Measurements of Heat Transfer and Boundary-layer Transition on an 8-inch-diameter Hemisphere-cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88 PDF Download
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Author: Benjamine J. Garland
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: Benjamine J. Garland
Publisher:
ISBN:
Category :
Languages : en
Pages : 32
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Author: James R. Hall
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ISBN:
Category : Boundary layer
Languages : en
Pages : 34
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Author: James R. Hall
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: James R. Hall
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Category :
Languages : en
Pages :
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Author: Charles B. Rumsey
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 42
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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: Morton Cooper
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 42
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Author: Leo T. Chauvin
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ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
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Abstract: Equilibrium temperatures and heat-transfer coefficients for a hemispherical nose have been measured for Mach numbers from 1.62 to 3.04. Heat transfer to the surface of the hemisphere was presented as Stanton number against Reynolds number for various surface heating conditions. Heat transfer at the stagnation point has been measured and correlated with theory. Transition from a laminar to a turbulent boundary layer was obtained at Reynolds numbers of approximately 1 x 106 corresponding to a region on the body located between 45© and 60© from the stagnation point.
Author: John O. Reller
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 64
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Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.
Author: James J. Buglia
Publisher:
ISBN:
Category : Laminar flow
Languages : en
Pages : 26
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A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 106 based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer. The measured Stanton numbers were in good agreement with theory. Transition Reynolds numbers based on the laminar boundary-layer momentum thickness at transition ranged from 2,190 to 794. Comparison with results from previous tests of blunt shapes having a surface roughness of 20 to 40 microinches showed that the high degree of polish was instrumental in delaying the transition from laminar to turbulent flow.
Author: Paige B. Burbank
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 30
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