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Experiments on high speed ejectors
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Wu, J. J. |
| Copyright Year | 1986 |
| Description | Experimental studies were conducted to investigate the flow and the performance of thrust augmenting ejectors for flight Mach numbers in the range of 0.5 to 0.8, primary air stagnation pressures up to 107 psig (738 kPa), and primary air stagnation temperatures up to 1250 F (677 C). The experiment verified the existence of the second solution ejector flow, where the flow after complete mixing is supersonic. Thrust augmentation in excess of 1.2 was demonstrated for both hot and cold primary jets. The experimental ejector performed better than the corresponding theoretical optimal first solution ejector, where the mixed flow is subsonic. Further studies are required to realize the full potential of the second solution ejector. The research program was started by the Flight Dynamics Research Corporation (FDRC) to investigate the characteristic of a high speed ejector which augments thrust of a jet at high flight speeds. |
| File Size | 3405318 |
| Page Count | 85 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860020348 |
| Archival Resource Key | ark:/13960/t9673bf52 |
| Language | English |
| Publisher Date | 1986-07-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Propulsion And Power Supersonic Flow Stagnation Pressure Multiphase Flow Subsonic Flow Ejectors Thrust Augmentation Air Breathing Engines Mach Number Research Management Jet Propulsion 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 |
