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Comparisons of two-dimensional shock-expansion theory with experimental aerodynamic data for delta-planform wings at high supersonic speeds
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jernell, L. S. |
| Copyright Year | 1974 |
| Description | An investigation has been conducted to explore the potential for optimizing airfoil shape at high supersonic speeds by utilizing the two-dimensional shock-expansion method. Theoretical and experimental force and moment coefficients are compared for four delta-planform semispan wings having a leading-edge sweep angle of 65 deg and incorporating modified diamond airfoils with a thickness-chord ratio of 0.06. The wings differ only in airfoil maximum-thickness position and camber. The experimental data are obtained at Mach numbers of 3.95 and 4.63 and at a Reynolds number of 9.84 million per meter. A relatively simple method is developed for predicting, in terms of lift-drag ratio, the optimum modified diamond airfoil at high supersonic and hypersonic speeds. |
| File Size | 3103684 |
| Page Count | 38 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19740018331 |
| Archival Resource Key | ark:/13960/t6k11vd1n |
| Language | English |
| Publisher Date | 1974-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Shock Waves Supersonic Speed Low Aspect Ratio Wings Lift Drag Ratio Delta Wings Aerodynamic Coefficients Aerodynamic Characteristics Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
