摘要：Aerodynamic heating of spinning flight vehicles have critical military applications such as flight testing, location tracking, stealth, and thermal protection. Based on the numerical method which is verified to be effective in the wind tunnel tests, this article discusses the aerodynamic thermal characteristics of a spinning winged projectile. Firstly, a 6-DOF trajectory model is established to demonstrate the motional behaviors. Partial flight data in supersonic, transonic, and subsonic regimes are separately defined as the inflow conditions. After that, thermo-fluid characteristics are compared between spin and non-spin. When the spin angular velocity is considered, a striking swirling flow phenomenon in the flow field, which result in the streamlines near the tail wings interfere with each other. Meanwhile, the impacts of the shear flow, trailing vortex and turbulent fluctuation are conspicuous. Besides, demonstrating the asymmetry of the temperature due to the flow deflection on the windward and leeward sides of the tail wings. Aerodynamic thermal differences on the surface of the tail wings are remarkable, especially at the tip of the wings. Therefore, the effects of spinning process on aerodynamic heating of winged vehicles cannot be ignored, particularly in supersonic flow at high Mach number.
