Experiments on High Speed Ejectors
Abstract
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. Keywords: Thrust augmentation; Jet mixing flow; Supersonic flow; Subsonic flight; Transonic flight.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1986
- Accession Number
- ADA201445
Entities
People
- J. J. Wu