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Effect of reynolds number on the subsonic boattail drag of several wing-body configurations
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reubush, D. E. |
| Copyright Year | 1976 |
| Description | An investigation was conducted in a transonic cryogenic tunnel to determine the effect of varying Reynolds number on the boattail drag of several wing-body configurations. This study was made at 0 deg angle of attack at Mach numbers from 0.6 to 0.9 for Reynolds numbers up to 67 x 1 million (based on distance from the nose to the start of the boattail). Results indicate that as the Reynolds number was increased the boattail static pressure coefficients in the expansion region of the boattail became more negative while those in the recompression region became more positive. Results show that there was only a small effect of Reynolds number of boattail pressure drag. |
| File Size | 3978343 |
| Page Count | 85 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19760019069 |
| Archival Resource Key | ark:/13960/t3dz51j5w |
| Language | English |
| Publisher Date | 1976-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Pressure Drag Subsonic Speed Body-wing Configurations Boattails Reynolds Number Wind Tunnel Tests Propulsion System Configurations 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 |
