Effect of Inertia Level on Aerodynamic Derivatives of a wedge in Hypersonic Flow

Abstract

In this paper a 2-dimensional slender bodies in hypersonic flow at high angle of attack with different Mach number has been implemented. By utilizing the concept of a piston moving in a cylinder at any speed, relations for stability derivatives are obtained for a wedge, which depends on the flight Mach number and semi vertex angle of the wedge. Stiffness derivatives decreases linearly with the increase in the Mach number for h = 0, 0.2, 0.4 but for Mach number 10 and above the steady state is achieved and stability derivative becomes independent of Mach number. For pivot positions h = 0.6, 0.8, and 1.0 unlike for h = 0 to 0.4 the stability derivative increases up to Mach 10 and again it becomes independent of Mach number. The variation of the damping derivatives is unaltered for all the values of the pivot positions. The damping derivative decreases marginally and then it becomes independent of Mach number. Viscous effects, secondary wave reflections are neglected in the present study. In the present study the real gas effects and leading edge bluntness have not been taken into considerations.