Experimental and computational investigation of delta wing aerodynamics

The aerodynamic behavior of delta wing has been investigated both computationally and experimentally. Force measurement experiment has been performed on a 70 degree sweep delta wing model with sharp leading and trailing edges in wind tunnel for a range of angle of attack. A steady-state RANS investigation has been performed using the commercial CFD code ANSYS FLUENT-14. Different visualizations offered by the post-processing software ANSYS CFD-POST 14 has been used in order to observe the main primary vortex core which is providing the main suction peak on the upper surface of the wing. Results of lift and drag coefficients at different angles of attack from experiments and computations have been compared. The experimental and numerical results are in good agreement with each other.