CFD Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature
Bui, Trong T. (2009) CFD Analysis of Nozzle Jet Plume Effects on Sonic Boom Signature. Technical Report NASA/TM-2009-214650, Research and Engineering, NASA Dryden Flight Research Center.
Full text available as: |
Abstract
A computational fluid dynamics study is conducted to examine nozzle exhaust jet plume effects on the sonic boom signature of a supersonic aircraft. A simplified axisymmetric nozzle geometry, representative of the nozzle on the NASA Dryden NF-15B Lift and Nozzle Change Effects on Tail Shock research airplane, is considered. The computational fluid dynamics code is validated using available wind-tunnel sonic boom experimental data. The effects of grid size, spacial order of accuracy, grid type, and flow viscosity on the accuracy of the predicted sonic boom pressure signature are quantified. Grid lines parallel to the Mach wave direction are found to give the best results. Second-order accurate upwind methods are required as a minimum for accurate sonic boom simulations. The highly underexpanded nozzle flow is found to provide significantly more reduction in the tail shock strength in the sonic boom N-wave pressure signature than perfectly expanded and overexpanded nozzle flows. A tail shock train in the sonic boom signature is observed for the highly underexpanded nozzle flow. Axisymmetric computational fluid dynamics simulations show the flow physics inside the F-15 nozzle to be nonisentropic and complex.
| EPrint Type: | NASA Technical Memorandum |
|---|---|
| Keywords: | CFD, F-15B, LaNCETS, Nozzle, Sonic boom |
| Subjects: | (01 - 09) Aeronautics: (01) Aeronautics - General |
| ID Code: | 2042 |
| Deposited On: | 04 November 2009 |
| Additional Information: | 45 pages. Also presented as AIAA-2009-1054 at the 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, January 5-8, 2009. |
