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Calculation of three-dimensional, inviscid supersonic, steady flows
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Moretti, G. |
| Copyright Year | 1982 |
| Description | A numerical technique is described for the calculation of three dimensional, inviscid, supersonic, steady flows over wing-body configurations. A high degree of accuracy without increasing the number of computational nodes is obtained by means of a powerful conformal mapping technique. Results are presented for some simple body configurations and for a more complex arrow wing airframe. The numerical results show good agreement with experimental measurements. |
| File Size | 5699641 |
| Page Count | 123 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820020370 |
| Archival Resource Key | ark:/13960/t5r835m3g |
| Language | English |
| Publisher Date | 1982-06-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Supersonic Flow Body-wing Configurations Computational Fluid Dynamics Steady Flow Coordinates Shock Wave Interaction Elliptical Cylinders Equations of Motion Rankine-hugoniot Relation Circular Cones Arrow Wings Cambered Wings Three Dimensional Flow Conformal Mapping Inviscid Flow Fuselages Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |