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Aerodynamics of slender bodies at mach number of 3.12 and reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) v : aerodynamic load distributions for a series of four boattailed bodies
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1954 |
| Description | Pressure distributions for a series of four boattailed bodies of revolution were obtained and compared with theory for a Mach number of 3.12, a Reynolds number range of 2 x 10 to 6th power to 14 x 10 to the 6th power, and angles of attack from zero to 9 degrees. Second-order theory adequately predicted the pressure distribution for regions free of the effects of cross-flow separation. |
| File Size | 11184444 |
| Page Count | 22 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930088175 |
| Archival Resource Key | ark:/13960/t3mw6tm3w |
| Language | English |
| Publisher Date | 1954-05-06 |
| Access Restriction | Open |
| Subject Keyword | Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |