Accession Number:

ADB004733

Title:

SST Technology Follow-On Program - Phase 2. Noise Suppressor/Nozzle Development. Volume 6. Performance Technology - Thrust and Flow Characteristics of a Reference Multitube Nozzle With Ejector

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:

57.0

Abstract:

Static tests are conducted to establish reference performance levels for a round convergent nozzle and a 3.3 area ratio, 37-tube suppressor nozzle. After assessing bare nozzle performance characteristics, ejector shrouds are added, and the effect of secondary inlet changes and ejector length change on thrust is established. Pressure measurements on nozzleejector surfaces are correlated with measured thrust. The secondary flow is measured, and the flow conditions inside the ejectors are established by performing pressure temperature traverses.

Subject Categories:

  • Transport Aircraft
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE