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Prediction of airfoil stall using navier-stokes equations in streamline coordinates
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Choi, D. H. Oh, C. S. Sohn, C. H. |
| Copyright Year | 1992 |
| Description | A Navier-Stokes procedure to calculate the flow about an airfoil at incidence was developed. The parabolized equations are solved in the streamline coordinates generated for an arbitrary airfoil shape using conformal mapping. A modified k-epsilon turbulence model is applied in the entire domain, but the eddy viscosity in the laminar region is suppressed artificially to simulate the region correctly. The procedure was applied to airfoils at various angles of attack, and the results are quite satisfactory for both laminar and turbulent flows. It is shown that the present choice of the coordinate system reduces the error due to numerical diffusion, and that the lift is accurately predicted for a wide range of incidence. |
| File Size | 626039 |
| Page Count | 10 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930018267 |
| Archival Resource Key | ark:/13960/t1ck39t2x |
| Language | English |
| Publisher Date | 1992-01-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Navier-stokes Equation Turbulent Flow Conformal Mapping Coordinates K-epsilon Turbulence Model Airfoils Shapes Angle of Attack Eddy Viscosity Aerodynamic Stalling Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
