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Formulas pertinent to the calculation of flow-field effects at supersonic speeds due to wing thickness
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1959 |
| Description | Expressions based on linearized supersonic-flow theory are derived for the perturbation velocity potential in space due to wing thickness for rectangular wings with biconvex airfoil sections and for arrow, delta, and quadrilateral wings with wedge-type airfoil sections. The complete range of supersonic speeds is considered subject to a minor aspect-ratio-Mach number restriction for the rectangular plan form and to the condition that the trailing edge is supersonic for the sweptback wings. The formulas presented can be utilized in determining the induced-flow characteristics at any point in the field and are readily adaptable for either numerical computation or analytical determination of any velocity components desired. |
| File Size | 642509 |
| Page Count | 26 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19980228306 |
| Archival Resource Key | ark:/13960/t0cv97h39 |
| Language | English |
| Publisher Date | 1959-05-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics And Heat Transfer 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 |
