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Supersonic and hypersonic aerodynamic characteristics of two shuttle-orbiter configurations designed for reduced length
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Stone, H. W. |
| Copyright Year | 1974 |
| Description | Performance, stability, and control tests at supersonic and hypersonic speeds have been performed on two versions of a shuttle orbiter configuration designed for reduced length. One of the test configurations had twin dorsal fins rolled out 15 deg the other a centerline single dorsal fin. Effects of elevon and body deg flap deflection, rudder flare, planform fillet, and aileron deflection were examined. The supersonic tests were over the Mach number range from 1.6 to 4.63 at a Reynolds number based on model length of 4,300,000. The hypersonic tests were conducted at a Mach number of 10.3 and Reynolds number of 670,000. |
| File Size | 1255156 |
| Page Count | 55 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740015281 |
| Archival Resource Key | ark:/13960/t8kd6p328 |
| Language | English |
| Publisher Date | 1974-04-01 |
| Access Restriction | Open |
| Subject Keyword | Space Vehicles Hypersonic Speed Supersonic Speed Deflection Wind Tunnel Tests Control Stability Aerodynamic Characteristics Space Shuttle Orbiters Dorsal Sections Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
