Computational Study of Boundary Layer Control for Improving Airfoil Performance

Abstract

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.

Meeting Name

Aerospace Technology Conference and Exposition

Department(s)

Mechanical and Aerospace Engineering

Keywords and Phrases

Mathematical Analysis; Aerodynamics

Document Type

Article - Conference proceedings

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 1993 Society of Automotive Engineers, All rights reserved.

Publication Date

01 Jan 1993

Link to Full Text

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