9 research outputs found
Effects of Mach number and wall-temperature ratio on turbulent heat transfer at Mach numbers from 3 to 5
Mode of access: Internet
A Comparative Study of Weights and Sizes of Flat-plate Exhaust-gas-to-air Heat Exchangers with and Without Fins
The effect of fluid injection on the compressible turbulent boundary layer : the effect of skin friction of air injected into the boundary layer of a cone at M = 2.7
A Determination of the Laminar-, Transitional-, and Turbulent-boundary-layer Temperature-recovery Factors on a Flat Plate in Supersonic Flow
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NACA Technical Notes
Note presenting heat-transfer data evaluated from temperature time histories on a cooled cylindrical model with a cone-shaped nose and with turbulent flow at Mach numbers 3.00, 3.44, 4.08, 4.56, and 5.04. The experimental data were compared with calculated values using a modified Reynolds analogy between skin friction and heat transfer. Results regarding the air flow and temperature-distribution results and heat-transfer results are provided
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NACA Technical Notes
Report presenting flight testing to investigate the temperature gradients in the wing structure of a typical high-speed fighter airplane caused by rapid changes in surface temperatures. Reports were carried out using dive testing and measured at multiple points on the airplane
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NACA Technical Notes
Note presenting analytical comparisons of weights and volumes for flat-plate heat exchangers with the same calculated thermal output and friction pressure drop for three different fin configurations, including no fins, fins in both the air and exhaust gas passages, and fins in the air passages only. Two different heat exchangers were used and compared with predicted weights and volumes
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NACA Research Memorandums
Report presenting data from which the effects of transpiration air flow on average skin-friction coefficients and pressure drag of a conical model were evaluated. The model consisted of a truncated porous nose cone with a solid ogival nose section. Results regarding the pressure distribution, base pressure drag, average skin-friction coefficients, effects of transpiration air, and comparison with theory
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NACA Technical Notes
Report presenting wind-tunnel testing to determine the temperature-recovery factors for laminar, transitional, and turbulent boundary layers on a flat plate