Development of a three-dimensional supersonic inlet flow analysis
Abstract
A method for computing three dimensional flow in supersonic inlets is described. An approximate set of governing equations is given for viscous flows which have a primary flow direction. The governing equations are written in general orthogonal coordinates. These equations are modified in the subsonic region of the flow to prevent the phenomenon of branching. Results are presented for the two sample cases: a Mach number equals 2.5 flow in a square duct, and a Mach number equals 3.0 flow in a research jet engine inlet. In the latter case the computed results are compared with the experimental data. A users' manual is included.
- Publication:
-
Final Report Scientific Research Associates
- Pub Date:
- January 1980
- Bibcode:
- 1980srai.reptQ....B
- Keywords:
-
- Computer Programs;
- Supersonic Inlets;
- Three Dimensional Flow;
- Viscous Flow;
- Branching (Physics);
- Flow Distribution;
- Navier-Stokes Equation;
- Partial Differential Equations;
- Supersonic Boundary Layers;
- Fluid Mechanics and Heat Transfer