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Experimental Investigation Of The Heat Transfer Rate To A Series Of 20 Degree Cones Of Various Surface Finishes At A Mach Number Of 495
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Book Synopsis Experimental Investigation of the Heat-transfer Rate to a Series of 20 Degree Cones of Various Surface Finishes at a Mach Number of 4.95 by : Jim J. Jones
Download or read book Experimental Investigation of the Heat-transfer Rate to a Series of 20 Degree Cones of Various Surface Finishes at a Mach Number of 4.95 written by Jim J. Jones and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Heat-transfer Rate to Series of 20° Cones of Various Surface Finishes at Mach Number of 4.95 [with List of References] by :
Download or read book Experimental Investigation of Heat-transfer Rate to Series of 20° Cones of Various Surface Finishes at Mach Number of 4.95 [with List of References] written by and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 by : Jerome D. Julius
Download or read book Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 written by Jerome D. Julius and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Laminar Heat Transfer to Cones at Hypersonic Speeds by : Carl T. Berry
Download or read book An Experimental Investigation of Laminar Heat Transfer to Cones at Hypersonic Speeds written by Carl T. Berry and published by . This book was released on 1972 with total page 99 pages. Available in PDF, EPUB and Kindle. Book excerpt: The present study was an experimental investigation of the laminar surface heat transfer distribution about cones. The study was conducted in the Princeton University hypersonic nitrogen facility and covered a wide range of geometries and test conditions in an attempt to evaluate the numerical accuracy, theoretical modeling, and range of applicability of the several theories which are available. Cones, varying from 3 degrees to 30 degrees, with two nose bluntnesses, and lengths from one to eight inches were examined over a range of test conditions: Mach numbers from 16 to 25, and unit Reynolds numbers from 7,000 to 40,000 per inch. The detailed heat transfer distributions, covering the full range of 'nose dominated', 'merged', and 'weak interaction' regimes, were compared with several theoretical prediction techniques. A critical review of the modeling involved in the theories, as compared to the experiments, is presented. (Author).
Book Synopsis Comparisons of Experimental and Theoretical Heat Transfer to a Yawed Sphere-cone Model at Supersonic Speeds by : Lionel Pasiuk
Download or read book Comparisons of Experimental and Theoretical Heat Transfer to a Yawed Sphere-cone Model at Supersonic Speeds written by Lionel Pasiuk and published by . This book was released on 1964 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt: Theoretical laminar heat transfer rates to a sphere-cone model at angles of yaw up to 18 degrees are compared with wind tunnel data measured at Mach numbers of 3.2 and 4.8. Two methods of heat transfer prediction have been chosen--the methods of Beckwith and VaglioLaurin. These require that the inviscid streamline pattern on the surface of the yawed spherecone model be known. These steamlines have been calculated from measured surface pressure distributions. The theory of Beckwith agrees reasonably well with the experimental data.
Book Synopsis Laminar Heat-transfer Distributions for a Blunted-cone, Cone-frustum Reentry Configuration at Mach 10 by : J. David Dearing
Download or read book Laminar Heat-transfer Distributions for a Blunted-cone, Cone-frustum Reentry Configuration at Mach 10 written by J. David Dearing and published by . This book was released on 1969 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Heat-transfer Distributions in Deep Cavities in Hypersonic Separated Flow by : Allan R. Wieting
Download or read book Experimental Investigation of Heat-transfer Distributions in Deep Cavities in Hypersonic Separated Flow written by Allan R. Wieting and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypervelocity wind tunnel tests to determine local cold wall convective heating rates to small rectangular cavities,
Book Synopsis Comparison of Theoretical and Experimental Heat Transfer on a Cooled 20 Degree Cone with a Laminar Boundary Layer at a Mach Number of 2.02 by : Richard Scherrer
Download or read book Comparison of Theoretical and Experimental Heat Transfer on a Cooled 20 Degree Cone with a Laminar Boundary Layer at a Mach Number of 2.02 written by Richard Scherrer and published by . This book was released on 1950 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer measurements have been made on a cooled 20 degree cone with a laminar boundary layer at a Mach number of 2.02. Although the constant-temperature test region on the cone was preceded by severe surface-temperature gradients, a comparison of the results with the theory for a constant surface temperature on the basis of heat-transfer parameter, Nusselt number divided by the square root of Reynolds number, indicates agreement within the experimental accuracy over 60 percent of the instrumented length of the cone.
Book Synopsis Measurements of Pressure and Local Heat Transfer on a 20 Deg Cone at Angles of Attack Up to 20 Deg for a Mach Number of 4.95 by :
Download or read book Measurements of Pressure and Local Heat Transfer on a 20 Deg Cone at Angles of Attack Up to 20 Deg for a Mach Number of 4.95 written by and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Base Heating on Typical Mars Entry Body Shapes by : O. L. Zappa
Download or read book An Experimental Investigation of Base Heating on Typical Mars Entry Body Shapes written by O. L. Zappa and published by . This book was released on 1971 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis U.S. Government Research Reports by :
Download or read book U.S. Government Research Reports written by and published by . This book was released on 1962 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Near Wake of a Slender Cone at Mach Number by : Robert J. Cresci
Download or read book An Experimental Investigation of the Near Wake of a Slender Cone at Mach Number written by Robert J. Cresci and published by . This book was released on 1965 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: Various experimental data were obtained in the near wake region of a 10 degree angle sharp cone at free stream Mach numbers of 8.0 and 11.8. The Mach 8.0 tests were conducted at free stream Reynolds numbers of 300,000 and 1,700,000 per foot; laminar and turbulent boundary layers were obtained on the cone surface at these respective Reynolds numbers. Data obtained include radial profiles of temperature, pressure, and Mach number at axial locations between one and three base diameters downstream of the model. Heat transfer and pressure distributions on the model base were also obtained. The Mach 11.8 tests were conducted at a free stream Reynolds number of 600,000 per foot and the surface boundary layer for all these tests were laminar. Data obtained include centerline distributions of Mach number, pressure, and temperature for a distance between one and four base diameters downstream of the model. Centerline temperatures were also obtained in the recirculation region for model wall to stagnation temperature ratios of 0.06 and 0.47. In addition, total temperature profiles were obtained downstream of the rear stagnation point. (Author).
Book Synopsis An Experimental Investigation of Flat Plate Heat Transfer Coefficients at Mach Numbers of 2, 2.5, and 3 for a Surface Temperature to Stream Total Temperature Ratio of 1.18 by : Robert Howard Shoulberg
Download or read book An Experimental Investigation of Flat Plate Heat Transfer Coefficients at Mach Numbers of 2, 2.5, and 3 for a Surface Temperature to Stream Total Temperature Ratio of 1.18 written by Robert Howard Shoulberg and published by . This book was released on 1953 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Characteristics of a 40 Degree Cone for Measuring Mach Number, Total Pressure, and Flow Angles at Supersonic Speeds by : Frank J. Centolanzi
Download or read book Characteristics of a 40 Degree Cone for Measuring Mach Number, Total Pressure, and Flow Angles at Supersonic Speeds written by Frank J. Centolanzi and published by . This book was released on 1957 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted to determine the characteristics of a 40 degree cone for use in the measurement of Mach number, total pressure, and flow angles. The cone had a total-pressure orifice at the apex and four equally spaced static-pressure orifices on the surface. Pressure measurements were taken at angles of pitch up to 26 degrees at Mach numbers of 1.72, 1.95, and 2.46 for Reynolds numbers of 3.12 and 5.41 million per foot. This instrument is capable of measuring Mach number within approximately plus-or-minus 1.0 percent and the flow angles within plus-or-minus 0.25 degrees. The total pressure can be measured within plus-or-minus 0.5 percent at a Mach number of 1.72 and within plus-or-minus 2.0 percent at a Mach number of 2.46. These flow quantities can be determined from the measured cone pressures and charts presented in this report. In general, an iterative procedure is required; however, in practice, such a procedure is necessary only for accurate determination of the Mach number and total pressure at Mach numbers near 2.5.
Book Synopsis Experimental Investigation of Temperature Recovery Factors on a 10 Degree Cone at Angle of Attack at a Mach Number of 3.12 by : John R. Jack
Download or read book Experimental Investigation of Temperature Recovery Factors on a 10 Degree Cone at Angle of Attack at a Mach Number of 3.12 written by John R. Jack and published by . This book was released on 1954 with total page 15 pages. Available in PDF, EPUB and Kindle. Book excerpt: For the windward surface of the model, local recovery factors in the fully laminar and turbulent regions were not significantly affected by changes in angle of attack. At all angles of attack, increasing the free-stream Reynolds number moved the transition region upstream. For a given angle of attack, the transition region on the leeward surface is substantially upstream of that on the windward surface.
Book Synopsis An Experimental Investigation of Heat Transfer to Cones in Rarified Hypersonic Flow by : Carl T. Berry
Download or read book An Experimental Investigation of Heat Transfer to Cones in Rarified Hypersonic Flow written by Carl T. Berry and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of Heat Transfer to Cones in Rarefied Hypersonic Flow by : Carl T. Berry
Download or read book An Experimental Investigation of Heat Transfer to Cones in Rarefied Hypersonic Flow written by Carl T. Berry and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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