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A Method Of Calculating Boundary Layer Thickness In Axisymmetric Nozzles With Laminar Hypersonic Flow
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Book Synopsis A Method of Calculating Boundary-layer Thickness in Axisymmetric Nozzles with Laminar Hypersonic Flow by : Arlo F. Johnson
Download or read book A Method of Calculating Boundary-layer Thickness in Axisymmetric Nozzles with Laminar Hypersonic Flow written by Arlo F. Johnson and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The excellent agreement between measured boundary layer thickness and thickness calculated by Sivells and Payne recommends their method for calculating turbulent boundary layer growth in axisymmetric hypersonic nozzles. It was thought worthwhile to adapt their approach to the laminar boundary layer. This analysis, along with a limited amount of corroborating data, is presented herein.
Download or read book SC-RR written by and published by . This book was released on 19?? with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Thicknesses of Laminar Boundary Layers in Axisymmetric Nozzles with Low-Density, Hypervelocity Flows by : J. A. Durand
Download or read book Calculation of Thicknesses of Laminar Boundary Layers in Axisymmetric Nozzles with Low-Density, Hypervelocity Flows written by J. A. Durand and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new method for the estimation of boundarylayer thickness corrections to the contours of cooled axisymmetric nozzles for low-density, hypersonic flows is presented. Laminar flows of real gases in thermodynamic equilibrium with possible variation of specific heats, frozen flows, and boundary-layer thicknesses of the order of nozzle radii are considered. The derivation combines an appropriate integral momentum relation with an approximate friction law based on local similarity. Results of application of the method to several typical cases are shown to agree closely with experimental data. (Author).
Book Synopsis An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature by : Jay M. Solomon
Download or read book An Approximate Solution for Compressible Axisymmetric Laminar Boundary Layers Including the Effects of Transverse Curvature written by Jay M. Solomon and published by . This book was released on 1967 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approximate momentum integral solution for the compressible axisymmetrix laminar boundary layer when transverse curvature effects are important is presented. Both finite and infinite inviscid Mach numbers are considered. Detailed comparisons with exact asymptotic solutions are given. The method is found, in many instances, to agree to leading order with the exact solutions as the transverse curvature becomes very large--a property that none of the existing approximate solutions for compressible flow possess. Some example calculations for a cone in supersonic and hypersonic flow are presented. Also, the method is applied to the hypersonic self-induced pressure problem for a cone. (Author).
Book Synopsis Real-gas Laminar Boundary Layers in Hypervelocity Nozzles by : Willard E. Summers
Download or read book Real-gas Laminar Boundary Layers in Hypervelocity Nozzles written by Willard E. Summers and published by . This book was released on 1965 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Comparisons of Turbulent-boundary-layer Measurements at Mach Number 19.5 with Theory and an Assessment of Probe Errors by : Ivan E. Beckwith
Download or read book Comparisons of Turbulent-boundary-layer Measurements at Mach Number 19.5 with Theory and an Assessment of Probe Errors written by Ivan E. Beckwith and published by . This book was released on 1971 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of total temperature and pitot pressure across boundary layer of test section wall of axisymmetric contoured nozzle at hypersonic speed in nitrogen.
Book Synopsis Low-density Boundary-layer Modulation by Suction in a Hypersonic Nozzle by : Max Kinslow
Download or read book Low-density Boundary-layer Modulation by Suction in a Hypersonic Nozzle written by Max Kinslow and published by . This book was released on 1973 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: The potential value of controlled boundary-layer removal from the wall of a nozzle for low-density hypersonic flow was investigated in a brief experimental program. A particular objective was the achievement of sufficient control over boundary-layer thickness to enable a contoured nozzle to be operated under off-design conditions without excessive deterioration of flow uniformity. The nozzle contour was greatly influenced by boundary-layer thickness. Boundary-layer removal involved suction through perforated walls where local nozzle static pressures exceeded the pressure in the large tank which enclosed the nozzle and test section.
Book Synopsis Methods of Calculating Boundary Layer Thickness in a Supersonic Nozzle by : Harold Klein
Download or read book Methods of Calculating Boundary Layer Thickness in a Supersonic Nozzle written by Harold Klein and published by . This book was released on 1947 with total page 198 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Investigation of a Boundary Layer and Heat Transfer in a Supersonic Nozzle by : Edwin Snow Gallacher
Download or read book Theoretical Investigation of a Boundary Layer and Heat Transfer in a Supersonic Nozzle written by Edwin Snow Gallacher and published by . This book was released on 1950 with total page 214 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Parametric Study of Relaminarization of Turbulent Boundary Layers on Nozzle Walls by : J. P. Kreskovsky
Download or read book Parametric Study of Relaminarization of Turbulent Boundary Layers on Nozzle Walls written by J. P. Kreskovsky and published by . This book was released on 1974 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculation of Compressible, Nonadiabatic Boundary Layers in Laminar, Transitional and Turbulent Flow by the Method of Integral Relations by : Gary D. Kuhn
Download or read book Calculation of Compressible, Nonadiabatic Boundary Layers in Laminar, Transitional and Turbulent Flow by the Method of Integral Relations written by Gary D. Kuhn and published by . This book was released on 1971 with total page 140 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients by : Shimer Zane Pinckney
Download or read book Method for Predicting Compressible Turbulent Boundary Layers in Adverse Pressure Gradients written by Shimer Zane Pinckney and published by . This book was released on 1971 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Integral Methods in Compressible Laminar Boundary Layers and Their Application to Hypersonic Pressure Interactions by : Yat-Yung Chan
Download or read book Integral Methods in Compressible Laminar Boundary Layers and Their Application to Hypersonic Pressure Interactions written by Yat-Yung Chan and published by . This book was released on 1965 with total page 108 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical and Experimental Investigation of Boundary Layers in Low Density Hypersonic Axisymmetric Nozzles by : David L. Whitfield
Download or read book Theoretical and Experimental Investigation of Boundary Layers in Low Density Hypersonic Axisymmetric Nozzles written by David L. Whitfield and published by . This book was released on 1968 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt: The viscous flow region in low density hypersonic axisymmetric nozzles was investigated both theoretically and experimentally. Nonsimilar solutions were obtained for the internal laminar boundary layer equations which include second-order transverse curvature terms. These solutions were obtained on a CDC 1604 digital computer. Four existing low density axisymmetric nozzles were considered. Numerical solutions were obtained for these nozzles using various plenum chamber conditions and wall temperature distributions. The plenum chamber conditions used in the numerical solutions for these nozzles produced a test section Mach number range of about 3.0 to 18.0 and a test section Reynolds number per foot range of about 1000 to 15,000. Some results of the numerical solutions are compared with experimental measurements of pitot pressure, relative heat flux, and nozzle wall heat transfer coefficients. In all comparisons the numerical solutions appear to be consistent with the experimental data. (Author).
Book Synopsis Axisymmetric Laminar Boundary Layers with Very Large Transverse Curvature by : Jay M. Solomon
Download or read book Axisymmetric Laminar Boundary Layers with Very Large Transverse Curvature written by Jay M. Solomon and published by . This book was released on 1967 with total page 130 pages. Available in PDF, EPUB and Kindle. Book excerpt: The compressible axisymmetric laminar boundary layer is considered for very large values of the transverse curvature parameter (roughly proportional to the ratio of the Mangler value of the boundary layer displacement thickness to the local cross-sectional radius of the body). Asymptotic expansions are constructed using the method of inner-outer expansions and verified by comparison with exact numerical similarity solutions. Both finite and hypersonic Mach number inviscid flow conditions are considered. The principal results are asymptotic formulas for skin friction, heat transfer, and boundary layer displacement thickness. Existing expansions, obtained by Wei, are found to be incorrect. The viscous pressure interaction near the vertex of a pointed axisymmetric body is treated within the framework of boundary layer theory and a tangent-cone approximation. (Author).
Book Synopsis Boundary Layer Profile Measurements in Hypersonic Nozzles by : Norman Ellis Scaggs
Download or read book Boundary Layer Profile Measurements in Hypersonic Nozzles written by Norman Ellis Scaggs and published by . This book was released on 1965 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Crocco's relationship for the static temperature in terms of the velocity profile. (Author).
Book Synopsis Boundary Layer Profile Measurements in Hypersonic Nozzles by : Norman Ellis Scaggs
Download or read book Boundary Layer Profile Measurements in Hypersonic Nozzles written by Norman Ellis Scaggs and published by . This book was released on 1965 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation made to determine the flow parameter profiles across the boundary layer on contoured, axisymmetric hypersonic nozzles is described. The pitot pressure and total temperature profiles measured across the boundary layers on nozzles of Mach number seven and twelve are shown in graphical form. The static temperature and velocity profiles, calculated with the assumption of constant static pressure across the boundary layer, are given. A correlation is shown to exist between the exponent of the velocity profile power law and the product of the ratios of wall temperature to free stream total temperature and axial distance to momentum thickness. The static temperature profiles, calculated from the measured data is compared with Crocco's relationship for the static temperature in terms of the velocity profile. (Author).
