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Study of boundary-layer transition using transonic-cone preston tube data
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Moretti, P. M. Reed, T. D. |
| Copyright Year | 1980 |
| Description | The laminar boundary layer on a 10 degree cone in a transonic wind tunnel was studied. The inviscid flow and boundary layer development were simulated by computer programs. The effects of pitch and yaw angles on the boundary layer were examined. Preston-tube data, taken on the boundary-layer-transition cone in the NASA Ames 11 ft transonic wind tunnel, were used to develope a correlation which relates the measurements to theoretical values of laminar skin friction. The recommended correlation is based on a compressible form of the classical law-of-the-wall. The computer codes successfully simulates the laminar boundary layer for near-zero pitch and yaw angles. However, in cases of significant pitch and/or yaw angles, the flow is three dimensional and the boundary layer computer code used here cannot provide a satisfactory model. The skin-friction correlation is thought to be valid for body geometries other than cones. |
| File Size | 1804860 |
| Page Count | 98 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800019804 |
| Archival Resource Key | ark:/13960/t6j14vn23 |
| Language | English |
| Publisher Date | 1980-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Transonic Flow Speed Indicators Laminar Boundary Layer Cones Skin Friction Transonic Wind Tunnels Inviscid Flow Boundary Layer Transition Computerized Simulation Pitot Tubes Heat Transfer Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
