Free-flight Investigation of Heat Transfer to an Unswept Cylinder Subjected to an Incident Shock and Flow Interference from an Upstream Body at Mach Numbers Up to 5.50 PDF Download
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Author: Howard S. Carter
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 38
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Book Description
Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 106 to 1.87 x 106. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
Author: Howard S. Carter
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 38
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Book Description
Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 106 to 1.87 x 106. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
Author: Howard S. Carter
Publisher:
ISBN:
Category :
Languages : en
Pages : 34
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Author: James R. Hall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 38
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Author: Dennis M. Bushnell
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 60
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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: James Larry Hunt
Publisher:
ISBN:
Category : Angle of attack (Aerodynamics)
Languages : en
Pages : 50
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Author: Charles R. Rumsey
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 66
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Author: ROBERT L. O'NEAL
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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A flight investigation of a rocket-powered model was conducted to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Heat-transfer data were obtained on leading edges of 3/4-inch diameter at sweep angles of 0 and 75 degrees, Mach numbers from 1.90 to 3.07, and Reynolds numbers based on leading-edge diameter from 8.05 to 11.80 times 10 to the 5th power. The measured heating rates of both the 0 and 75 degrees swept leading edges were of the magnitude predicted by turbulent theory rather than by laminar theory. It is believed that the high level of heating observed on the leading edges was due to the influence of conditions existing in the turbulent boundary layer of the body. Comparison of the average measured heating on the cylindrical portions of both the swept and unswept leading edges indicates that the heating of the unswept segment was generally about twice that of the swept segment. (Author).
Author: Clyde W. Winters
Publisher:
ISBN:
Category : Ablative materials
Languages : en
Pages : 40
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Book Description
