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Hypersonic Turbulent Cold Wall Skin Friction And Heat Transfer Measurements On An Axisymmetric Sharp Cone
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Book Synopsis Hypersonic, Turbulent, Cold-wall, Skin-friction and Heat-transfer Measurements on an Axisymmetric Sharp Cone by : Kuei-Yuan Chien
Download or read book Hypersonic, Turbulent, Cold-wall, Skin-friction and Heat-transfer Measurements on an Axisymmetric Sharp Cone written by Kuei-Yuan Chien and published by . This book was released on 1973 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent skin-friction coefficients directly measured on an axisymmetric five-degree-half-angle sharp cone by two floating-element skin-friction balances at a free-stream Mach number of 7.9 are presented. Heat-transfer distributions are obtained simultaneously. These results yield directly the Reynolds analogy factor. Experimental data are used to evaluate four predictive methods. Except for the relatively low-Reynolds-number case, the directly measured sharp-cone Reynolds analogy factor is between 1.01 and 1.07, which is in good agreement with recent flat-plate measurements. Results indicate that the Stanton Number is essentially constant for one range and decreases by about 10 percent in another. (Modified author abstract).
Book Synopsis Hypersonic, Turbulent, Cold-Wall, Skin-Friction and Heat-Transfer Measurements on an Axisymmetric Sharp Cone by : Kuei-Yuan Chien
Download or read book Hypersonic, Turbulent, Cold-Wall, Skin-Friction and Heat-Transfer Measurements on an Axisymmetric Sharp Cone written by Kuei-Yuan Chien and published by . This book was released on 1973 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent skin-friction coefficients directly measured on an axisymmetric five-degree-half-angle sharp cone by two floating-element skin-friction balances at a free-stream Mach number of 7.9 are presented. Heat-transfer distributions are obtained simultaneously. These results yield directly the Reynolds analogy factor. Experimental data are used to evaluate four predictive methods. Except for the relatively low-Reynolds-number case, the directly measured sharp-cone Reynolds analogy factor is between 1.01 and 1.07, which is in good agreement with recent flat-plate measurements. Results indicate that the Stanton Number is essentially constant for one range and decreases by about 10 percent in another. (Modified author abstract).
Book Synopsis Computation of the Skin-friction and Heat Transfer on a Sharp Cone in Axisymmetric Turbulent Hypersonic Flow by : Stephen Sacks
Download or read book Computation of the Skin-friction and Heat Transfer on a Sharp Cone in Axisymmetric Turbulent Hypersonic Flow written by Stephen Sacks and published by . This book was released on 1973 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program has been written to determine the skin-friction coefficient and heat-transfer rate on a sharp cone in axisymmetric hypersonic flow with a turbulent boundary layer. The methods of Spalding and Chi, Sommer and Short, and Van Driest transformations between the incompressible and compressible planes. The Karman-Schoenherr flat plate equation is used to relate the incompressible skin friction to Reynolds number based on momentum thickness. A listing of the program is also included in the report. (Author).
Book Synopsis Summary and Correlation of Skin-friction and Heat-transfer Data for a Hypersonic Turbulent Boundary Layer on Simple Shapes by : Edward J. Hopkins
Download or read book Summary and Correlation of Skin-friction and Heat-transfer Data for a Hypersonic Turbulent Boundary Layer on Simple Shapes written by Edward J. Hopkins and published by . This book was released on 1969 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt: Skin friction and heat transfer data for hypersonic turbulent layer on flat plates, wind tunnel wall, and cones.
Book Synopsis Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone by : Donald M. Wilson
Download or read book Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone written by Donald M. Wilson and published by . This book was released on 1967 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
Book Synopsis Turbulent Boundary Layer Skin Friction, Heat Transfer and Pressure Measurements on Hypersonic Inlet Compression Surfaces by : M. O Ryder (Jr)
Download or read book Turbulent Boundary Layer Skin Friction, Heat Transfer and Pressure Measurements on Hypersonic Inlet Compression Surfaces written by M. O Ryder (Jr) and published by . This book was released on 1968 with total page 143 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study of turbulent boundary layer flow, under the influence of adverse pressure gradients typical of hypersonic inlets, was conducted on a two-dimensional and an axisymmetric model each instrumented with skin friction, heat transfer and pressure gages. Tests were conducted over a Mach and Reynolds number rage of 6.74 to 11.37 and 1,050,000 per ft. to 29,300,000 per ft., respectively. These test conditions produced boundary layer transition on the forward portions of the models without resorting to artificial trips. It was possible to attain a fully turbulent boundary layer before the start of the adverse pressure gradient region for most of the axisymmetric model tests but for most of the two-dimensional tests, transition was not completed until after the start of the pressure gradient. A comparison of the pressure data with the inviscid pressure distribution was made and good agreement is generally found indicating very little change in effective model shape due to boundary layer growth. This result is a consequence of the large model size relative to the boundary layer thickness, i.e. high Reynolds number flows over large models. An important conclusion resulting from this program was that turbulent boundary layers can negotiate large adverse pressure gradients without separating. Comparison with some existing laminar boundary layer data indicate that a turbulent boundary layer can negotiate adverse pressure gradients at least an order of magnitude greater than those gradients which will separate a laminar layer. (Author).
Book Synopsis Influence of Roughness and Blowing on Compressible Turbulent Boundary Layer Flow by : Robert L.P. Voisinet
Download or read book Influence of Roughness and Blowing on Compressible Turbulent Boundary Layer Flow written by Robert L.P. Voisinet and published by . This book was released on 1979 with total page 224 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Hypersonic Rarefied Flow Over Sharp Slender Cones by : Marvin I. Kussoy
Download or read book Hypersonic Rarefied Flow Over Sharp Slender Cones written by Marvin I. Kussoy and published by . This book was released on 1972 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Drag, heat transfer, and number flux were measured on sharp cones in the near free, molecule flow regime, and the results were compared with available Monte Carlo calculations. In general, the calculations predicted the magnitude of the data; however, the heat transfer and drag increased with increasing Knudsen number at a faster rate than predicted. Also the drag coefficients measured for the slender cones at high Knudsen number were higher than predicted for free molecule flow. These disagreements between theory and experiment could possibly be attributed to the simplicity of the surface interaction laws assumed in the theory. Reynolds analogy factors obtained from the experimental measurements agreed with free-molecule values and also with that obtained by the Monte Carlo technique.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1984 with total page 1278 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Direct Measurement of Skin Friction on a Cone at Supersonic Speed by : Charles Barge Blumer
Download or read book The Direct Measurement of Skin Friction on a Cone at Supersonic Speed written by Charles Barge Blumer and published by . This book was released on 1954 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis International Aerospace Abstracts by :
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1996 with total page 500 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Skin Friction, Heat Transfer, and Pressure Measurements on Hypersonic Inlet Compression Surfaces in the Mach Number Range 7.5 to 16 by : M. O. Ryder (Jr.)
Download or read book Skin Friction, Heat Transfer, and Pressure Measurements on Hypersonic Inlet Compression Surfaces in the Mach Number Range 7.5 to 16 written by M. O. Ryder (Jr.) and published by . This book was released on 1965 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study of boundary layer flow, under the influence of adverse pressure gradients typical of hypersonic inlets, was conducted on two two-dimensional and three axisymmetric compression surface models instrumented with skin friction, heat transfer and pressure gages. Tests were conducted over a Mach and Reynolds number range of 7.5 to 16 and 32,000 per ft. to 4,700,000 per ft., respectively. The boundary layers on the two-dimensional models were laminar and attached for all conditions tested. Local laminar separation occurred for some conditions of the axisymmetric tests. Boundary layer transition occurred for the high Reynolds number runs at a Mach number of 8 on the axisymmetric models but the adverse pressure gradients were not large enough to cause the turbulent boundary layers to separate. The skin friction gages gave a more accurate indication of localized boundary layer separation than either the heat transfer or static pressure distributions on the models tested.
Book Synopsis Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone by : Donald M. Wilson
Download or read book Measurements of Hypersonic Turbulent Heat Transfer on a Highly Cooled Cone written by Donald M. Wilson and published by . This book was released on 1967 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
Book Synopsis A Review of High-speed, Convective, Heat-transfer Computation Methods by : Michael E. Tauber
Download or read book A Review of High-speed, Convective, Heat-transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Laminar Heat Transfer on Sharp and Blunt Ten-degree Cones in Conical and Parallel Low-density Flow by : David E. Boylan
Download or read book Laminar Heat Transfer on Sharp and Blunt Ten-degree Cones in Conical and Parallel Low-density Flow written by David E. Boylan and published by . This book was released on 1973 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents heat-transfer-rate measurements on sharp and blunt 10-deg half-angle cones at angles of attack between -9 and +10 deg in a low-density, hypersonic wind tunnel. Circumferential and longitudinal distributions are presented for cold wall conditions for a range at Mach and Reynolds numbers. The effect of source-like flows was studied by utilizing both conical and contoured expansion nozzles with the same free-stream similarity parameters and model wall temperatures. Comparisons are made with previously published experimental and theoretical results. (Author).
Book Synopsis Local Skin Friction and Induced Pressure Measurements on a Sharp-edged Insulated Flat Plate in Low Density Hypersonic Flow by : Eugene Sidney Moulic
Download or read book Local Skin Friction and Induced Pressure Measurements on a Sharp-edged Insulated Flat Plate in Low Density Hypersonic Flow written by Eugene Sidney Moulic and published by . This book was released on 1966 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurement of Heat Transfer and Recovery Factor of a Compressible Turbulent Boundary Layer on a Sharp Cone with Foreign Gas Injection by : C. C. Pappas
Download or read book Measurement of Heat Transfer and Recovery Factor of a Compressible Turbulent Boundary Layer on a Sharp Cone with Foreign Gas Injection written by C. C. Pappas and published by . This book was released on 1964 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt:
