CFD Simulations of Steady Flows over the IAR 65°Delta Wing

摘要

Computational Fluid Dynamics(CFD)studies have been conducted to simulate vortical flows around the IAR 65°delta wing with a sharp leading edge.The effects of the centerbody on the aerodynamic characteristics of the wing are also investigated.Two flow solvers have been employed to compute steady inviscid flows over with and without centerbody configurations of the wing.These two solvers are an IAR in-house code,FJ3SOLV,and the CFD- FASTRAN commercial software.The computed flow solutions of the two solvers have been compared and correlated against the IAR wind tunnel data, including Pressure Sensitive Paint(PSP) measurements.The major features of the primary vortex have been well captured and overall reasonable accuracy was obtained.In accordance with the experimental observations for the flow conditions considered,the CFD computations revealed no major global effects of the centerbody on the surface pressure distributions of the wing and on the lift coefficient.However,CFD-FASTRAN seems to predict a vortex breakdown,which is neither predicted by FJ3SOLV nor observed in the wind tunnel for the flow conditions considered.