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Results for “Laminarization”
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The Eckert reference formulation applied to high-speed laminar boundary layers of nitrogen and carbon dioxide
Eckert reference equation for nitrogen and carbon dioxide boundary layer approximations at high speed
Analysis of laminar fully developed heat transfer in thin rectangular channels with fuel loading removed from the corners.
Convective heat transfer in thin rectangular channels commonly found in nuclear reactor fuel assemblies
Integral method in compressible laminar boundary layers and its application.
Properties of compressible boundary layers with heat transfer and arbitrary pressure gradients calculated, using integral equation and correlation concept for application in hypersonic flows
Nonsimilar solution of the multicomponent laminar boundary layer by an integral matrix method.
Nonsimilar solution to complex boundary layer problems, using matrix concept to integral relations via Taylor series expansion of parameters
Theory of laminar flames in stagnation flows.
Parallel porous wall burner for studying premixed and diffusion flames in stagnation flows
Laminar flow of a slightly viscous incompressible fluid that issues from a slit and passes over a flat plate
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A Determination of the Laminar-, Transitional-, and Turbulent-boundary-layer Temperature-recovery Factors on a Flat Plate in Supersonic Flow
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Interferometer Corrections and Measurements of Laminar Boundary Layers in Supersonic Stream
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Experimental Investigation of Localized Regions of Laminar-boundary-layer Separation
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Tables of exact laminar-boundary-layer solutions when the wall is porous and fluid properties are variable
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Study of the Pressure Rise Across Shock Waves Required to Separate Laminar and Turbulent Boundary Layers
Results are presented of a dimensional study and an experimental investigation of the pressure rise across a shock wave which causes separation of the boundary layer on a flat plate. The experimental part of the investigation was conducted at a Mach number of 3.03 for a Reynolds number range of 2 x 10 (sup) 6 to 19 x 10 (sup) 6. The available experimental data are compared with the predictions of the present study, and the significance of the results obtained is discussed relative to certain practical design problems.
Effect of thermal properties on laminar-boundary-layer characteristics
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Exact solutions of laminar-boundary-layer equations with constant property values for porous wall with variable temperature
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A Flight Investigation of the Boundary Layer Characteristics and Profile Drag of the NACA 35-215 Laminar-Flow Airfoil at High Reynolds Numbers
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The solution of the laminar-boundary-layer equation for the flat plate for velocity and temperature fields for variable physical properties and for the diffusion field at high concentration
In connection with Pohlhausen's solution for the temperature field on the flat plate, a series of formulas were indicated by means of which the velocity and temperature field for variable physical characteristics can be computed by an integral equation and an iteration method based on it. With it, the following cases were solved: On the assumption that the viscosity simply varies with the temperature while the other fluid properties remain constant, the velocity and temperature field on the heated and cooled plate, respectively, was computed at the Prandtl numbers 12.5 and 100 (viscous fluids). A closer study of these two cases resulted in general relations: The calculations for a gas of Pr number 0.7 (air) were conducted on the assumption that all fluid properties vary with the temperature, and the velocities are low enough for the heat of friction to be discounted. The result was a thickening of the boundary layers, but no appreciable modification in shearing stress or heat-transfer coefficient.
The AEDC 10-Deg Cone Wind Tunnel/Flight Laminar-Turbulent Correlation Program (Invited Historical)
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The AEDC 10-Deg Cone Wind Tunnel/Flight Laminar-Turbulent Correlation Program
The AEDC 10-Deg Cone Program stands as a historical tunnel/flight correlation program in which a simple standard calibration body (a sharp, smooth, slender 10-deg included-angle cone) was used for correlation of wind tunnel flow quality and Reynolds number effects in 23 major wind tunnels. The investigation, initiated by the USAF at AEDC, was conducted in the 1970’s and included participation by NASA, the Navy, the United Kingdom, France, the Netherlands, and Industry. The flight test was performed at NASA/DFRC (now AFRC) at Edwards AFB on a NASA F-15 A aircraft to Mach 2.0. Testing in the wind tunnels was from Mach 0.2 to 5.5. This program produced an extensive database.