Measured and theoretical supersonic dynamic stability characteristics of a National Aero-Space Plane configuration

Abstract

Wind-tunnel tests of a National Aero-Space Plane configuration were conducted in the NASA Langley Unitary Plan Wind Tunnel (UPWT). The model used is a Langley designed blended body configuration. Dynamic stability characteristics were measured on this configuration at Mach numbers of 2.0, 2.5, 3.5, and 4.5. In addition to tests of the baseline configuration, component breakdown tests were conducted. The test results show that the baseline configuration generally has stable damping about all three axes, with only isolated exceptions. In addition, there was generally good agreement between the in-phase dynamic parameters and the corresponding static data which were measured during another series of tests in UPWT. Also included are comparisons of the experimental damping parameters with results from the engineering predictive code aerodynamic preliminary analysis system. These comparisons show good agreement at low angles of attack; however, the comparisons are generally not as good at the higher angles of attack.