Abstract
Various approximations to unsteady aerodynamics are examined for the unsteady aerodynamic force of a pitching thin double wedge airfoil in hypersonic flow. Results of piston theory, Van Dyke’s second-order theory, Newtonian impact theory, and CFD method are compared in the same motion and Mach number effects. The results indicate that, for this thin double wedge airfoil, Newtonian impact theory is not suitable for these Mach number, while piston theory and Van Dyke’s second-order theory are in good agreement with CFD method for Ma<7.
Highlights
Hypersonic aeroelasticity is an active area of research in nowadays
This is an Open Access article published by World Scientific Publishing Company
1660177-1 aeroelastic analysis of flutter boundary showed there was large difference between that predicted by approximate unsteady aerodynamic theories
Summary
Hypersonic aeroelasticity is an active area of research in nowadays It is defined as the mutual interaction of inertial, elastic, and aerodynamic forces in a system, when there is feedback between deformation and flow. Because of the limited capabilities of computational and experimental facilities, researchers have relied upon a number of approximate unsteady aerodynamic theories[1,2,3] for the aeroelastic analysis of hypersonic vehicles. This is an Open Access article published by World Scientific Publishing Company. 1660177-1 aeroelastic analysis of flutter boundary showed there was large difference between that predicted by approximate unsteady aerodynamic theories. It noted that the piston theory results were generally unconservative with respect to the experimental flutter boundaries. Approximate Aerodynamic Models The approximate models considered in this paper are briefly described
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