis, adaptive mesh refinement using a gradient p sensor was used. Through this, a grid of sufficient resolution was obtained for the region of shock wave, expansion wave, and flow separation. The prediction performance of 7 turbulence models that are widely used in engineering application were compared. The baseline k–ω two-equation model showed the best prediction performance, while the SST k–ω model, which is one of the most widely used two-equation models, and the 2 Reynolds stress models showed relatively poor prediction performance. In the SWBLI problem, the use of adaptive mesh refinement made it possible to secure sufficient grid resolution; meanwhile, comparison of the prediction performance of the various turbulence models confirmed that for the SWBLI problem, the generally used turbulence model was somewhat inappropriate.
Highlights
IntroductionShock wave/boundary layer interaction (SWBLI) occurs when a shock wave (oblique shock or normal shock) penetrates the boundary layer in transonic or supersonic flow, and is observed in various shapes, such as the outer shape of the aircraft, the engine inlet, and the fins of rockets
Shock wave/boundary layer interaction (SWBLI) occurs when a shock wave penetrates the boundary layer in transonic or supersonic flow, and is observed in various shapes, such as the outer shape of the aircraft, the engine inlet, and the fins of rockets
The number of grids increases in the order: (a) A1 < (b) base mesh < (c) A6; if the number of grids is small, it can be confirmed that the resolution of the grid near the shock wave or expansion wave is insufficient; and in the case of A6 with the largest number of grids, the discontinuity of the shock wave is best resolved
Summary
Shock wave/boundary layer interaction (SWBLI) occurs when a shock wave (oblique shock or normal shock) penetrates the boundary layer in transonic or supersonic flow, and is observed in various shapes, such as the outer shape of the aircraft, the engine inlet, and the fins of rockets. Supersonic ramp flow is a representative problem of SWBLI, and adverse pressure gradients are formed by the ramp shape, resulting in separation of the boundary layer. This again directly causes mutual interference with the shock wave; and here, accurate predictions of the pressure distribution, friction coefficient, and heat transfer coefficient on the wall are very important in engineering application. In this study, using ANSYS FLUENT, one of the most widely used commercial CFD software, we analyzed compression ramp flow, a representative problem of SWBLI, and analyzed the predictive capability of various turbulence models available in FLUENT
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
