NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Performance of a 2D-CD nonaxisymmetric exhaust nozzle on a turbojet engine at altitudeBaseline thrust and cooling data obtained with a 2D-CD versatile research exhaust nozzle mounted on a turbojet engine in an altitude chamber are presented. The tests covered a range of nozzle pressure ratios, nozzle pressure ratios, nozzle throat areas, and internal expansion area ratios. The thrust data obtained show good agreement with theory and scale model results after correcting the data for leakage and bypass cooling flows. Additional work is needed to improve predictability of cooling performance.
Document ID
19820018365
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Straight, D. M. (NASA Lewis Research Center Cleveland, OH, United States)
Cullom, R. R. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
E-1257
NAS 1.15:82881
NASA-TM-82881
Report Number: E-1257
Report Number: NAS 1.15:82881
Report Number: NASA-TM-82881
Accession Number
82N26241
Funding Number(s)
PROJECT: RTOP 505-43-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available