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Investigations of Compression Shocks and Boundary Layers in Gases Moving at High SpeedThe mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Document ID
20030063988
Acquisition Source
Langley Research Center
Document Type
Other - NACA Technical Memorandum
Authors
Ackeret, J. (Eidgenoessische Technische Hochschule Zurich, Switzerland)
Feldmann, F. (Eidgenoessische Technische Hochschule Zurich, Switzerland)
Rott, N. (Eidgenoessische Technische Hochschule Zurich, Switzerland)
Date Acquired
September 7, 2013
Publication Date
January 1, 1947
Publication Information
Publication: Mitteilungen aus dem Institut fuer Aerodynamik an der Eidgenoessischen Technischen Hochschule
Issue: 10
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1113
Report Number: NACA-TM-1113
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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