NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Performance of high area ratio nozzles for a small rocket thrusterTheoretical estimates of supersonic nozzle performance have been compared to experimental test data for nozzles with an area ratio of 100:1 conical and 300:1 optimum contour, and 300:1 nozzles cut off at 200:1 and 100:1. These tests were done on a Hughes Aircraft Company 5 lbf monopropellant hydrazine thruster with chamber pressures ranging from 25 to 135 psia. The analytic method used is the conventional inviscid method of characteristic with correction for laminar boundary layer displacement and drag. Replacing the 100:1 conical nozzle with the 300:1 contoured nozzle resulted in an improvement in thrust performance of 0.74 percent at chamber pressure of 25 psia to 2.14 percent at chamber pressure of 135 psia. The data is significant because it is experimental verification that conventional nozzle design techniques are applicable even where the boundary layer is laminar and displaces as much as 35 percent of the flow at the nozzle exit plane.
Document ID
19860057984
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kushida, R. O.
(Hughes Aircraft Co. El Segundo, CA, United States)
Hermel, J.
(Hughes Aircraft Co. El Segundo, CA, United States)
Apfel, S.
(Hughes Aircraft Co. El Segundo, CA, United States)
Zydowicz, M.
(California Institute of Technology, Jet Propulsion Laboratory, Pasadena; Hughes Aircraft Co. El Segundo, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1986
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 86-1573
Accession Number
86A42722
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available