Experimental and theoretical study of swept-wing boundary-layer instabilities. Three-dimensional Tollmien-Schlichting instability

Extensive combined experimental and theoretical investigations of the linear evolution of three-dimensional (3D) Tollmien-Schlichting (TS) instability modes of 3D boundary layers developing on a swept airfoil section have been carried out. The flow under consideration is the boundary layer over an a...

Full description

Saved in:
Bibliographic Details
Published inPhysics of fluids (1994) Vol. 31; no. 11
Main Authors Borodulin, V. I., Ivanov, A. V., Kachanov, Y. S., Mischenko, D. A., Örlü, R., Hanifi, A., Hein, S.
Format Journal Article
LanguageEnglish
Published Melville American Institute of Physics 01.11.2019
Subjects
Angle of attack
Boundary layers
Fluid dynamics
Mathematical analysis
Physics
Stability
Swept wings
Online AccessGet full text

Cover

More Information
Summary:Extensive combined experimental and theoretical investigations of the linear evolution of three-dimensional (3D) Tollmien-Schlichting (TS) instability modes of 3D boundary layers developing on a swept airfoil section have been carried out. The flow under consideration is the boundary layer over an airfoil at 35° sweep and an angle of attack of +1.5°. At these conditions, TS instability is found to be the predominant one. Perturbations with different frequencies and spanwise wavenumbers are generated in a controlled way using a row of elastic membranes. All experimental results are deeply processed and compared with results of calculations based on theoretical approaches. Very good quantitative agreement of all measured and calculated stability characteristics of swept-wing boundary layers is achieved.
ISSN:1070-6631
1089-7666
1089-7666
DOI:10.1063/1.5125812