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The calculation of steady non-linear transonic flow over finite wings with linear theory aerodynamics
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Cunningham Jr., A. M. |
| Copyright Year | 1976 |
| Description | The feasibility of calculating steady mean flow solutions for nonlinear transonic flow over finite wings with a linear theory aerodynamic computer program is studied. The methodology is based on independent solutions for upper and lower surface pressures that are coupled through the external flow fields. Two approaches for coupling the solutions are investigated which include the diaphragm and the edge singularity method. The final method is a combination of both where a line source along the wing leading edge is used to account for blunt nose airfoil effects; and the upper and lower surface flow fields are coupled through a diaphragm in the plane of the wing. An iterative solution is used to arrive at the nonuniform flow solution for both nonlifting and lifting cases. Final results for a swept tapered wing in subcritical flow show that the method converges in three iterations and gives excellent agreement with experiment at alpha = 0 deg and 2 deg. Recommendations are made for development of a procedure for routine application. |
| File Size | 1829893 |
| Page Count | 59 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760021106 |
| Archival Resource Key | ark:/13960/t4dn8xf9j |
| Language | English |
| Publisher Date | 1976-08-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Transonic Flow Wings Flow Distribution Pressure Distribution Linear Programming Airfoils Leading Edges Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
