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An experimental documentation of a separated trailing-edge flow at a transonic mach number
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Brown, J. L. Viswanath, P. R. |
| Copyright Year | 1982 |
| Description | A detailed experiment on the separated flow field at a sharp trailing edge is described and documented. The separated flow is a result of sustained adverse pressure gradients. The experiment was conducted using an elongated airfoil-like model at a transonic Mach number and at a high Reynolds number of practical interest. Measurements made include surface pressures and detailed mean and turbulence flow quantities in the region just upstream of separation to downstream into the near-wake, following wake closure. The data obtained are presented mostly in tabular form. These data are of sufficient quality and detail to be useful as a test case for evaluating turbulence models and calculation methods. |
| File Size | 3277203 |
| Page Count | 58 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19830005122 |
| Archival Resource Key | ark:/13960/t6741m31n |
| Language | English |
| Publisher Date | 1982-11-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer Thickness Transonic Flow Turbulent Flow Laser Doppler Velocimeters Turbulence Models Reynolds Number Flow Distribution Trailing Edges Wakes Mach Number Boundary Layer Flow Pressure Gradients Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
