INTERACTIVE BOUNDARY-LAYER METHOD FOR UNSTEADY AIRFOIL FLOWS - QUASI-STEADY MODEL

被引：5

作者：

CEBECI, T

JANG, HM

机构：

[1] University of Michigan, Ann Arbor, MI

[2] Douglas Aircraft Company, Long Beach, CA

[3] Mechanical Engineering Department, Long Beach, CA

来源：

JOURNAL OF AIRCRAFT | 1990年 / 27卷 / 08期

关键词：

D O I：

10.2514/3.25340

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

An interactive boundary-layer method previously developed and tested for steady flows is used here in a quasisteady manner to examine the evolution of the flow behavior of airfoils subject to harmonic oscillation and ramp-type motions. The calculations encompass the airfoil and wake flows at angles of attack that lead to separation. The results quantify the effects of the viscous boundary layer and wake on the variation of lift coefficient with angle of attack and reduced frequency. These effects are shown to be large at angles of attack that involve boundary-layer separation. © 1990 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

引用

页码：673 / 678

页数：6

共 19 条

[11]

Teng N.G., The Development of a Computer Code for the Numerical Solution of Unsteady Inviscid, and Incompressible Flow over an Airfoil, (1987)

[12]

Hess J.L., Smith A.M.O., Calculation of Potential Flow About Arbitrary Bodies, Progress in Aeronautical Sciences: Guidance and Control, 8, pp. 1-138, (1966)

[13]

Basu B.C., Hancock G.J., The Unsteady Motion of Two-Dimensional Airfoil in Incompressible Inviscid Flow, 87, 1, pp. 159-178, (1978)

[14]

Veldman A.E.P., New Quasi-Simultaneous Method to Calculate Interacting Boundary Layers, 19, 1, pp. 79-85, (1981)

[15]

Leballeur J.C., Couplage Visqueux-Non Visqueux: Methode Numerique Et Applications Aux Ecoulements Bidimensionnels Transsonique Set Supersoniques, pp. 65-76, (1978)

[16]

Carter J.E., A New Boundary-Layer Inviscid Iteraction Technique for Separated Flow, pp. 75-1450, (1979)

[17]

Michel R., Etude De La Transition Sur Les Profiles D'aile

[18]

Estab-Lissement D'un Critere De Determination De Point De Transition Et Calcul De La Trainee De Profile Incompressible, (1951)

[19]

Lorber P.F., Carta F.O., Airfoil Dynamic Stall at Constant Pitch Rate and High Reynolds Number, 25, 6, pp. 548-556, (1988)

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