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  • Other Sources  (18)
  • PROPULSION SYSTEMS  (11)
  • Fluid Mechanics and Thermodynamics  (7)
  • 1955-1959  (18)
  • 1930-1934
  • 1959  (18)
  • 1
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    THEORETICAL PROBLEMS ASSOCIATED WITH THE VAN ALLEN LAYER, PRESS CONFERENCE (1959)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Keywords: PROPULSION SYSTEMS
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  • 2
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    Longitudinal Laminar Flow Between Cylinders Arranged in Regular Array (1959)
    In:  CASI
    Details
    Publication Date: 2018-06-02
    Description: The increasing complexity of heat transfer and process situations which involve fluid flow has demanded the frequent use of flow passages of unusual geometrical configuration. The present investigation is concerned with one such novel configuration, namely the longitudinal flow between solid cylindrical rods which are arranged in regular array. A schematic diagram of the situation under study. The rods may be located either in triangular or square array. The flow will be taken to be laminar and fully developed. The aim of this analysis is to determine the pressure drop, shear stress, and velocity-distribution characteristics of the system. The starting point of this study is the basic law of momentum conservation. The resulting differential equation has been solved in an approximate, but almost exact, manner by the use of truncated trigonometric series. Results are obtained over a wide range of porosity values for both the triangular and square arrays. Heat transfer has not been considered. The configuration under investigation has potential application in compact heat exchangers for nuclear reactors and other situations. Further the results should also be of interest in the theory of flow through unconsolidated porous beds (ia, 9a). The only related analytical work known to the authors is that of Emersleben (S), who considered only the square array. His rather involved solution, based on complex zeta functions, appears to be valid only at high porosities. Experiments covering a porosity range of 0.093 to 0.984 have been made by Sullivan (4) using parallel-oriented fibers, most of the tests being for fibers in random array. These previous investigations will be compared with the present theory in a later section.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIChE Journal; Volume 5; No. 3; 325-330
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  • 3
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    Some design principles for turbojet combustors operating on boron-containing fuels (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Design techniques and problems in combustors of turbojet engines operating on boron-containing fuels
    Keywords: PROPULSION SYSTEMS
    Type: NASA-MEMO-6-3-59E
    Format: application/pdf
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  • 4
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    Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Performance characteristics and efficiency determined for air cooled turbojet engine suitable for supersonic speed flight
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-148
    Format: application/pdf
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  • 5
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    TRAPPED AND COSMIC RADIATION MEASUREMENTS FROM EXPLORER VI (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-10
    Keywords: PROPULSION SYSTEMS
    Type: EFINS-59-73
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  • 6
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    Experimental performance of liquid hydrogen and liquid fluorine in regeneratively cooled rocket engines (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Performance of liquid hydrogen-fluorine propellant combination in regeneratively cooled rocket engine
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-87
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  • 7
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    Investigation of small-scale hydrazine- fluorine injectors (1959)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Performance tests of shower-head, triplet, and like-on-like liquid hydrazine-fluorine injectors in uncooled rocket engine
    Keywords: PROPULSION SYSTEMS
    Type: NASA-MEMO-1-23-59E
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  • 8
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    Use of a Theoretical Flow Model to Correlate Data for Film Cooling or Heating an Adiabatic Wall by Tangential Injection of Gases of Different Fluid Properties (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-130
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  • 9
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    Experimental investigation of the partial- admission performance characteristics of a single-stage Mach 2 supersonic turbine (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Partial admission performance characteristics of single stage supersonic turbine
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-80
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  • 10
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    Altitude performance of a full-scale high-temperature turbojet engine using pentaborane fuel and HEF-2 (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simulated altitude performance of full scale, high temperature turbojet engine using pentaborane and HEF-2 fuel
    Keywords: PROPULSION SYSTEMS
    Type: NASA-MEMO-12-31-58E
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  • 11
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    Design and Experimental Investigation of a High-weight-flow Low-pressure-ratio Turbine (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance characteristics of high-weight flow, low pressure ratio, single stage turbine rotor and stator blades
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-6
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  • 12
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    Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Previous work on turbulent heat transfer and flow in tubes was generalized and applied to flow in non-circular passages of equilateral triangular and square cross section. Expressions for eddy diffusivity that had been verified for flow and heat transfer in tubes were assumed to apply in general along lines normal to a wall. Velocity distributions, wall shear-stress distributions, and friction factors, as well as wall heat-transfer distributions, wall temperature distributions, and average heat-transfer coefficients were calculated. In addition, results from a previous analysis for axial flow between rods were compared with new experimental data. For calculating wall temperature distributions, uniform heat generation in the passage wall and uniform heat transfer at the outer surface were assumed. The application of the results is restricted to moderately small peripheral wall temperature variations. Calculations were made for Reynolds numbers from 20,000 to 900,000 and Prandtl numbers from 0.73 to 300. Results show that velocities, shear stresses, and heat transfer in the region near the corner were lower than average values and were zero at the corner. Friction factors and average Nusselt numbers were lower than in a tube.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TR-R-31
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  • 13
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    Van Allen Discovery Most Important (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The first step toward the exploration of space occurred approximately 22 months ago as a part of the International Geophysical Year. In the short interval since October, 1957, the new tools of research, the satellite and the space rocket, have produced two unexpected results of fundamental scientific importance. First, instruments placed in the Explorer satellites by James A. Van Allen have revealed the existence of layers of energetic particles in the outer atmosphere. This discovery constitutes the most significant research achievement of the IGY satellite program. The layers may provide the explanation for the aurora and other geophysical phenomena, and they will also influence the design of vehicles for manned space flight, whose occupants must be shielded against their harmful biological effects. Second, the shape of the earth has been determined very accurately with the aid of data from the first Vanguard. As a result of this investigation, we have found that our planet tends toward the shape of a pear, with its stem at the North Pole. This discovery may produce major changes in our ideas on the interior structure of the earth.
    Keywords: PROPULSION SYSTEMS
    Type: Missiles and Rockets
    Format: text
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  • 14
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    Overexpanded Performance of Conical Nozzles with Area Ratios of 6 and 9 With and Without Supersonic External Flow (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: An investigation of the thrust characteristics and internal pressure distributions of two convergent-divergent 15 deg. half-angle exhaust nozzles having area ratios of 6 and 9 was made in the NASA Lewis 10- by 10-foot supersonic wind tunnel. The tests were conducted at free-stream Mach numbers of 0, 2.0, 2.5, 3.0, and 3.5 over a range of nozzle pressure ratios from 3 to 105. Attempts were made to induce separation of the overexpanded nozzle flow using secondary airflow and a wedge. Nozzle flow expansion under all free-stream conditions followed one-dimensional theory until separation from the nozzle wall occurred. In quiescent air the nozzle flow expanded to a pressure approximately one-half the base pressure before separation. When the nozzles were tested with supersonic external flow at the same effective pressure ratios, the nozzle flow separated with negligible expansion below the base pressure. The effect of a supersonic stream on internal nozzle flow separation characteristics was well defined only at a free-stream Mach number of 2.0. Thrust data at supersonic free-stream conditions indicate that only a small percentage of the ideal nozzle thrust will be available at nozzle pressure ratios below design. However, the overexpanded primary nozzle thrust loss was decreased by injecting large quantities of secondary air near the nozzle exit. In most cases no net gain in thrust resulted from secondary-air injection when the nozzle thrust was compared with the ideal thrust of both the primary and secondary airflows.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-83 , E-208
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  • 15
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    Flow Studies of Decelerators at Supersonic Speeds (1959)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Wind tunnel tests recorded the effect of decelerators on flow at various supersonic speeds. Rigid parachute models were tested for the effects of porosity, shroud length, and number of shrouds. Flexible model parachutes were tested for effects of porosity and conical-shaped canopy. Ribbon dive brakes on a missile-shaped body were tested for effect of tension cable type and ribbon flare type. The final test involved a plastic sphere on riser lines.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: L-445
    Format: text
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  • 16
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    A National Space Vehicle Program (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-66794 , HQ-E-DAA-TN57203
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  • 17
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    Measurements of Heat-Transfer and Friction Coefficients for Helium Flowing in a Tube at Surface Temperatures up to 5900 Deg R (1959)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Measurements of average heat transfer and friction coefficients and local heat transfer coefficients were made with helium flowing through electrically heated smooth tubes with length-diameter ratios of 60 and 92 for the following range of conditions: Average surface temperature from 1457 to 4533 R, Reynolds numbe r from 3230 to 60,000, heat flux up to 583,200 Btu per hr per ft2 of heat transfer area, and exit Mach numbe r up to 1.0. The results indicate that, in the turbulent range of Reynolds number, good correlation of the local heat transfer coefficients is obtained when the physical properties and density of helium are evaluated at the surface temperature. The average heat transfer coefficients are best correlated on the basis that the coefficient varies with [1 + (L/D))(sup -0,7)] and that the physical properties and density are evaluated at the surface temperature. The average friction coefficients for the tests with no heat addition are in complete agreement with the Karman-Nikuradse line. The average friction coefficients for heat addition are in poor agreement with the accepted line.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TM-X-57139 , ARS PAPER-850-59 , GRC-E-DAA-TN43549 , American Rocket Society Journal; 30; 9; 830-832|American Rocket Society Semi-Annual Meeting; Jun 08, 1959 - Jun 11, 1959; San Diego, CA; United States
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  • 18
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    Scientists at Space Agency Seminar Compare Views on Composition and Origin of Van Allen Radiation Layer (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: No abstract available
    Keywords: PROPULSION SYSTEMS
    Type: Science; 129; 3355; 1012-1013
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