Numerical investigation on the drag and heat flux reduction of a supersonic reentry capsule with a counter-flow jet

作者：Zhou Chao Ying^*; Ji Wen Ying; Xie Peng

来源：Information Technology Journal, 2012, 11(12): 1705-1713.

DOI：10.3923/itj.2012.1705.1713

• Axisymmetric
• Blunt bodies
• Engineering applications
• Flow modes
• Flux reduction
• Flux vector splitting
• K-E turbulence model
• Maximum drag reductions
• Mixing flow field
• Numerical investigations
• Penetration mode
• Re-entry capsules
• Stagnation points
• Total pressure ratio

The mixing flow field around a reentry capsule with a counter-flow jet from its front stagnation point in supersonic flow is numerically studied by solving the axisymmetric Navier-Stokes equation coupled with k-e turbulence model using the Van Leer's flux vector splitting spatial discretion scheme. With the jet Mach number and total temperature fixed, the effects of jet total-pressure ratio on the flow structure, drag and heat flux on the body are investigated. The results show that two classical flow modes exist in the mixing flow field, one is long penetration mode and the other is short penetration mode. The drag on the blunt body is reduced significantly because of counter-flow jet. Considering the exhaustion of jet thrust, the effect of drag reduction is better when flow is in LPM than in SPM. It is found that the maximum drag reduction can reach as high as 55.8% for the cases studied. Blunt body heat flux can also be reduced significantly and can even be negative when jet total pressure ratio is high enough. The results may have some significance for the engineering application of supersonic blunt body counter-flow jet technology.

• 出版日期2012