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Wedge shock and nozzle exhaust plume interaction in a supersonic jet flow
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Zaman, Khairul Fagan, Amy Castner, Raymond Heath, Christopher |
| Copyright Year | 2014 |
| Description | Fundamental research for sonic boom reduction is needed to quantify the interaction of shock waves generated from the aircraft wing or tail surfaces with the nozzle exhaust plume. Aft body shock waves that interact with the exhaust plume contribute to the near-field pressure signature of a vehicle. The plume and shock interaction was studied using computational fluid dynamics and compared with experimental data from a coaxial convergent-divergent nozzle flow in an open jet facility. A simple diamond-shaped wedge was used to generate the shock in the outer flow to study its impact on the inner jet flow. Results show that the compression from the wedge deflects the nozzle plume and shocks form on the opposite plume boundary. The sonic boom pressure signature of the nozzle exhaust plume was modified by the presence of the wedge. Both the experimental results and computational predictions show changes in plume deflection. |
| File Size | 1841826 |
| Page Count | 19 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150006759 |
| Archival Resource Key | ark:/13960/t6c29wr50 |
| Language | English |
| Publisher Date | 2014-01-13 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Free Jets Supersonic Aircraft Exhaust Nozzles Computational Fluid Dynamics Jet Flow Deflection Exhaust Gases Shock Wave Interaction Convergent-divergent Nozzles Sonic Booms Pressure Measurement Plumes Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
