高超声速圆锥边界层转捩数值研究

Numerical study on hypersonic boundary layer transition over a sharp cone

以类似于处理湍流脉动的方式来模型化非湍流脉动,考虑湍流的间歇性特征及引起超声速流动失稳机制,研究包括转捩起始位置及转捩区范围的高超声速流动转捩问题,发展可反映扰动模态和可压缩性影响的两方程SST转捩/湍流模式。针对尖锥模型,在马赫数6、攻角0°～2°时,采用第二模态(Second-mode)机制,预测并比较完全层流态、完全湍流态,以及自然转捩发展过程中的表面热流、表面摩阻等气动特性。

Treating non-turbulent fluctuations in a turbulence-like manner and considering the intermittency of turbulence and the mechanisms of supersonic flow instability, the hypersonic transition problems that include the transitional onset and transitional extent are studied. Two-equation transition/turbulent SST model,which including the influences of disturbed mode and compressible flow,is also developed. Appling the second-mode mechanism of transition, the aerodynamic characteristics that include skin friction and surface heat flux over a sharp cone under Mach number 6,angle of attack 0°～2° are calculated and compared at dif- ferent states which include laminar, turbulence and nature transition.