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Application of supersonic linear theory and hypersonic impact methods to three nonslender hypersonic airplane concepts at mach numbers from 1.10 to 2.86
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Pittman, J. L. |
| Copyright Year | 1979 |
| Description | Aerodynamic predictions from supersonic linear theory and hypersonic impact theory were compared with experimental data for three hypersonic research airplane concepts over a Mach number range from 1.10 to 2.86. The linear theory gave good lift prediction and fair to good pitching-moment prediction over the Mach number (M) range. The tangent-cone theory predictions were good for lift and fair to good for pitching moment for M more than or equal to 2.0. The combined tangent-cone theory predictions were good for lift and fair to good for pitching moment for M more than or equal to 2.0. The combined tangent-cone/tangent-wedge method gave the least accurate prediction of lift and pitching moment. The zero-lift drag was overestimated, especially for M less than 2.0. The linear theory drag prediction was generally poor, with areas of good agreement only for M less than or equal to 1.2. For M more than or equal to 2.), the tangent-cone method predicted the zero-lift drag most accurately. |
| File Size | 4200539 |
| Page Count | 60 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19800003815 |
| Archival Resource Key | ark:/13960/t9770927v |
| Language | English |
| Publisher Date | 1979-12-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Hypersonics Supersonics Supersonic Aircraft Skin Friction Wave Drag Zero Lift Angle of Attack Aerodynamic Characteristics Prediction Analysis Techniques 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 |
