Computational Study of Boundary Layer Control for Improving Airfoil Performance 932513
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-∈ 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.
Citation: Chen, C. and Lee, S., "Computational Study of Boundary Layer Control for Improving Airfoil Performance," SAE Technical Paper 932513, 1993, https://doi.org/10.4271/932513. Download Citation
Author(s):
Chang-Ren Chen, Shen C. Lee
Affiliated:
University of Missouri-Rolla
Pages: 10
Event:
Aerospace Technology Conference and Exposition
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Turbulence
Wind tunnel tests
Aerodynamics
Wings
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