AERODYNAMIC SHAPE OPTIMIZATION OF TRANSONIC AIRFOIL AND WING USING RESPONSE SURFACE METHODOLOGY

摘要

A Response Surface Methodology (RSM) for Aerodynamic Shape Optimization (ASO) using the compressible Reynolds-Averaged Navier-Stokes (RANS) equations is implemented and tested. The quadratic polynomials which cancel the second-order cross items are employed to construct RS model. This approach improves on the efficiency of using the RSM for high-dimensional design optimization problems. By using present method the aerodynamic performance of the transonic airfoil and wing are greatly improved. Successful design results confirm validity and efficiency of the present design method.