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  • Fluid Mechanics and Thermodynamics
  • 2020-2024
  • 1970-1974  (3)
  • 1940-1944  (9)
  • 1971  (3)
  • 1943  (9)
Collection
Keywords
Years
  • 2020-2024
  • 1970-1974  (3)
  • 1940-1944  (9)
Year
  • 1
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    CSM/LM Spacecraft Operational Data Book. Volume 3: Mass Properties Data Book (1971)
    In:  CASI
    Details
    Publication Date: 2019-11-09
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-69016 , SNA-8-D-027-VOL-3-REV-3 , JSC-E-DAA-TN75190
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  • 2
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    Analysis of Free-Flight Laminar, Transitional, and Turbulent Heat-Transfer Results at Free-Stream Mach Numbers Near 20 (Reentry F) (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Laminar, transitional, and turbulent heat-transfer data were measured during a reentry flight at a Mach number of 20 on a 5 deg half-angle cone 3.962 m (13 ft) long with an initial nose tip radius of 0.254 cm (0.1 in.). The free-stream Reynolds number increased during the prime data period from 7.0 x 10(exp 6) to 51.5 x 10(exp 6) per meter (2.1 x 10(exp 6) to 15.7 x 10(exp 6) per foot) and the ratio of wall to total temperature varied from 0.053 to 0.12. The angle of attack was less than 1deg for the prime data period. The experimental laminar and turbulent heating rates are compared with results from existing flat-plate prediction methods. At conditions of minimal tip blunting and angle of attack (above 26.8 km (88 000 ft)), values from a flat-plate laminar method agreed within 20 percent with the laminar data. The Schultz-Grunow skin-friction equation with reference enthalpy; conditions, with the Reynolds number based on distance from the transition location, and with the Colburn Reynolds analogy agreed within 10 percent with the experimental turbuleiit heating data. The Van Driest n skin-friction equation with Reynolds number greater than 10(exp 7) based on distance from the peak heating point and the Colburn Reynolds analogy was also within approximately 10 percent of the experimental turbulent heating data. A data correlation jbf the extent of transition and a simple empirical transition-zone heating correlation were also presented.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-2335 , L-7803
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  • 3
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    Thermal Analysis Methods and Basic Heat-Transfer Data for a Turbulent Heating Flight Experiment at Mach 20 (Reentry F) (1971)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: A heat-transfer experiment was flight conducted on a 5 deg half-angle cone, 396.2 cm (13 ft) in length, as it entered the sensible atmosphere under laminar, transitional, and turbulent boundary-layer conditions at a free-stream Mach number of about 20. Accurate turbulent-heat-transfer data with natural transition were obtained for correlation with theories in regions of simultaneous high Mach number, Reynolds number, enthalpy, and total-to-wall temperature ratio. Temperatures were measured at four depths through the 15.24-mm-thick (0.600-in.) beryllium wall. Experimental heating rates at 20 stations on the cone were determined independently from the outermost temperature measurement and from the temperature measurement at the second depth by a single-thermocouple inverse method and also from the temperature histories at all four depths by an integral method. The thermal data analysis procedure, associated problems, and results are presented herein.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-2282 , L-7520
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  • 4
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    Heat Transfer Through Turbulent Friction Layers (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The "general Prandtl number" Pr(exp 1) - A(sub q)/A Pr, aside from the Reynolds number determines the ratio of turbulent to molecular heat transfer, and the temperature distribution in turbulent friction layers. A(sub q) = exchange coefficient for heat; A = exchange coefficient for momentum transfer. A formula is derived from the equation defining the general Prandtl number which describes the temperature as a function of the velocity. For fully developed thermal boundary layers all questions relating to heat transfer to and from incompressible fluids can be treated in a simple manner if the ratio of the turbulent shear stress to the total stress T(sub t)/T in the layers near the wall is known, and if the A(sub q)/A can be regarded as independent of the distance from the wall. The velocity distribution across a flat smooth channel and deep into the laminar sublayer was measured for isothermal flow to establish the shear stress ratio T(sub t)/T and to extend the universal wall friction law. The values of T(sub t)/T which resulted from these measurements can be approximately represented by a linear function of the velocity in the laminar-turbulent transition zone. The effect of the temperature relationship of the material values on the flow near the wall is briefly analyzed. It was found that the velocity at the laminar boundary (in contrast to the thickness of the laminar layer) is approximately independent of the temperature distribution. The temperature gradient at the wall and the distribution of temperature and heat flow in the turbulent friction layers were calculated on the basis of the data under two equations. The derived formulas and the figures reveal the effects of the Prandtl number, the Reynolds number, the exchange quantities and the temperature relationship of the material values.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1047 , Zeitschrift fuer Angewandte Mathematik und Mechanik; 20; 6; 297-328
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  • 5
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    Heat Transfer and Hydraulic Flow Resistance for Streams of High Velocity (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Problems of hydraulic flow resistance and heat transfer for streams with velocities comparable with acoustic have present great importance for various fields of technical science. Especially, they have great importance for the field of heat transfer in designing and constructing boilers.of the "Velox" type. In this article a description of experiments and their results as regards definition of the laws of heat transfer in differential form for high velocity air streams inside smooth tubes are given.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1054 , Journal of Technical Physics; 9; 9; 808-818
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  • 6
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    Periodic Heat Transfer at Small Pressure Fluctuations (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The effect of cyclic gas pressure variations on the periodic heat transfer at a flat wall is theoretically analyzed and the differential equation describing the process and its solution for relatively. Small pressure fluctuations developed, thus explaining the periodic heat cycle between gas and wall surface. The processes for pure harmonic pressure and temperature oscillations, respectively, in the gas space are described by means of a constant heat transfer coefficient and the equally constant phase angle between the appearance of the maximum values of the pressure and heat flow most conveniently expressed mathematically in the form of a complex heat transfer coefficient. Any cyclic pressure oscillations, can be reduced by Fourier analysis to harmonic oscillations, which result in specific, mutual relationships of heat-transfer coefficients and phase angles for the different harmonics.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1048 , Forschung auf de Gebiete des Ingenieurwesens; 11; 2; 67-75
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  • 7
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    Pressure Distribution in Nonuniform Two-Dimensional Flow (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In an attempt to follow the time rate of change of the processes in turbulent flows by quantitative measurements the measurement of the pressure is often beset with insuperable difficulties for the reason that the speeds and hence the pressures to be measured are often very small. On the other hand, the measurement of very small pressures requires, at least, considerable time, so that the follow-up of periodically varying processes is as goad as impossible. In order to obviate these difficulties a method, suggested by Prof. Prandtl, has been developed by which the pressure distribution is simply determined from the photographic flow picture. This method is described and proved on a worked-out example. It was found that quantitatively very satisfactory results can be achieved.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1039 , Ingenieur-Archives; 6; 1; 34-50
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  • 8
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    Heat Transfer Over the Circumference of a Heated Cylinder in Transverse Flow (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method for recording the local heat-transfer coefficients on bodies in flow was developed. The cylinder surface was kept at constant temperature by the condensation of vapor except for a narrow strip which is heated separately to the same temperature by electricity. The heat-transfer coefficient at each point was determined from the electric heat output and the temperature increase. The distribution of the heat transfer along the circumference of cylinders was recorded over a range of Reynolds numbers of from 5000 to 426,000. The pressure distribution was measured at the same time. At Reynolds numbers up to around 100,000 high maximums of the heat transfer occurred in the forward stagnation point at and on the rear side at 180C, while at around 80 the heat-transfer coefficient on both sides of the cylinder behind the forward stagnation point manifested distinct minimums. Two other maximums occurred at around 115 C behind the forward stagnation point between 170,000 and 426,000. At 426,000 the heat transfer at the location of those maximums was almost twice as great as in the forward stagnation point, and the rear half of the cylinder diffused about 60 percent of the entire heat, The tests are compared with the results of other experimental and theoretical investigations.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1050 , Forschung auf dem Gebiete des Ingenieurwesens; 12; 2; 65-73
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  • 9
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    The Heat Transfer to a Plate in Flow at High Speed (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The heat transfer in the laminar boundary layer of a heated plate in flow at high speed can be obtained by integration of the conventional differential equations of the boundary layer, so long as the material values can be regarded as constant. This premise is fairly well satisfied at speeds up to about twice the sonic speed and at not excessive temperature rise of the heated plate. The general solution of the equation includes Pohlhausen's specific cases of heat transfer to a plate at low speeds and of the plate thermometer. The solution shows that the heat transfer coefficient at high speed must be computed with the same equation as at low speed, when it is referred to the difference of the wall temperature of the heated plate in respect to its "natural temperature." Since this fact follows from the linear structure of the differential equation describing the temperature field, it is equally applicable to the heat transfer in the turbulent boundary layer.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1045 , Forschung; 11; 3; 116-124
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  • 10
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    Turbulent Friction in the Boundary Layer of a Flat Plate in a Two-Dimensional Compressible Flow at High Speeds (1943)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: In the present report an investigation is made on a flat plate in a two-dimensional compressible flow of the effect of compressibility and heating on the turbulent frictional drag coefficient in the boundary layer of an airfoil or wing radiator. The analysis is based on the Prandtl-Karman theory of the turbulent boundary later and the Stodola-Crocco, theorem on the linear relation between the total energy of the flow and its velocity. Formulas are obtained for the velocity distribution and the frictional drag law in a turbulent boundary later with the compressibility effect and heat transfer taken into account. It is found that with increase of compressibility and temperature at full retardation of the flow (the temperature when the velocity of the flow at a given point is reduced to zero in case of an adiabatic process in the gas) at a constant R (sub x), the frictional drag coefficient C (sub f) decreased, both of these factors acting in the same sense.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NACA-TM-1053 , Report of the Central Aero-Hydrodynamical Institute, Moscow; Rept-321
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