부산대학교 도서관

This study was focused on the profile drag estimation from the wake survey of the now field with the wind tunnel testing. The experimental investigation was conducted with the low turbulence wind tunnel to estimate the profile drag coefficient of the supersonic biplane from the pressure loss in the wake of the model. The surveys were conducted behind the supersonic biplane model whose airfoil could realize the shock wave cancellation at design Mach number 1.7. The two-dimensional CFD simulations were also conducted to compare with the experimental results. The reduction of the test data by Jones equation gave the profile drag coefficients agreed with those obtained from the CFD simulations at zero lift conditions. However, at lifting conditions. the experimental results and the CFD results didn't agree. In this study, the profile drag characteristics of the supersonic biplane were discussed based on these results.