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Effect of leading-edge load constraints on the design and performance of supersonic wings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Darden, C. M. |
| Copyright Year | 1985 |
| Description | A theoretical and experimental investigation was conducted to assess the effect of leading-edge load constraints on supersonic wing design and performance. In the effort to delay flow separation and the formation of leading-edge vortices, two constrained, linear-theory optimization approaches were used to limit the loadings on the leading edge of a variable-sweep planform design. Experimental force and moment tests were made on two constrained camber wings, a flat uncambered wing, and an optimum design with no constraints. Results indicate that vortex strength and separation regions were mildest on the severely and moderately constrained wings. |
| File Size | 40719203 |
| Page Count | 79 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850021611 |
| Archival Resource Key | ark:/13960/t2v45m70z |
| Language | English |
| Publisher Date | 1985-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Boundary Layer Separation Supersonic Flow Supersonic Airfoils Aerodynamic Configurations Swept Wings Wind Tunnels Vortices Wind Tunnel Tests Aerodynamic Forces Leading Edges Optimization Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
