Numerical Simulation of Aerodynamic Pressure and Aerodynamic Heat on Stagnation Point and Wall of Hypersonic Double Cone Aircraft

The aerodynamic pressure and aerodynamic heat characteristics of hypersonic aircraft are important research directions in the development of aircraft technology. The double cone is a typical aerodynamic configuration of the aircraft. To study the heating and compression law of the double cone aircraft under hypersonic conditions, the numerical model of the double cone aircraft under hypersonic conditions is established based on the finite element analysis method. The aerodynamic pressure and aerodynamic heat of the stagnation point and wall of the aircraft at different Mach numbers are analyzed. The numerical simulation results are compared with the theoretical solutions. The results show that the numerical simulation error of the stagnation point temperature is not more than 0.24% and the numerical simulation error of the stagnation point pressure is not more than 0.33%. The stagnation point and wall temperature of the double-cone aircraft increase monotonically with the Mach number. The stagnation point pressure and wall pressure increase monotonically with the Mach number. The relationship between the wall temperatures of the double cone aircraft is tail temperature > head temperature > front cone temperature > back cone temperature. The relationship between wall pressures of the double cone aircraft is head pressure > back cone pressure > front cone pressure > tail pressure.