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Aerodynamic characteristics of a slender cone-cylinder body of revolution at a mach number of 3.85
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1951 |
| Description | An experimental investigation of the aerodynamics of a slender cone-cylinder body of revolution was conducted at a Mach number of 3.85 for angles of attack of 0 degree to 10 degrees and a Reynolds number of 3.85x10(exp 6). Boundary-layer measurements at zero angle of attack are compared with the compressible-flow formulations for predicting laminar boundary-layer characteristics. Comparison of experimental pressure and force values with theoretical values showed relatively good agreement for small angles of attack. The measured mean skin-friction coefficients agreed well with theoretical values obtained for laminar flow over cones. |
| File Size | 11154898 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19930086899 |
| Archival Resource Key | ark:/13960/t1zd28b2d |
| Language | English |
| Publisher Date | 1951-11-05 |
| Access Restriction | Open |
| Subject Keyword | Flow, Laminar Bodies Loads, Aerodynamic Flow, Supersonic 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 |