The Influence Of Low Wall Temperature On Boundary Layer Transition And Local Heat Transfer On 2 Inch Diameter Hemispheres At A Mach Number Of 495 And A Reynolds Number Per Foot Of 732 X 106
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Author | : Morton Cooper |
Publisher | : |
Total Pages | : 42 |
Release | : 1960 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106 Book in PDF, Epub and Kindle
Author | : Morton Cooper |
Publisher | : |
Total Pages | : 0 |
Release | : 1960 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download The Influence of Low Wall Temperature on Boundary-layer Transition and Local Heat Transfer on 2-inch-diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 106 Book in PDF, Epub and Kindle
Author | : Morton Cooper |
Publisher | : |
Total Pages | : 50 |
Release | : 1960 |
Genre | : |
ISBN | : |
Download The Influence of Low Wall Temperature on Boundary-Layer Transition and Local Heat Transfer on 2-Inch-Diameter Hemispheres at a Mach Number of 4.95 and a Reynolds Number Per Foot of 73.2 X 10(exp 6) Book in PDF, Epub and Kindle
Author | : James R. Hall |
Publisher | : |
Total Pages | : 34 |
Release | : 1957 |
Genre | : Boundary layer |
ISBN | : |
Download Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 Book in PDF, Epub and Kindle
Author | : Leo T. Chauvin |
Publisher | : |
Total Pages | : 24 |
Release | : 1954 |
Genre | : Aerodynamics |
ISBN | : |
Download Experimental Convective Heat Transfer to a 4-inch and 6-inch Hemisphere at Mach Numbers from 1.62 to 3.04 Book in PDF, Epub and Kindle
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 | : Charles B. Rumsey |
Publisher | : |
Total Pages | : 42 |
Release | : 1956 |
Genre | : Aerodynamics |
ISBN | : |
Download Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 Book in PDF, Epub and Kindle
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 | : Howard S. Carter |
Publisher | : |
Total Pages | : 38 |
Release | : 1961 |
Genre | : Aerodynamic heating |
ISBN | : |
Download 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 Book in PDF, Epub and Kindle
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 | : Eugene Sevigny |
Publisher | : |
Total Pages | : 50 |
Release | : 1959 |
Genre | : Boundary layer |
ISBN | : |
Download The Effect of Centrifugal Forces on Boundary Layer Transition for a Highly Heated Body Book in PDF, Epub and Kindle
Author | : James J. Buglia |
Publisher | : |
Total Pages | : 0 |
Release | : 1961 |
Genre | : |
ISBN | : |
Download Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 106 Book in PDF, Epub and Kindle
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 | : Raul Jorge Conti |
Publisher | : |
Total Pages | : 32 |
Release | : 1959 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Download Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution Book in PDF, Epub and Kindle