Accession Number:

ADB004736

Title:

SST Technology Follow-On Program - Phase 2. Noise Suppressor/Nozzle Development. Volume 9. Performance Technology - Analysis of the Low Speed Performance of Multitube Suppressor/Ejector Nozzles (0-167 kn)

Descriptive Note:

Final rept. on Task III

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Personal Author(s):

Report Date:

1975-03-01

Pagination or Media Count:

144.0

Abstract:

The effects of geometric variables on the performance of multitube suppressorejector nozzles are described and quantified for static and low forward velocity cases. The bulk of the investigation concentrates on configurations compatible with supersonic transport engine exhaust systems. Experimental results are presented for 28 related, model-scale suppressor ejector configurations tested at nozzle pressure ratios from 2 to 4 over a range of velocities from 0 to 167 kn. High static performance and minimum lapse rate are shown to be compatible through the proper selection of suppressorejector geometry and the optimum ejector inlet area.

Subject Categories:

  • Transport Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE