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Limitations of the method of characteristics when applied to axisymmetric hypersonic nozzle designA design study of axisymmetric hypersonic wind tunnel nozzles was initiated by NASA Langley Research Center with the objective of improving the flow quality of their ground test facilities. Nozzles for Mach 6 air, Mach 13.5 nitrogen, and Mach 17 nitrogen were designed using the Method of Characteristics/Boundary Layer (MOC/BL) approach and were analyzed with a Navier-Stokes solver. Results of the analysis agreed well with design for the Mach 6 case, but revealed oblique shock waves of increasing strength originating from near the inflection point of the Mach 13.5 and Mach 17 nozzles. The findings indicate that the MOC/BL design method has a fundamental limitation that occurs at some Mach number between 6 an 13.5. In order to define the limitation more exactly and attempt to discover the cause, a parametric study of hypersonic ideal air nozzles designed with the current MOC/BL method was done. Results of this study indicate that, while stagnations conditions have a moderate affect on the upper limit of the method, the method fails at Mach numbers above 8.0.
Document ID
19900032677
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Edwards, Anne C.
(NASA Langley Research Center Hampton, VA, United States)
Perkins, John N.
(North Carolina State University Raleigh, United States)
Benton, James R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 90-0192
Accession Number
90A19732
Funding Number(s)
CONTRACT_GRANT: NCC1-109
Distribution Limits
Public
Copyright
Other

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