Numerical simulation of flow over delta wing with trailing‐edge jet at high angle of attack

Abstract

SUMMARYThe incompressible Reynolds-averaged Navier-Stokes equations, together with a modified mixing length algebraic turbulence model, are solved to simulate the flow over a delta wing with trailing-edge jets at high angles of attack. An artificial compressibility method and a Beam-Warming implicit approximate factorization scheme are employed to discretize the equations. The computed results indicate that trailing-edge jets tend to not only decrease the pressure but also increase the velocity at the cores of the streamwise primary vortices. This moves the vortex breakdown locations aft and stabilizes the vortical flow. As a result, the jets lead to a decreased pressure on the upper wing surface and an increased pressure on the lower wing surface, thereby increasing the overall lift. Computations further show that as the exit area of the trailing-edge jets is enlarged, or, as the jets are deflected downward, the above-mentioned effects become more pronounced.