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Aerodynamic Characteristics of Parachutes at Mach Numbers from 1.6 to 3A wind-tunnel investigation was conducted to determine the parameters affecting the aerodynamic performance of drogue parachutes in the Mach number range from 1.6 to 3. Flow studies of both rigid and flexible-parachute models were made by means of high-speed schlieren motion pictures and drag coefficients of the flexible-parachute models were measured at simulated altitudes from about 50,000 to 120,000 feet.
Document ID
20070030970
Acquisition Source
Langley Research Center
Document Type
Video
External Source(s)
http://lisar.larc.nasa.gov/MOVIES/LARGE/LV-2007-00019.mov
http://lisar.larc.nasa.gov/MOVIES/MEDIUM/LV-2007-00019.mov
Authors
Maynard, J. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 24, 2013
Publication Date
February 1, 1961
Subject Category
Aerodynamics
Report/Patent Number
L-598
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
[Tunnel] UPWT

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