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Laminarization of a boundary layer in a supersonic nozzle by cooling of the surfaceThe concept of cooling of the surface of wind tunnel walls in order to laminarize the boundary layer, and thereby eliminate perturbations in the working area, is discussed. Equations are given, which are used to calculate the temperature conditions under which the flow in the boundary layer will be stably laminar.
Document ID
19840006051
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Maksimov, V. P. (NASA Headquarters Washington, DC United States)
Maslov, A. A. (NASA Headquarters Washington, DC United States)
Date Acquired
September 4, 2013
Publication Date
August 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:77341
NASA-TM-77341
Report Number: NAS 1.15:77341
Report Number: NASA-TM-77341
Accession Number
84N14119
Funding Number(s)
CONTRACT_GRANT: NASW-3541
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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