等离子体气动激励减小翼型跨音速阻力的数值模拟

等离子体气动激励能够显著提升飞行器／动力装置的气动性能。本文进行了等离子体气动激励减小RAE2822翼型跨音速阻力的数值模拟。将电弧放电等离子体激励简化为对流场的热能注入,建立了基于唯象学的数值计算模型,以实验测试结果作为输入条件,将热能以源项的形式加入N-S方程求解,研究了不同来流速度、激励强度以及激励位置下等离子体气动激励对翼型阻力特性的影响。仿真结果表明:等离子体气动激励可以有效减小RAE2822翼型跨音速阻力,来流速度与等离子体气动激励减阻效果有较大关系,当WTBX]Ma=0.81时,减阻达到13.58％;激励强度对减阻效果影响较小,当WWTBZ]=3 000 K时,减阻达到11.77％;增大激励位置,减阻效果增大,但幅度变小,当WTBX]DWTBZ]=20 mm时,减阻达到13.17％。

Numerical Simulation of Plasma Aerodynamic Actuation for Airfoil Transonic Drag Reduction

Plasma flow control has potential applications in shock wave control for improving aircraft/thruster performance obviously. Numerical simulation of plasma aerodynamic actuation reducing transonic drag of RAE2822 airfoil was presented. Based on phenomenological modeling viewpoint, the discharge plasma aerodynamic actuation was simplified as thermal energy injection into flow, which was initialized from experimental data and added in the flow N-S equation as thermal source term. The effect of plasma aerodynamic actuation on the airfoil drag characteristic was investigated under different conditions. The results show that plasma aerodynamic actuation can reduce airfoil transonic drag availability. The drag reduction depended on the freestream parameters, which was 13.58% at Ma=0.81. The drag reduction responded to source term temperature rarely, which was 11.77% at W=3 000 K. The drag reduction responded to the distance between the location of plasma actuation and shock wave, which was 13.17% at D=20 mm.