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Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 10 deg Cone in Free Flight at Supersonic Mach Numbers up to 5.9Measurements of aerodynamic heat transfer have been made at six stations on the 40-inch-long 10 deg. total-angle conical nose of a rocket- propelled model which was flight tested at Mach numbers up to 5.9. are presented for a range of local Mach number just outside the bound- ary layer on the cone from 1.57 to 5.50, and a range of local Reynolds number from 6.6 x 10(exp 6) to 55.2 x 10(exp 6) based on length from the nose tip.
Document ID
20040047150
Acquisition Source
Headquarters
Document Type
Other - NASA Technical Note (TN)
Authors
Rumsey, Charles B.
(NASA Langley Research Center Hampton, VA, United States)
Lee, Dorothy B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 21, 2013
Publication Date
May 1, 1961
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NASA-TN-D-745
L-1539
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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