Computational Study of Boundary Layer Control for Improving Airfoil Performance
A Computational method was developed for investigating boundary layer control. Solutions of the Reynolds-averaged Navier-Stokes equations were obtained using the two-equation K- E turbulence model which includes the low-Reynolds-number effect in the near-wall region. Stream function and vorticity together with the turbulent kinetic energy and its dissipation rate were calculated for the flowfield in a body-fitted coordinate system. By increasing the amount of suction on the upper surface, flow separation could be totally eliminated. Transition from laminar to turbulent flow was delayed. Aerodynamic performance was substantially improved.
C. Chen and S. C. Lee, "Computational Study of Boundary Layer Control for Improving Airfoil Performance," SAE Technical Papers, Society of Automotive Engineers, Jan 1993.
The definitive version is available at https://doi.org/10.4271/932513
Aerospace Technology Conference and Exposition
Mechanical and Aerospace Engineering
Keywords and Phrases
Mathematical Analysis; Aerodynamics
Article - Conference proceedings
© 1993 Society of Automotive Engineers, All rights reserved.