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Investigation of the flow field surrounding circular-arc boattail nozzles at subsonic speedsThe effects of jet exhaust on the subsonic flow field surrounding boattail nozzles with attached and separated boundary layers were investigated. Measurements of local Mach numbers and flow angles were made at free-stream Mach numbers of 0.60 and 0.80 at an angle of attack of 0 deg. Jet exhaust flow was simulated with a solid cylindrical sting and with high pressure air at jet-nozzle total pressure ratios of 2.9 and 5.0. Results show strong effects of the jet-wave structure on the external flow field. The predicted local Mach numbers and flow angles for attached-flow nozzles with solid jet simulators obtained by using subsonic inviscid/viscous-flow theory are in good agreement with experimental data. Prediction of nozzle surface pressure distributions which include jet-entrainment effects also agree with experimental data for attached-flow nozzles with high pressure air jets.
Document ID
19800013775
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Abeyounis, W. K. (NASA Langley Research Center Hampton, VA, United States)
Putnam, L. E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
L-13318
NASA-TP-1633
Accession Number
80N22262
Funding Number(s)
PROJECT: RTOP 505-32-13-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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