Application of a Method to Estimate Heating for Three-Dimensional Hypersonic Aeroshells

摘要

In the early stages of aeroshell shape design it is important to strike the appropriate balance between analysis fidelity and computational effort. Since the prediction of aerodynamic heating in axisymmetric flows is significantly faster than three-dimensional flows, it is desirable to employ an axisymmetric analogue method. The current work couples an equivalent axisymmetric body technique with different axisymmetric heating approaches to approximate three-dimensional heating. Multiple levels of fidelity are investigated in order to gauge the computational effort as a function of analysis fidelity. The three levels of fidelity include: 1) a Newtonian inviscid solution coupled with an axisymmetric integral boundary layer approach, 2) an Euler solution coupled with an axisymmetric integral boundary layer approach, and 3) a Navier-Stokes solution applied to each equivalent axisymmetric body. Heating analyses are presented for two sphere-cones in perfect air and a cylinder in thermochemical nonequilibrium. Results are also presented for a 15° sphere-cone at an angle of attack in perfect air and for an elliptic paraboloid in chemically reacting air. Solutions are compared with high fidelity computational and experimental data.