AERODYNAMIC HEATING SOLUTIONS FOR A TYPICAL MISSILE DETERMINED FROM THREE TURBULENT BOUNDARY LAYER THEORIES
Technical Report
·
OSTI ID:4309452
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)
- Research Organization:
- Sandia Corp., Albuquerque, N. Mex.
- DOE Contract Number:
- AT(29-1)-789
- NSA Number:
- NSA-12-006579
- OSTI ID:
- 4309452
- Report Number(s):
- SC-4138(TR)
- Country of Publication:
- United States
- Language:
- English
Similar Records
DEVELOPMENT OF AN EXPLICIT EQUATION FOR TURBULENT SKIN-FRICTION COEFFICIENT FROM VAN DRIEST'S THEORIES FOR FLAT PLATE AND CONE
Turbulent compressible boundary layer with heat-transfer effects on conditions at the sublayer
Aerodynamics of missiles with slotted fin configurations
Technical Report
·
Fri Aug 30 00:00:00 EDT 1957
·
OSTI ID:4309206
Turbulent compressible boundary layer with heat-transfer effects on conditions at the sublayer
Journal Article
·
Sun Jul 01 00:00:00 EDT 1979
· AIAA J.; (United States)
·
OSTI ID:5452700
Aerodynamics of missiles with slotted fin configurations
Conference
·
Mon Dec 31 23:00:00 EST 1990
·
OSTI ID:6111355