Experimental and computational investigation for two-dimensional characteristics of flat plate wings

Abstract

Wind tunnel tests for three types of flat plate wings for missiles are conducted at Mach numbers of 0.5, 0.8 and 2.0. Prior to the tests, verification of the TwoDimensional performance of Mitsubishi Electric trisonic wind tunnel is made using a conventional wing model NACA0012. At the same time, in order to confirm the applicability of 2-D Navier-Stokes code to flat plate wings, computations are made and compared with the experiments. The aerodynamic performances, C1 ( section lift coefficient) and Cdp (section pressure drag coefficient ), differ among the different types of the wings except for C1 at supersonic region. It is observed the peculiar characteristics to the corresponding speed region. Also, the computational results prove effectiveness of numerical simulation to flat plate wings. However, there is a little difficulty in a separated flow. On the other hand, there has been a rapid progress in the computational aerodynamics using the codes for the Navier-Stokes equations of various methods. Some of these codes are now in the phase of practical use. 'LANSPD' code developed by S. Obayashi, S. Fujii and K. Kuwahara is one of them. This code solves twodimensional compressible Navier-Stokes equations using LU-AD1 factorization algorithm and has proved its capability of practical c omputation of normal streamlined airfoils. In order to evaluate effectiveness of this code on flat plate wings, 'LANSSD' is applied to one type of the flat plate wing and the results are compared to the experimental data.