Abstract This article presents a rapid and accurate aeroheating calculation method for hypersonic vehicles. The main innovation is combining accurate of numerical method with efficient of engineering method, which makes aeroheating simulation more precise and faster. Based on the Prandtl boundary layer theory, the entire flow field is divided into inviscid and viscid flow at the outer edge of the boundary layer. The parameters at the outer edge of the boundary layer are numerically calculated from assuming inviscid flow. The thermodynamic parameters of constant-volume specific heat, constant-pressure specific heat and the specific heat ratio are calculated, the streamlines on the vehicle surface are derived and the heat flux is then obtained. The results of the double cone show that at the 0° and 10° angle of attack, the method of aeroheating calculation based on inviscid outer edge of boundary layer parameters reproduces the experimental data better than the engineering method. Also the proposed simulation results of the flight vehicle reproduce the viscid numerical results well. Hence, this method provides a promising way to overcome the high cost of numerical calculation and improves the precision.
Highlights The inviscid numerical simulation for parameters at the outer edge boundary layer. The temperature-dependent gas model and streamlines on vehicle surface deduction. The aeroheating engineering simulation based on outer edge boundary layer parameters.
A hypersonic aeroheating calculation method based on inviscid outer edge of boundary layer parameters
Acta Astronautica ; 129 ; 429-437
2016-08-08
9 pages
Article (Journal)
Electronic Resource
English
Aeroheating Predictions for X-34 Using an Inviscid-Boundary Layer Method
British Library Conference Proceedings | 1998
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