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Heat Transfer Measurements On A Flat Plate With Attached Protuberances In A Turbulent Boundary Layer At Mach Numbers Of 249 351 And 444
Download Heat Transfer Measurements On A Flat Plate With Attached Protuberances In A Turbulent Boundary Layer At Mach Numbers Of 249 351 And 444 full books in PDF, epub, and Kindle. Read online Heat Transfer Measurements On A Flat Plate With Attached Protuberances In A Turbulent Boundary Layer At Mach Numbers Of 249 351 And 444 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
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 Heat-transfer Measurements on a Flat Plate with Attached Protuberances in a Turbulent Boundary Layer at Mach Numbers of 2.49, 3.51, and 4.44 by : Lana Murphy Couch
Download or read book Heat-transfer Measurements on a Flat Plate with Attached Protuberances in a Turbulent Boundary Layer at Mach Numbers of 2.49, 3.51, and 4.44 written by Lana Murphy Couch and published by . This book was released on 1966 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on a Flat Plate and Attached Protuberances in a Turbulent Boundary Layer at Mach Numbers of 2.65, 3.51, and 4.44 by : Robert L. Stallings
Download or read book Heat-transfer Measurements on a Flat Plate and Attached Protuberances in a Turbulent Boundary Layer at Mach Numbers of 2.65, 3.51, and 4.44 written by Robert L. Stallings and published by . This book was released on 1964 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on a Flat Plate and Attached Fins at Mach Numbers of 3.51 and 4.44 by : Earl A. Price
Download or read book Heat-transfer Measurements on a Flat Plate and Attached Fins at Mach Numbers of 3.51 and 4.44 written by Earl A. Price and published by . This book was released on 1964 with total page 46 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 Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers with Variable Fluid Properties by : Robert G. Deissler
Download or read book Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers with Variable Fluid Properties written by Robert G. Deissler and published by . This book was released on 1958 with total page 608 pages. Available in PDF, EPUB and Kindle. Book excerpt: A previous analysis of turbulent heat transfer and flow with variable fluid properties in smooth passages is extended to flow over a flat plate at high Mach numbers. Velocity and temperature distributions are calculated for a boundary layer in which the effects of both frictional heating and external heat transfer are appreciable. The viscosity and thermal conductivity are assumed to vary as a power of the temperature, while the Prandtl number and specific heat are taken as constant. Skin-friction and heat-transfer coefficients are calculated and compared with the incompressible values. The relation between boundary-layer thickness and distance along the plate is obtained for various Mach numbers. The analytical results are compared with representative experimental data.
Book Synopsis Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers with Variable Fluid Properties by : R. G. Deissler
Download or read book Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers with Variable Fluid Properties written by R. G. Deissler and published by . This book was released on 1959 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free Flight Observation of a Separated Turbulent Flow Including Heat Transfer Up to Mach 8.5 by : Dudley George McConnell
Download or read book Free Flight Observation of a Separated Turbulent Flow Including Heat Transfer Up to Mach 8.5 written by Dudley George McConnell and published by . This book was released on 1960 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: A turbulent boundary layer separated by a forward-facing step was observed on the cylindrical portion of a hemisphere-cone-cylinder test vehicle. Tip blunting, producing a shear flow, was found to induce higher pressures on the cylindrical portion than were predicted from ballistic tunnel data of unblunted projectiles. An approximate method for predicting this blunt-body pressure distribution was hypothesized. These findings, along with the hypothesis, were substantiated by a wind tunnel test of a similar body. The peak pressure ratios of the separation were smaller in magnitude than flat plate theory predicted because of the effect of the shear flow. The decrement in heating of the separated flow, relative to the corresponding attached flow, was found to compare well with the expected results.
Book Synopsis The Effect of an Arbitrary Surface-temperature Variation Along a Flat Plate on the Convective Heat Transfer in an Incompressible Turbulent Boundary Layer by : Morris W. Rubesin
Download or read book The Effect of an Arbitrary Surface-temperature Variation Along a Flat Plate on the Convective Heat Transfer in an Incompressible Turbulent Boundary Layer written by Morris W. Rubesin and published by . This book was released on 1951 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis was performed to determine the effects on the rates of convective heat transfer produced by arbitrary variations of the surface temperature with distance along a flat plate. The analysis was confined to the case of a low-speed turbulent boundary layer on a flat plate oriented parallel to the free-stream velocity. It was found that a continuously variable surface temperature has, in general, a smaller effect on the local convective heat transfer than does a surface-temperature discontinuity.
Book Synopsis Heat Transfer on an Afterbody Immersed in the Separated Wake of a Hemisphere by : Helmer V. Nielsen
Download or read book Heat Transfer on an Afterbody Immersed in the Separated Wake of a Hemisphere written by Helmer V. Nielsen and published by . This book was released on 1958 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted to determine the average heat transfer and temperature recovery factor on a tapered cylindrical afterbody immersed in the wake of a hemisphere. The range of the investigation was from a Reynolds number of 125,000 to 870,000 (based on hemisphere diameter and free-stream conditions). The nominal Mach number was 2.4.
Book Synopsis Heat Transfer and Skin Friction for Turbulent Boundary Layers on Heated Or Cooled Surfaces at High Speeds by : Coleman duP. Donaldson
Download or read book Heat Transfer and Skin Friction for Turbulent Boundary Layers on Heated Or Cooled Surfaces at High Speeds written by Coleman duP. Donaldson and published by . This book was released on 1952 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent boundary layer in compressible flow on an insulated surface is extended to evaluate the turbulent skin friction and heat transfer in compressible flow on a surface which is heated or cooled. The results of this analysis are in good agreement with the heat transfers measured in flight on the NACA RM-10 missile up to Mach number of 3.8.
Book Synopsis Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration by : Charles B. Rumsey
Download or read book Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis 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 by : Howard S. Carter
Download or read book 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 written by Howard S. Carter and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
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 Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : Robert L. O'Neal
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Heat-Transfer and Pressure Measurements on a Flat-Face Cylinder at a Mach Number Range of 2.49 to 4.44 by : Paige B. Burbank
Download or read book Heat-Transfer and Pressure Measurements on a Flat-Face Cylinder at a Mach Number Range of 2.49 to 4.44 written by Paige B. Burbank and published by . This book was released on 1959 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
