Numerical study of aeroheating predictions for hypersonic reentry bodies
Kang Honglin1, Yan Chao1, Li Tinghe1, Guo Dilong2*
1. School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
2. Institute of Mechanics, Chinese Academy of Sciences, Beijing 100080, China
Abstract��
In order to calculate the heating rates on hypersonic blunt bodies quickly and effectively, two engineering methods were developed based upon the axisymmetric analogue which required tracking the inviscid surface streamlines. Engineering predictions in the boundary layer were used in both methods. However, method No.1 used engineering predictions out of the boundary layer, and in method No.2 the boundary-layer edge conditions were determined by the CFD method solved by Euler equations of three dimensions. Results of the two methods are in good agreement with the existing experimental data, which validates the correctness of the methods in calculating the heating rates on hypersonic vehicles. Results of these two engineering methods were also compared with those of CFD method solved by N-S equations, which indicates that the engineering methods save much calculating time and also have precision on predicting the heating rates on windward.
Kang Honglin, Yan Chao, Li Tinghe, Guo Dilong.Numerical study of aeroheating predictions for hypersonic reentry bodies[J] JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2006,V32(12): 1395-1398
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2006, Vol. 32 
