低雷诺数翼型和跨声速翼型边界层计算

CALCULATION OF BOUNDARY-LAYER FLOWS ON LOW REYNOLDS NUMBER AND TRANSONIC AIRFOILS

本文利用边界层动量积分方程和平均流动能积分方程兼容计算了翼面的层流和湍流边界层流动。文中采用一种e^9型转捩判别公式预测翼面存在层流分离气泡情况的转捩位置。并引入对剪应力系数C_r的滞后方程以体现湍流中雷诺应力的历程效应。为避免在翼面流动分离时边界层方程的奇异,采用反解法计算。算例表明,计算与测量结果吻合良好。

In this paper, the laminar and turbulent boundary-layer flows on the transonic and low Reynolds number airfoils is calculated by using a compressible momentum and meanflow kinetic energy inverse integral boundary-layer equation method. A transition prediction formulation of the e9 type is employed to evaluate the location of transition with laminar separation bubbles and an extra lag equation is included in the turbulent formulation to account for lags in the response of the tarbulent stresses. Good agreement with experiment is obtained.