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Heat-Transfer Tests of 20-Millimeter Projectiles at a Mach Number of 5 with an Analysis by Unsteady Scaling Laws to Predict Component Temperature Rises after Firing for Various Free-Flight ConditionsThe temperature time history of various components of a 20-millimeter projectile was obtained by transient heating tests in a Mach number 5 blowdown tunnel. An unsteady scaling law is derived and used to predict the temperature time histories after firing in flight at various Mach numbers and altitudes.
Document ID
20040006303
Acquisition Source
Langley Research Center
Document Type
Other - NASA Technical Note (TN)
Authors
Trimpi, Robert L.
(NASA Langley Research Center Hampton, VA, United States)
Gallagher, James G.
(NASA Langley Research Center Hampton, VA, United States)
Jones, Robert A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
May 1, 1961
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-758
L-1323
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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