Interactive-boundary-layer method developed for computations of steady flow, extended under assumption of quasi-steady flow, to computations of evolution of two-dimensional flow about oscillating airfoil under light-dynamic-stall conditions. Represents advance toward ability to compute unsteady flows at even greater angles of attack with solutions of equations normally used for description of boundary-layer flows on airfoils prior to stall. Important in practical studies of flow on blades of helicopter rotors, axial compressors, and turbines.
Interactive-Boundary-Layer Computations For Oscillating Airfoil
NASA Tech Briefs ; 17 , 2
1993-02-01
Sonstige
Keine Angabe
Englisch
Computations of unsteady separating flows over an oscillating airfoil
Tema Archiv | 1997
|Computations of Unsteady Separating Flows over an Oscillating Airfoil (TN)
Online Contents | 1997
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