Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration PDF Download
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Author: Charles B. Rumsey Publisher: ISBN: Category : Aerodynamic heating Languages : en Pages : 26
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 : Aerodynamic heating Languages : en Pages : 26
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: Langley Aeronautical Laboratory Publisher: Hassell Street Press ISBN: 9781015043015 Category : Languages : en Pages : 30
Book Description
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Author: Charles B. Rumsey Publisher: ISBN: Category : Aerodynamics Languages : en Pages : 42
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: Charles B. Rumsey
Author: Charles B. Rumsey
Author: Langley Aeronautical Laboratory
Author: Charles R. Rumsey
Author: Charles B. Rumsey
Author: Charles R. Rumsey
Author: Charles B. Rumsey
Author: Charles R. Rumsey
Author: Charles B. Rumsey
Author: Benjamine J. Garland
Author: Charles B. Rumsey