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Determination of General Relations for the Behavior of Turbulent Boundary Layers

Description: Report presenting an analysis of data for turbulent boundary layers along wings and bodies of various shapes in order to determine the fundamental variables that control the development of turbulent boundary layers. Results indicate that the type of velocity distribution in the boundary layer could be expressed in terms of a single parameter.
Date: July 1943
Creator: von Doenhoff, Albert E. & Tetervin, Neal
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Some Recent Contributions to the Study of Transition and Turbulent Boundary Layers

Description: Report presenting a paper in two parts about transition and turbulent boundary layers. The first part reviews the current problem of the instability of laminar boundary layers. The second part reviews the current state of knowledge of the mechanics of turbulent boundary layers and of the methods now being used for fundamental studies of the turbulent fluctuations in turbulent boundary layers.
Date: April 1947
Creator: Dryden, Hugh L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations on Reductions of Friction on Wings, in Particular by Means of Boundary Layer Suction

Description: Memorandum presenting investigation on reductions of friction on wings, especially by means of boundary-layer suction. The report is broken up into several sections, including: causes of transition, laminar profiles with the transition taking place, laminar boundary-layer suction, investigation of the laminar pressure increase, investigation of the slot flow for laminar boundary-layer suction with single slots, tests about keeping a boundary layer for high Reynolds laminar with the aid of bound… more
Date: August 1947
Creator: Pfenninger, Werner
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigation of Effects of Surface Temperature and Single Roughness Elements on Boundary-Layer Transition

Description: Note presenting an investigation of the laminar boundary layer and the position of the transition point on a heated flat plate. The Reynolds number of transition was found to decrease as the temperature of the plate is increased. Results regarding the effect of surface temperature, effect of roughness elements, mean-velocity profile near a heated wall, instability of inflection-point profiles, and laminar separation and transition are provided.
Date: April 1947
Creator: Liepmann, Hans W. & Fila, Gertrude H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature

Description: From Summary: "Exact solution of the laminar-boundary-layer equations for wedge-type flow with constant property values are presented for transpiration-cooled surfaces with variable wall temperatures. The difference between wall and stream temperature is assumed proportional to a power of the distance from the leading edge. Solutions are given for a Prandtl number of 0.7 and ranges of pressure-gradient, cooling-air-flow, and wall-temperature-gradient parameters. Boundary-layer profiles, dimensi… more
Date: July 15, 1954
Creator: Donoughe, Patrick L. & Livingood, John N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Calculations of Laminar Heat Transfer Around Cylinders of Arbitrary Cross Section and Transpiration-Cooled Walls With Application to Turbine Blade Cooling

Description: "An approximate method for the development of flow and thermal boundary layers in the laminar region on cylinders with arbitrary cross section and transpiration-cooled walls is obtained by the use of Karman's integrated momentum equation and an analogous heat-flow equation. Incompressible flow with constant property values throughout the boundary layer is assumed. The velocity and temperature profiles within the boundary layer are approximated by expressions composed of trigonometric functions"… more
Date: June 22, 1951
Creator: Eckert, E. R. G. & Livingood, J. N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Similar Solutions for the Compressible Laminar Boundary Layer with Heat Transfer and Pressure Gradient

Description: "Stewartson's transformation is applied to the laminar compressible boundary-layer equations and the requirement of similarity is introduced, resulting in a set of ordinary nonlinear differential equations previously quoted by Stewartson, but unsolved. The requirements of the system are Prandtl number of 1.0, linear viscosity-temperature relation across the boundary layer, an isothermal surface, and the particular distributions of free-stream velocity consistent with similar solutions. This sys… more
Date: October 15, 1954
Creator: Cohen, Clarence B. & Reshotko, Eli
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-Stream Boundaries of Turbulent Flows

Description: Report presents the results of an experimental and theoretical study made of the instantaneously sharp and irregular front which is always found to separate turbulent fluid from contiguous "nonturbulent" fluid at a free-stream boundary. This distinct demarcation is known to give an intermittent character to hot-wire signals in the boundary zone. The overall behavior of the front is described statistically in terms of its wrinkle-amplitude growth and its lateral propagation relative to the fluid… more
Date: 1955
Creator: Corrsin, Stanley & Kistler, Alan L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis and Calculation by Integral Methods of Laminar Compressible Boundary-Layer With Heat Transfer and With and Without Pressure Gradient

Description: From Introduction: "The purpose of the present report is to present a comprehensive summary of theoretical investigations of comprehensible laminar boundary layers which have been carried out since 1949 at the Polytechnic Institute of Brooklyn under the sponsorship and with the financial assistance of the National Advisory Committee for Aeronautics. The results of these investigations are contained primarily in references 1 to 7."
Date: April 12, 1955
Creator: Morduchow, Morris
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Influence of Surface Injection on Heat-Transfer and Skin Friction Associated With the High-Speed Turbulent Boundary Layer

Description: Memorandum presenting a correlation of analyses of the effect of distributed surface injection on the heat transfer and skin friction associated with the turbulent boundary layer at high speeds to eliminate the effects of Mach and Reynolds number. Data for heat transfer and skin friction at three Mach numbers are compared with the analyses and the agreement is good.
Date: February 20, 1956
Creator: Rubesin, Morris W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Similarity Theory for Turbulent Boundary Layer Over a Flat Plate in Compressible Flow

Description: Note presenting a treatment of the problem of turbulent boundary layer over a flat plate in compressible flow. The dissipation term in the energy equation, often neglected, is first carefully studied and found to be of importance. The four main approximations include the turbulence pattern, the boundary-layer growth, the two choices of the length scale, and the effect of pressure gradient.
Date: November 1951
Creator: Lin, C. C. & Shen, S. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flow: Investigation of Turbulent Boundary Layer Over a Flat Plate in Compressible Flow by the Similarity Theory

Description: Note presenting an investigation of the turbulent-boundary-layer flow over a flat plate in compressible flow. The report shows how the influence of the Mach number can be predicted from the theory after the constant coefficients in the theory are determined by one set of experimental measurements. By averaging the Navier-Stokes equations, differential equations for the mean flow are obtained.
Date: November 1951
Creator: Shen, S. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Laminar Boundary Layer With Heat Transfer on a Cone at Angle of Attack in a Supersonic Stream

Description: Note presenting the equations of the compressible laminar boundary layer for the windward streamline in the plane of symmetry of a yawed cone. Solutions are obtained for both insulated and cooled surfaces. The heat-transfer rate to this most windward streamline increases significantly with angle of attack.
Date: December 1957
Creator: Reshotko, Eli
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Wall Cooling on Inlet Parameters of a Scoop Operating in a Turbulent Boundary Layer on a Flat or Conical Surface for Mach Numbers 2 to 10

Description: Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.
Date: March 1958
Creator: Beke, Andrew
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The compressible laminar boundary layer with heat transfer and small pressure gradient

Description: Report presenting a perturbation method for the calculation of velocity and temperature profiles and skin-friction and heat-transfer characteristics for two-dimensional, compressible laminar boundary layers with heat transfer and a small arbitrary pressure gradient is presented. The combined effects of heat transfer and pressure gradient on boundary-layer characteristics are demonstrated by applying the results of the analysis to two representative wings.
Date: October 1953
Creator: Low, George M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The compressible laminar boundary layer with heat transfer and arbitrary pressure gradient

Description: Report presenting an approximate method for the calculation of the compressible laminar boundary layer with heat transfer and arbitrary pressure gradient, based on Thwaites' correlation concept. The method results from the application of Stewartson's transformation to Prandtl's equations, which yields a nonlinear set of two first-order differential equations. Calculations of an example show that the method is reliable when compared with the perturbation method over the same range of Mach number… more
Date: April 1955
Creator: Cohen, Clarence B. & Reshotko, Eli
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Laminar Boundary Layer Behind Shock Advancing Into Stationary Fluid

Description: Note presenting a study of the laminar compressible boundary layer induced by a shock wave advancing into a stationary fluid bounded by a wall. Velocity and temperature profiles, recovery factors, and skin-friction and heat-transfer coefficients are tabulated for a wide range of shock strengths.
Date: March 1955
Creator: Mirels, Harold
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of thermal properties on laminar-boundary-layer characteristics

Description: Report presenting an iteration method for solving the laminar-boundary-layer equations for compressible flow in the absence of a pressure gradient when the temperature variation of all the fluid thermal properties is considered. Results in regard to skin friction and heat-transfer characteristics are provided.
Date: March 1953
Creator: Klunker, E. B. & McLean, F. Edward
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Modified Reynolds Analogy for the Compressible Turbulent Boundary Layer on a Flat Plate

Description: Note presenting a modified Reynolds analogy developed for the compressible turbulent boundary layer on a flat plate. When mixing-length theories are used to evaluate terms of the final expressions, it is found for air that the ratio of Stanton number to half the local skin-friction coefficient is greater than unity.
Date: March 1953
Creator: Rubesin, Morris W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Thermal System for Continuous Monitoring of Laminar and Turbulent Boundary-Layer Flows During Routine Flight

Description: Note presenting a thermal system which could be used to determine whether the boundary layer on a wing in flight is turbulent or laminar. Tests were made using this system in the low-turbulence pressure tunnel.
Date: September 1957
Creator: Richardson, Norman R. & Horton, Elmer A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Second Approximation to Laminar Compressible Boundary Layer on Flat Plate in Slip Flow

Description: Note presenting the first-order solution for the laminar compressible boundary-layer flow over a flat plate at constant wall temperature. The effect of slip at the wall as well as the interaction between the boundary-layer flow and the outer stream flow are taken into consideration.
Date: November 1952
Creator: Maslen, Stephen H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Laminar Boundary Layer on Cone in Supersonic Flow at Large Angle of Attack

Description: Note presenting an analysis of the laminar boundary-layer flow about a circular cone at large angles of attack to a supersonic stream in the plane of symmetry by a method applicable in general to the flow about conical bodies. Velocity profiles at the bottom of the cone indicated that the expected tendency of the boundary layer to become thinner on the under side of the cone as the angle of attack is increased.
Date: November 1952
Creator: Moore, Franklin K.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Compressible Laminar Boundary Layer Over a Yawed Infinite Cylinder With Heat Transfer and Arbitrary Prandtl Number

Description: Note presenting the equations for development of the compressible laminar boundary layer over a yawed infinite cylinder. The results indicate that the effect of yaw on the heat-transfer coefficient at the stagnation line depends markedly on the free-stream Mach number.
Date: June 1957
Creator: Reshotko, Eli & Beckwith, Ivan E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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