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Boundary-layer transition at supersonic speeds

Description: "Recent results of the effects of Mach number, stream turbulence, leading-edge geometry, leading-edge sweep, surface temperature, surface finish, pressure gradient, and angle of attack on boundary-layer transition are summarized. Factors that delay transition are nose blunting, surface cooling, and favorable pressure gradient. Leading-edge sweep and excessive surface roughness tend to promote early transition. The effects of leading-edge blunting on two-dimensional surfaces and surface cooling can be predicted adequately by existing theories, at least in the moderate Mach number range" (p. 1).
Date: August 3, 1956
Creator: Low, George M.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Simplified method for calculation of compressible laminar boundary with arbitrary free-stream pressure gradient

Description: Report presenting a simplification of the Karman-Polhausen integral method as applied to compressible laminar boundary layers. The analysis was conducted under the assumptions of a Prandtl number of 1, zero heat transfer, and a linear viscosity-temperature relation.
Date: October 1951
Creator: Low, George M.
Partner: UNT Libraries Government Documents Department

Cooling requirements for stability of laminar boundary layer with small pressure gradient at supersonic speeds

Description: Report presenting the amount of cooling required to stabilize the two-dimensional supersonic laminar boundary layer for all Reynolds numbers for flows with pressure gradients of a magnitude usually encountered over slender aerodynamic shapes. It is determined that small pressure gradients have an appreciable effect on stability.
Date: March 1954
Creator: Low, George M.
Partner: UNT Libraries Government Documents Department

Factors affecting laminar boundary layer measurements in a supersonic steam

Description: Report presenting an investigation of the observed discrepancy at supersonic speeds between theoretical and apparent experimental average flat plate friction-drag coefficients calculated from boundary layer total-pressure surveys. Some of the qualities investigated included the effects of the total-pressure probe, heat transfer through the leading-edge region, change in leading-edge radius and strength of the leading-edge wave, possible early transition to turbulent flow, and the slight streamwise pressure gradient in flat plate flow were investigated for plates with very sharp leading edges.
Date: February 1953
Creator: Blue, Robert E. & Low, George M.
Partner: UNT Libraries Government Documents Department

Temperature distribution in internally heated walls of heat exchangers with noncircular flow passages using coolants with very low Prandtl number

Description: Report presenting a prediction of the magnitude of temperature variation in order to detect the places of highest temperature and to determine the operating temperatures admissible for the material of which the heat exchanger is composed. Results regarding the temperature distribution in triangular passages, temperature distribution in rectangular passages, influence of velocity field on temperature field, and a comparison of Prandtl number 1 solution are provided.
Date: July 1951
Creator: Eckert, E. R. G. & Low, George M.
Partner: UNT Libraries Government Documents Department

Temperature distribution in internally heated walls of heat exchangers composed of nonnuclear flow passages

Description: "In the walls of heat exchangers composed of noncircular passages, the temperature varies in the circumferential direction because of local variations of the heat-transfer coefficients. A prediction of the magnitude of this variation is necessary in order to determine the region of highest temperature and in order to determine the admissible operating temperatures. A method for the determination of these temperature distributions and of the heat-transfer characteristics of a special type of heat exchanger is developed" (p. 383).
Date: October 4, 1950
Creator: Eckert, E. R. G. & Low, George M.
Partner: UNT Libraries Government Documents Department