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The Numerical Simulation of Trailing Edge Jet Effect on Shock Oscillation over Airfoil at Transonic Speed
Received date: 2012-05-21
Online published: 2025-05-24
The shock/separated boundary layer interaction on transonic airfoil may result in shock oscillation which in turn may lead to wing buffet. Shock oscillation over transonic airfoil might be controlled by modifying the flow in the shock/boundary layer interaction region and by manipulating the wake flow near airfoil trailing edge. The effects of trailing edge jet on the airfoil wake flow and on shock oscillations were simulated by numerical methods. The flow around an 18% thick biconvex airfoil with various jet velocities were computed, and the effects on shock oscillation and aerodynamic characteristics were analyzed. It is found that the trailing edge jet will suppress the shock oscillation and improve the aerodynamic characteristics of airfoil.
Key words： jet flow; shock oscillation; transonic; boundary layer separation
ZHOU Wei , ZHANG Zhengke , QU Ke , GAO Chao . The Numerical Simulation of Trailing Edge Jet Effect on Shock Oscillation over Airfoil at Transonic Speed[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013 , 33(1) : 135 -137,144 . DOI: 10.15892/j.cnki.djzdxb.2013.01.018
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