SST Technology Follow-On Program - Phase I, Performance Evaluation of an SST Noise Suppressor Nozzle System. Volume 2. Unsuppressed Acceleration and Cruise Modes.
Abstract
A parametric test of internal performance for the NSC-119B nozzle system in the unsuppressed operating mode was conducted. Geometrically compatible ejectors were tested in subsonic, transonic, and supersonic flight regimes. Ejector area and spacing ratios, secondary/primary weight flow ratios, and the fairings over the suppressor tube stowage cavity were the primary variables. Static pressures were monitored inside each ejector allowing the calculation of an equivalent resultant force on the ejector flaps. The present stowage concept requires a relatively large spacing ratio. It was found that the ejector flap loads increase and the performance decreases with increasing spacing ratio. A fairing becomes increasingly important to performance as the nozzle pressure ratio increases. The configuration yielding the best performance when restricted to the NSC-119B spacing ratio requirements consists of an area ratio-1.7 ejector incorporating a simple four-point linkage system and a fairing over the stowage cavity. An actuator will be required to hold the ejector flaps in at all operating conditions. At all pressure ratios, the fairing reduced the flap loading. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 15, 1972
- Accession Number
- AD0900400
Entities
People
- D. B. Morden
Organizations
- Boeing