Exploratory Heat-transfer Measurements at Mach 10 on a 7.5 ̊total-angle Cone Downstream of a Region of Air and Helium Transpiration Cooling PDF Download
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Author: James C. Dunavant
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 36
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Book Description
Heat transfer measurements at Mach 10 on total angle cone downstream of air and helium transpiration cooling region.
Author: James C. Dunavant
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 36
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Book Description
Heat transfer measurements at Mach 10 on total angle cone downstream of air and helium transpiration cooling region.
Author: James C. Dunavant
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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Book Description
Author: James C. Dunavant
Publisher:
ISBN:
Category :
Languages : en
Pages : 30
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1250
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Book Description
Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 26
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Book Description
Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 42
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Book Description
Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Author: Jerome D. Julius
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 32
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Book Description
Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 50
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Book Description
Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 38
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Book Description
Author: Thomas E. Walton (Jr.)
Publisher:
ISBN:
Category :
Languages : en
Pages : 31
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Book Description
Transpiration-cooling parameters are presented for a turbulent boundary layer on a cone configuration with a total angle of 25° which was tested in both free flight and in an ethylene-heated high-temperature jet at a Mach number of 2.0. The flight-tested cone was flown to a maximum Mach number of 4.08 and the jet tests were conducted at stagnation temperatures ranging from 937° R to 1,850° R. In general, the experimental heat transfer was in good agreement with the theoretical values. Inclusion of the ratio of local stream temperature to wall temperature in the nondimensional flow rate parameter enabled good correlation of both sets of transpiration data. The measured pressure at the forward station coincided with the theoretical pressure over a sharp cone; however, the measured pressure increased with distance from the nose tip.
