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Comparison of computational and experimental results for a supercritical airfoil
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wahls, Richard A. Rivers, Melissa B. |
| Copyright Year | 1994 |
| Description | A computational investigation was performed to study the flow over a supercritical airfoil model. Solutions were obtained for steady-state transonic flow conditions using a thin-layer Navier-Stokes flow solver. The results from this computational study were compared with time-averaged experimental data obtained over a wide Reynolds number range at transonic speeds in the Langley 0.3-Meter Transonic Cryogenic Tunnel. Comparisons were made at a nominal Mach number of 0.72 and at Reynolds numbers ranging from 6 x 10(exp 6) to 35 x 10(exp 6). |
| File Size | 1282278 |
| Page Count | 34 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19950010493 |
| Archival Resource Key | ark:/13960/t2k69df3b |
| Language | English |
| Publisher Date | 1994-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Navier-stokes Equation Transonic Flow Supercritical Airfoils Reynolds Number Transonic Wind Tunnels Cryogenics Pressure Distribution Wind Tunnel Models Angle of Attack Steady State 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 |
