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Transonic airfoil analysis and design in nonuniform flow
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Chang, J. F. Lan, C. E. |
| Copyright Year | 1986 |
| Description | A nonuniform transonic airfoil code is developed for applications in analysis, inverse design and direct optimization involving an airfoil immersed in propfan slipstream. Problems concerning the numerical stability, convergence, divergence and solution oscillations are discussed. The code is validated by comparing with some known results in incompressible flow. A parametric investigation indicates that the airfoil lift-drag ratio can be increased by decreasing the thickness ratio. A better performance can be achieved if the airfoil is located below the slipstream center. Airfoil characteristics designed by the inverse method and a direct optimization are compared. The airfoil designed with the method of direct optimization exhibits better characteristics and achieves a gain of 22 percent in lift-drag ratio with a reduction of 4 percent in thickness. |
| File Size | 1619988 |
| Page Count | 85 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860015857 |
| Archival Resource Key | ark:/13960/t17m55b97 |
| Language | English |
| Publisher Date | 1986-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Incompressible Flow Transonic Flow Numerical Analysis Divergence Propeller Fans Lift Drag Ratio Slipstreams Airfoils Optimization Computer Programs Convergence Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
