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High reynolds number analysis of an axisymmetric afterbody with flow separation
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reubush, David E. Carlson, John R. |
| Copyright Year | 1996 |
| Description | The ability of a three-dimensional Navier-Stokes method, PAB3D, to predict nozzle afterbody flow at high Reynolds number was assessed. Predicted surface pressure coefficient distributions and integrated afterbody drag are compared with experimental data obtained from the NASA-Langley 0.3 m Transonic Cryogenic Tunnel. Predicted afterbody surface pressures matched experimental data fairly closely. The change in the pressure coefficient distribution with Reynolds number was slightly over-predicted. Integrated afterbody drag was typically high compared to the experimental data. The change in afterbody pressure drag with Reynolds number was fairly small. The predicted point of flow separation on the nozzle was slightly downstream of that observed from oilflow data at low Reynolds numbers and had a very slight Reynolds number dependence, moving slightly further downstream as Reynolds number increased. |
| File Size | 836516 |
| Page Count | 16 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19960028556 |
| Archival Resource Key | ark:/13960/t8sb9147k |
| Language | English |
| Publisher Date | 1996-06-20 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Boundary Layer Separation High Reynolds Number Navier-stokes Equation Pressure Drag Aerodynamic Drag Nozzle Flow Transonic Wind Tunnels Afterbodies Cryogenics Pressure Ratio Separated Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
