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Flow field analysis of aircraft configurations using a numerical solution to the three-dimensional unified supersonic/hypersonic small disturbance equations, part 1
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Knight, C. J. Gunness Jr., R. C. Dsylva, E. |
| Copyright Year | 1972 |
| Description | The unified small disturbance equations are numerically solved using the well-known Lax-Wendroff finite difference technique. The method allows complete determination of the inviscid flow field and surface properties as long as the flow remains supersonic. Shock waves and other discontinuities are accounted for implicity in the numerical method. This technique was programed for general application to the three-dimensional case. The validity of the method is demonstrated by calculations on cones, axisymmetric bodies, lifting bodies, delta wings, and a conical wing/body combination. Part 1 contains the discussion of problem development and results of the study. Part 2 contains flow charts, subroutine descriptions, and a listing of the computer program. |
| File Size | 3540464 |
| Page Count | 117 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19720009557 |
| Archival Resource Key | ark:/13960/t3jx34j96 |
| Language | English |
| Publisher Date | 1972-02-01 |
| Access Restriction | Open |
| Subject Keyword | Fluid Mechanics Supersonic Flow Flow Equations Three Dimensional Flow Finite Difference Theory Steady Flow Flow Distribution Inviscid Flow Hypersonic Flow Aircraft Configurations 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 |
