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Accession Number:
AD0900400
Title:
SST Technology Follow-On Program - Phase I, Performance Evaluation of an SST Noise Suppressor Nozzle System. Volume 2. Unsuppressed Acceleration and Cruise Modes.
Corporate Author:
BOEING COMMERCIAL AIRPLANE CO SEATTLE WA
Report Date:
1972-02-15
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, secondaryprimary 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
Descriptive Note:
Final rept. on task 4,
Supplementary Note:
See also AD-900 401L and Volume 1, AD-900 399L.
Pages:
0089
Contract Number:
DOT-FA-SS-71-12
File Size:
0.00MB
