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Calculation of boundary layers near the stagnation point of an oscillating airfoil
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Cebeci, T. Carr, L. W. |
| Copyright Year | 1983 |
| Description | The results of an investigation of boundary layers close to the stagnation point of an oscillating airfoil are reported. Two procedures for generating initial conditions, the characteristics box scheme and a quasi-static approach, were investigated, and the quasi-static approach was shown to be appropriate provided the initial region was far from any flow separation. With initial conditions generated in this way, the unsteady boundary layer equations were solved for the flow in the leading edge region of a NACA 0012 airfoil oscillating from 0 to 5 deg. Results were obtained for both laminar and turbulent flow, and, in the latter case, the effect of transition was assessed by specifying its occurrence at different locations. The results demonstrate the validity of the numerical scheme and suggest that the procedures should be applied to calculation of the entire flow around oscillating airfoils. |
| File Size | 5960134 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830018877 |
| Archival Resource Key | ark:/13960/t2c874939 |
| Language | English |
| Publisher Date | 1983-05-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Boundary Layer Separation Statics Turbulence Stagnation Point Oscillations Airfoils Unsteady Flow Angle of Attack Boundary Layer Equations Boundary Layers Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
