6DoF Aerodynamic Measurements of an Air-Breathing Hypersonic Vehicle

Abstract

Aerodynamic stability is very important for high-speed aircraft configurations, where reaction times to disturbances can become quite short. Six-degree-of freedom measurements have been performed with a wind tunnel model of an air-breathing hypersonic vehicle. Mach numbers ranged between Mach 3.5 and Mach 8, utilizing two different wind tunnels. The angle of attack was varied between α = -3° and α = 3°, and the sideslip angle between β = 0° and β = 2°. Further on, the modular design of the model allowed for examining the influence of control surface deflections by canards, rudders and ailerons. Additional numerical calculations have been performed for certain test points. The tests gave insight into the aerodynamic properties of the configuration and helped to determine flight conditions with critical or unstable longitudinal and lateral stability, respectively. Further on, the influence on the aerodynamics of the vehicles that is caused by changes in the flow state at the engine intake was shown.