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Static stability characteristics of a series of hypersonic boost-glide configurations at mach numbers of 1.41 and 2.01
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1959 |
| Description | An investigation of the static stability characteristics of several hypersonic boost-glide configurations has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.41 and 2.01 (with Reynolds numbers per foot of 2.90 x 10(exp 6) and 2.41 x 10(exp 6) respectively). This series of configurations consisted of a cone, with and without cruciform fins, a trihedron, two low-aspect-ratio delta wings that differed primarily in cross-sectional shape, and two wing-body configurations. All configurations indicated reasonably linear pitching-, yawing-, and rolling-moment characteristics for angles of attack to at least 12 deg. The maximum lift-drag ratio for the zero-thrust condition (base drag included) was about 3 for the delta-wing configurations and about 4 for the wing-body configurations. |
| File Size | 8443709 |
| Page Count | 88 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980227875 |
| Archival Resource Key | ark:/13960/t1kh59r9b |
| Language | English |
| Publisher Date | 1959-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Stability And Control 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 |
