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AERODYNAMIC HEATING SOLUTIONS FOR A TYPICAL MISSILE DETERMINED FROM THREE TURBULENT BOUNDARY LAYER THEORIES

Author
Burley, Jr, W. M.
Published
United States : [publisher not identified], 1957.
[Oak Ridge, Tennessee] : [U.S. Atomic Energy Commission], 1957.
Physical Description
microopaque : positive ; 8 x 13 cm

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Summary
Aerodynamic heating inputs and resulting skin temperatures for a missile with flight Mach numbers from 1.5 to 6.0 were computed on the REAC. The results, determined from three different boundary layer theories, are to be used as an aid in the design of a radiation facility to simulate aerodynamic heating inputs. The three theories yielded maximum skin temperatures as follows: Van Driest's cone theory, 1935 deg R, Van Driest's flat plate theory 1875 deg R, and an MIT theory, 1830 deg R. Van Driest's cone theory results are recommended for design values. (auth)
Report Numbers
SC-4138(TR)
Other Subject(s)
Collection
U.S. Atomic Energy Commission depository collection.
Note
DOE contract number: AT(29-1)-789
NSA number: NSA-12-006579
OSTI Identifier 4309452
Research organization: Sandia Corp., Albuquerque, N. Mex.
View MARC record | catkey: 42245610