The control of supercriticalairfoil boundary layer separation is adapted using micro-vortex generators.
超临界翼型附面层分离控制适合采用微型涡流发生器。
2
The paper investigates the problem on vortex generator control boundary layer's separation of supercriticalairfoil and wing for body configuration wing.
本文研究涡流发生器控制超临界翼型和翼身组合体机翼的附面层分离问题。
3
Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions.