The numerical study of cone-derived waverider with nonuniform blunt radius

Paper number

IAC-11,C2,7,19,x9929

Author

Dr. Jian-xia LIU, National University of Defense Technology, China

Year

2011

Abstract

Due to the high lift-to-drag ratio and appropriate plot ratio, cone-derived waverider has been considered as the basic configuration for hypersonic long-range vehicles. Most studies focused on the generation mechanics and impact factors of cone-derived waverider for the last several decades, but some scientific and technological challenges remain nowadays, especially the severe aero-heating problem caused by sharp leading edges.
For practical usage, the sharp leading edge needs to be blunted. The key problem is how to balance between aerodynamic performance and the design of temperature protection system. Usually, the sharp leading edge is blunted with a uniform radius to deal with the heat limitation. But this method would decrease the aerodynamic performance severely. In this paper, the concept of "nonuniform blunting" is proposed to deal with this confliction. Nonuniform blunting means that the blunt radius is varied with the position along the leading edge. The blunt radius at the nose region is bigger than the other regions because of the local higher heat flux.
This proposed paper will contain the following sections. At first, the physical model for the hypersonic flow over cone-derived waverider would be set up. Then the CFD method including the spatial scheme and grid effects would be validated in comparison with an experiment data. The performance of the cone-derived waverider with uniform and nonuniform blunt radius would be studied and compared in the end.

Abstract document

IAC-11,C2,7,19,x9929.brief.pdf

Manuscript document

IAC-11,C2,7,19,x9929.pdf (🔒 authorized access only).

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