Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Experimental Investigation Of Turbulent Boundary Layer Heat Transfer Rates On A Flat Plate In Low Mach Number Supersonic Flow With High Wall Cooling
Download Experimental Investigation Of Turbulent Boundary Layer Heat Transfer Rates On A Flat Plate In Low Mach Number Supersonic Flow With High Wall Cooling full books in PDF, epub, and Kindle. Read online Experimental Investigation Of Turbulent Boundary Layer Heat Transfer Rates On A Flat Plate In Low Mach Number Supersonic Flow With High Wall Cooling ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Experimental Investigation of Turbulent Boundary Layer Heat Transfer Rates on a Flat Plate in Low Mach Number Supersonic Flow with High Wall Cooling by : Kerry Gordon Geringer
Download or read book Experimental Investigation of Turbulent Boundary Layer Heat Transfer Rates on a Flat Plate in Low Mach Number Supersonic Flow with High Wall Cooling written by Kerry Gordon Geringer and published by . This book was released on 1973 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy by : Alvin Seiff
Download or read book Examination of the Existing Data on the Heat Transfer of Turbulent Boundary Layers at Supersonic Speeds from the Point of View of Reynolds Analogy written by Alvin Seiff and published by . This book was released on 1954 with total page 654 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer data from four wind-tunnel experiments and two free-flight experiments with turbulent boundary layers have been examined to see whether or not they are well represented by the Reynolds analogy or a modification thereof. The heat-transfer results are put into the form of dimensionless Stanton numbers based on fluid properties at the outer edge of the boundary layer and are compared with skin-friction coefficients for the same Mach numbers and wall to free-stream temperature ratios as obtained from an interpolation of the existing skin-friction data. The effective Reynolds number is taken to be the length Reynolds number measured from the effective turbulent origin, a position which differs importantly from the leading edge of the test surface in some cases.
Book Synopsis Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution by : Raul J. Conti
Download or read book Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution written by Raul J. Conti and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution by : Raul Jorge Conti
Download or read book Heat-transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution written by Raul Jorge Conti and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Measurements on a Flat-plate Surface and Heat-transfer Measurements on Attached Protuberances in a Supersonic Turbulent Boundary Layer at Mach Numbers of 2.65, 3.51, and 4.44 by : Paige B. Burbank
Download or read book Heat-transfer and Pressure Measurements on a Flat-plate Surface and Heat-transfer Measurements on Attached Protuberances in a Supersonic Turbulent Boundary Layer at Mach Numbers of 2.65, 3.51, and 4.44 written by Paige B. Burbank and published by . This book was released on 1962 with total page 430 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow by : Robert W. Higgins
Download or read book An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow written by Robert W. Higgins and published by . This book was released on 1951 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition has been studied on a heated flat plate in an air stream at a Mach number of 2.40 and a length Reynolds number range from 475,000 to 3,930,000. The transition region was investigated at nominal plate temperature levels of 60, 100, 140, 180, and 260 degrees F and depicted in a series of curves of transition Reynolds numbers, based on boundary-layer dimensions and fluid properties evaluated alternatively at free-stream and wall temperatures. The average skin-friction coefficient over the laminar portion of the boundary layer was determined.
Book Synopsis Experimental Investigation of Heat Transfer Through Laminar and Turbulent Boundary Layers on a Cooled Flat Plate at a Mach Number of 2.4 by : Ellis G. Slack
Download or read book Experimental Investigation of Heat Transfer Through Laminar and Turbulent Boundary Layers on a Cooled Flat Plate at a Mach Number of 2.4 written by Ellis G. Slack and published by . This book was released on 1952 with total page 734 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wind-tunnel tests of the heat-transfer characteristics for laminar and turbulent boundary layers on a cooled flat plate were conducted at a Mach number of 2.4. Data were obtained for a Reynolds number range of 150.000 to 3,000.000 and for a surface-temperature range of -40 degrees F to 45 degrees F with recovery temperature of the order of 65 degrees F. The temperature-recovery factors agreed well with previous flat-plate reslts. The heat-transfer results were obtained with negative temperature gradients along the surface and, when related to the constant-surface-temperature case, were, in general, in good agreement with theory.
Book Synopsis Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds by : William A. Cassels
Download or read book Boundary-layer Transition Study of Several Pointed Bodies of Revolution at Supersonic Speeds written by William A. Cassels and published by . This book was released on 1970 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Boundary-layer transition by the sublimation and impact-pressure techniques and force tests have been performed on three Haack-Adams bodies of revolution of fineness ratios 7, 10, and 13 at zero angle of attack for free-stream Mach numbers of 2.00, 2.75, and 4.63 and a range of Reynolds numbers based on model length of 6 to 15 X 10(to the 6 power) with and without a roughness strip. The grit method of inducing turbulence was found to provide for a nearly complete turbulent flow over the models at the lower Mach numbers and higher Reynolds numbers considered in this study while the amount of trip drag was less than 8 percent of the model drag with transition fixed. A method of interpreting sublimation data was discussed and used and the results compared well with the impact-pressure results.
Book Synopsis Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures by : Ernst Rudolf Georg Eckert
Download or read book Survey of Boundary Layer Heat Transfer at High Velocities and High Temperatures written by Ernst Rudolf Georg Eckert and published by . This book was released on 1960 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer by : Robert L. P. Voisinet
Download or read book Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer written by Robert L. P. Voisinet and published by . This book was released on 1973 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
Book Synopsis Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow by : Maurice Tucker
Download or read book Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow written by Maurice Tucker and published by . This book was released on 1951 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Book Synopsis Analysis of the Three-dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow by : John C. Adams
Download or read book Analysis of the Three-dimensional Compressible Turbulent Boundary Layer on a Sharp Cone at Incidence in Supersonic and Hypersonic Flow written by John C. Adams and published by . This book was released on 1972 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 150 Cone in Free Flight at Supersonic Mach Numbers Up to 5.2 by : Charles B. Rumsey
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 150 Cone in Free Flight at Supersonic Mach Numbers Up to 5.2 written by Charles B. Rumsey and published by . This book was released on 1961 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract:
Book Synopsis Measurement of Heat Transfer in the Turbulent Boundary Layer on a Flat Plate in Supersonic Flow and Comparison with Skin-friction Results by : C. C. Pappas
Download or read book Measurement of Heat Transfer in the Turbulent Boundary Layer on a Flat Plate in Supersonic Flow and Comparison with Skin-friction Results written by C. C. Pappas and published by . This book was released on 1954 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local heat-transfer rates on the surface of a heated flat plate at zero incidence to an air stream flowing at Mach numbers of 1.69 and 2.27 are presented. The Reynolds number range for both Mach numbers was 1,000,000 to 10,000,000. Surface temperatures were maintained near recovery temperature. It was found that the variation of heat transfer with Mach number was in agreement with previously reported variations of directly measured skin friction with Mach number on unheated bodies. The variation with Mach number of the average skin-friction coefficient, as determined from impact-pressure surveys, was in agreement with that from other momentum loss measurements but differed from the variation obtained from directly measured skin friction as reported by others.
Book Synopsis Turbulent Shear Layers in Supersonic Flow by : Alexander J. Smits
Download or read book Turbulent Shear Layers in Supersonic Flow written by Alexander J. Smits and published by A I P Press. This book was released on 1996 with total page 384 pages. Available in PDF, EPUB and Kindle. Book excerpt: Using the most recent data, this text describes the physical mechanisms of turbulent supersonic flows, emphasizing the similarities and differences between compressible and incompressible flows. DLC: Aerodynamics, Supersonic.
Book Synopsis Turbulent Boundary Layer Displacement Effects in Hypersonic Flow by : R. M. Grabow
Download or read book Turbulent Boundary Layer Displacement Effects in Hypersonic Flow written by R. M. Grabow and published by . This book was released on 1967 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of Laminar, Transitional and Turbulent Heat Transfer on Blunt-nosed Bodies in Hypersonic Flow by : Robert J. Cresci
Download or read book An Investigation of Laminar, Transitional and Turbulent Heat Transfer on Blunt-nosed Bodies in Hypersonic Flow written by Robert J. Cresci and published by . This book was released on 1959 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
