Numerical Computation And Research On Aerodynamic Heating Over Aircraft Of Ball-cone Shape At Supersonic Flow

Based on the Prandtl boundary layer theory, the theory formulas and numerical heat transfer approach coupled are adopted to simulate the aerodynamic heating over 0° angle of attack aircraft of ball-cone shape, and the value of the surface heating flux and temperature distribution inside the aircraft are obtained, as well as the aerodynamic heating environment of the aircraft, which can provide some valuable theoretical reference for the shape designing and aerodynamic thermal designing、thermal protection of supersonic aircraft to some extent.On one hand, the conical supersonic flow field is solved to determine the shock shape and the shock wave angle formed under the aircraft’s surface of the ball-cone shape at supersonic flight conditions, then the flow parameters are calculated through the relationship between front and behind of shock waves, and the flow parameters under the boundary layer outer edge of the aircraft surface are determined by the modified formulas of the secondary shock-expansion waves method coupled with Newton theory, then the heat flux equations over laminar boundary layer of the aircraft’s surface at0° angle of attack and supersonic flight conditions are obtained via Blasius’ formula, similarity and analcgic method, Eckert reference enthalpy method and characterization of high temperature gas etc; On the other hand the aircraft model of ball-cone shape created and mesh generated is introduced into the program as researching object, and the aerodynamic heating flux formulas are introduced into the program as boundary conditions, then the finite volume method is used to discrete governing equations (group), and aerodynamic heating environment of the supersonic aircraft is got after calculating finally.The main contents of this article are:aerodynamic heating situations over plane model and three-dimensional model about the aircraft of ball-cone shape are simulated under supersonic flight conditions, which show that the aerodynamic heating environment generated by 3D model is more severe than the plane model at the same supersonic flight conditions, and with the calculation of the Mach number increases, this harsh thermal environment has become more and more serious; secondly three aircraft models on different half cone angle of ball-cone shape are selected to simulate at the same conditions, whose results show when increasing its half-cone angle, within reasonable limits, can reduce the temperature of high temperature region of the aircraft modle, namely to improve the harsh thermal environment of the aircraft of ball-cone shape under supersonic flight conditions; finally the aerodynamic heating environment over aircraft model of ball-cone shape is simulated considering the heatting transfer between internal environment and the inner surface of the cavity, and the result displays it can improve the harsh aerodynamic thermal environment if the heatting transfer between internal environment and the inner surface of the cavity is considered under the high flight conditions.