Computational analysis of vented supersonic exhaust nozzles using a multiblock/multizone strategy
Abstract
NASA-Langley's PAB3D-v3 multiblock/multizone Navier Stokes code is presently used to study the behavior of the longitudinally-slotted nozzle configuration for fixed-geometry operation in supersonic cruise on the bases of high nozzle pressure ratios. The range of flow conditions encompassed nozzle pressure ratio values from 5 to 20, and freestream Mach numbers from 0 to 2.5. A large recirculation region was detected near the concave base of the nozzle, while smaller regions were located near and around the slots. In general, the discharge coefficient was predicted within 0.5 percent, and the thrust ratio within 1.5 percent, of measured values.
- Publication:
-
29th AIAA Aerospace Sciences Meeting
- Pub Date:
- January 1991
- Bibcode:
- 1991aiaa.meetU....A
- Keywords:
-
- Computational Fluid Dynamics;
- Exhaust Nozzles;
- Navier-Stokes Equation;
- Nozzle Geometry;
- Supersonic Nozzles;
- Computational Grids;
- Flow Characteristics;
- Mach Number;
- Reynolds Number;
- Three Dimensional Models;
- Fluid Mechanics and Heat Transfer