Loading...
Please wait, while we are loading the content...
Similar Documents
Unsteady pressure and structural response measurements of an elastic supercritical wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Eckstrom, Clinton V. Sandford, Maynard C. Seidel, David A. |
| Copyright Year | 1988 |
| Description | Results are presented which define unsteady flow conditions associated with high dynamic response experienced on a high aspect ratio elastic supercritical wing at transonic test conditions while being tested in the NASA Langley Transonic Dynamics Tunnel. The supercritical wing, designed for a cruise Mach number of 0.80, experienced the high dynamic response in the Mach number range from 0.90 to 0.94 with the maximum response occurring at a Mach number of approximately 0.92. At the maximum wing response condition the forcing function appears to be the oscillatory chordwise movement of strong shocks located on both the wing upper and lower surfaces in conjunction with the flow separating and reattaching in the trailing edge region. |
| File Size | 1249622 |
| Page Count | 13 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880014372 |
| Archival Resource Key | ark:/13960/t24b7zt6x |
| Language | English |
| Publisher Date | 1988-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Dynamic Structural Analysis Transonic Wind Tunnels Unsteady Aerodynamics Wind Tunnel Tests Surface Properties Supercritical Wings Pressure Measurement Aeroelasticity Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
