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  • FLUID MECHANICS AND HEAT TRANSFER  (4)
  • Fluid Mechanics and Heat Transfer  (4)
  • 550 - Earth sciences
  • 1955-1959  (8)
  • 1
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    Interaction Effects Produced by Jet Exhausting Laterally Near Base of Ogive-Cylinder Model in Supersonic Main Stream (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The experimentally determined interaction effects of a side jet exhausting near the base of an ogive-cylinder model are presented and discussed. The interaction force appears to be independent of main-stream Mach number, boundary-layer condition (laminar or turbulent), angle of attack, and forebody length. The ratio of interaction force to jet force is found to be inversely proportional to the square root of the product of jet stagnation-to-free-stream pressure ratio and jet-to-body diameter ratio.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-MEMO-12-5-58W
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  • 2
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    Investigation of Heat Transfer From (1956)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The convective heat transfer from the surface of an ellipsoidal forebody of fineness ratio 3 and 20-inch maximum diameter was investigated in clear air for both stationary and rotating operation over a range of conditions including air speeds up to 240 knots, rotational speeds up to 1200 rpm, and angles of attack of 0 deg, 3 deg, and 6 deg. The results are presented in the form of heat-transfer coefficients and the correlation of Nusselt and Reynolds numbers. Both a uniform surface temperature and a uniform input heater density distribution were used. The experimental results agree well with theoretical predictions for uniform surface temperature distribution. Complete agreement was not obtained with uniform input heat density in the laminar-flow region because of conduction effects. No significant effects of rotation were obtained over the range of airstream and rotational speeds investigated. Operation at angle of attack had only minor effects on the local heat transfer. Transition from laminar to turbulent heat transfer occurred over a wide range of Reynolds numbers. The location of transition depended primarily on surface roughness and pressure and temperature gradients. Limited transient heating data indicate that the variation of surface temperature with time followed closely an exponential relation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-3837
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  • 3
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    Impingement of Cloud Droplets on a Cylinder and Procedure for Measuring Liquid-Water Content and Droplet Sizes in Supercooled Clouds by Rotating Multicylinder Method (1955)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TR-1215
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  • 4
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    Investigation of Heat Transfer from a Stationary and Rotating Conical Forebody (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The convective heat transfer from the surface of a conical forebody having a hemispherical nose, an included angle of approximately 30 deg, and. a maximum diameter of 18.9 inches was investigated in a wind tunnel for both stationary and. rotating operation. The range of test conditions included free-stream velocities up to 400 feet per second, rotational speeds up to 1200 rpm, and. angles of attack of 0 deg and 6 deg. Both a uniform surface temperature and a uniform heater input power density were used. The Nusselt-Reynolds number relations provided good correlation of the heat-transfer data for the complete operating range at 0 deg angle of attack with and without spinner rotation, and for 6deg angle of attack with rotation. Rotational speeds up to 1200 rpm had no apparent effect on the heat-transfer characteristics of the spinner. The results obtained at 6 deg angle of attack with rotation were essentially the same as those obtained at 0 deg angle of attack without rotation. The experimental heat-transfer characteristics in the turbulent flow region were consistently in closer agreement with the results predicted for a two-dimensional body than with those predicted. for a cone. For stationary operation at 60 angle of attack, the measured heat-transfer coefficients in the turbulent flow region were from 6 to 13 percent greater on the lower surface (windward. side) than on the upper surface (sheltered side) for corresponding surface locations. The spinner-nose geometry appeared to cause early boundary-layer transition. Transition was initiated at a fairly constant Reynolds number (based on surface distance from nose) of 8.0 x 10(exp 4). Transition was completed at Reynolds numbers less than 5.0 x 10(exp 5) for all conditions investigated.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-4093
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  • 5
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    Experimental Droplet Impingement on Four Bodies of Revolution (1957)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The rate and. area of cloud droplet impingement on four bodies of revolution were obtained experimentally in the NACA Lewis icing tunnel with a dye-tracer technique. The study included spheres, ellipsoidal forebodies of fineness ratios of 2.5 and 3.0, and a conical forebody of 300 included angle and covered a range of angles of attack from 0? to 60 and rotational speeds up to 1200 rpm. The data were obtained at an airspeed of 157 knots and are correlated by dimensionless impingement parameters. In general, the experimental data show that the local and total impingement rates and impingement limits of bodies of revolution are primarily functions of the modified inertia parameters, the body shape, and fineness ratio. Both the local impingement rate and impingement limits depend upon the angle of attack. Rotation of the bodies had a negligible effect on the impingement characteristics except for an averaging effect at angle of attack. For comparable diameters the bluffer bodies had the largest total impingement efficiency, but the finer and sharper bodies had the largest values of maximum local impingement efficiency and, in most cases, the largest limits of impingement. In most cases, the impingement characteristics were less than those calculated from theoretical trajectories; in general, however, fairly good agreement was obtained between the experimental and theoretical impingement characteristics.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NACA-TN-4092
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  • 6
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    Exploratory Study of Ventilated Flows About Yawed Surface-Piercing Struts (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Reported herein are the results of observations and measurements made in connection with a study of the phenomenon of the development of atmosphere-connected cavities about surface-piercing struts. Conditions for the existence of such ventilated flows which have been derived from the experimental data are presented. In addition, certain broad conclusions pertinent to model testing and full-scale design are reached. Further experimentation to define the inception of ventilation as a function of boundary-layer state or Reynolds number is required.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-MEMO-2-23-59W , C-476
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  • 7
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    Experimental and Theoretical Studies of Axisymmetric Free Jets (1959)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Some experimental and theoretical studies have been made of axisymmetric free jets exhausting from sonic and supersonic nozzles into still air and into supersonic streams with a view toward problems associated with propulsive jets and the investigation of these problems. For jets exhausting into still air, consideration is given to the effects of jet Mach number, nozzle divergence angle, and jet static pressure ratio upon jet structure, jet wavelength, and the shape and curvature of the jet boundary. Studies of the effects of the ratio of specific heats of the jets are included are observations pertaining to jet noise and jet simulation. For jets exhausting into supersonic streams, an attempt has been made to present primarily theoretical certain jet interference effects and in formulating experimental studies. The primary variables considered are jet Mach number, free stream Mach number, jet static pressure ratio, ratio of specific heats of the jet, nozzle exit angle, and boattail angle. The simulation problem and the case of a hypothetical hypersonic vehicle are examined, A few experimental observations are included.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TR-R-6
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  • 8
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    Flight Investigation of the Surface Pressure Distribution and Flow Field Around an Elliptical Spinner (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A flight investigation has been made of the surface pressure distribution and the flow field around a dummy, nonrotating, elliptical spinner over a Mach number range from 0.65 to 0.95, which corresponds to a Reynolds number range from about 1.6 x 10(exp 6) per foot to about 3.9 x 10(exp 6) per foot. The results showed that free-stream conditions were approximated from about 15 to 90 percent of the spinner length, but the local Mach number in the propeller plane varied from about 5 percent less than free stream at a Mach number of 0.65 to about 10 percent less than free stream at a mach number of 0.95.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-MEMO-1-26-59L , L-150
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