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  • Weitere Quellen  (33)
  • Aircraft Propulsion and Power  (15)
  • FLUID MECHANICS AND HEAT TRANSFER  (10)
  • AERODYNAMICS  (8)
  • Inorganic Chemistry
  • 42.75
  • 1950-1954  (33)
  • 1953  (20)
  • 1950  (13)
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  • 1950-1954  (33)
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  • 1
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    NACA Conference on Aerodynamics of High- speed Aircraft A compilation of the papers presented (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-29
    Beschreibung: Conference on aerodynamics of high speed aircraft
    Schlagwort(e): AERODYNAMICS
    Materialart: NASA-TM-X-57121
    Format: application/pdf
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  • 2
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    Drag measurements at low lift of a four- nacelle airplane configuration having a longitudinal distribution of cross-sectional area conductive to low transonic drag rise (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-05-23
    Beschreibung: Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-RM-L53E29
    Format: application/pdf
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  • 3
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    A method for calculating the lift and center of pressure of wing-body-tail combinations at subsonic, transonic, and supersonic speeds (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-RM-A53G08
    Format: application/pdf
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  • 4
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    Analogy Between Mass and Heat Transfer with Turbulent Flow (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An analysis of combined heat and mass transfer from a flat plate has been made in terms of Prandtl t s simplified physical concept of the turbulent boundary layer. The results of the analysis show that for conditions of reasonably small heat and mass transfer, the ratio of the mass-and heat-transfer coefficients is dependent on the Reynolds number of the boundary layer, the Prandtl number of the medium of diffusion, and the Schmidt number of the diffusing fluid in the medium of diffusion. For the particular case of water evaporating into air, the ratio of mass-transfer coefficient to heat-transfer coefficient is found to be slightly greater than unity.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-3045
    Format: application/pdf
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  • 5
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    Impingement of Water Droplets on a Cylinder in an Incompressible Flow Field and Evaluation of Rotating Multicylinder Method for Measurement of Droplet-Size Distribution, Volume-Median Droplet-Size, and Liquid-Water Content in Clouds (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-2904
    Format: application/pdf
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  • 6
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    Impingement of cloud droplets on aerodynamic bodies as affected by compressibility of air flow around the body (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-2903
    Format: application/pdf
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  • 7
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    Analytical Investigation of Icing Limit for Diamond-Shaped Airfoil in Transonic and Supersonic Flow (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-TN-2861
    Format: application/pdf
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  • 8
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    De-icing and runback characteristics of three cyclic electric, external de-icing boots employing chordwise shedding (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-RM-E53C26
    Format: application/pdf
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  • 9
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    Effect of Ice and Frost Formations on Drag of NACA 65(sub 1) -212 Airfoil for Various Modes of Thermal Ice Protection (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The effects of primary and. runback icing and frost formations on the drag of an 8-foot-chord NACA 651-212 airfoil section were investigated over a range of angles of attack from 20 to 80 and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.25 to 1.4 grams per cubic meter and datum air temperatures of -30 to 30 F. The results showed that glaze-ice formations, either primary or runback, on the upper surface near the leading edge of the airfoil caused large and rapid increases in drag, especially at datum air temperatures approaching 32 F and in the presence of high rates of water catch. Ice formations at lower temperatures (rime ice) did not appreciably increase the drag coefficient over the initial (standard roughness) drag coefficient. Cyclic de-icing of the primary Ice formations on the airfoil leading-edge section permitted the drag coefficient to return almost to the bare airfoil drag value. Runback icing on the lower surface did not present a serious drag problem except when heavy spanwise ridges of runback ice occurred aft of the heatable area. Frost formations caused rapid and large increases in drag with incipient stalling of the airfoil.
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-TN-2962
    Format: application/pdf
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  • 10
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    Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 40 The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures.. In general, the results showed that rotation will increase the convective heat transfer from a spinner, especially in the turbulent-flow regions. Rotation of the spinner at 1200 rpm and at a free-stream velocity of 275 miles per hour increased the Nusselt number parameter in the turbulent-flow region by 32 percent over that obtained with a stationary spinner; whereas in the nose region, where the flow was laminar, an increase of only 18 percent was observed. Transition from laminar to turbulent flow occurred over a large range of Reynolds numbers primarily because of surface roughness of the spinner. Operation at an angle of attack of 40 had only small effects on the local convective heat transfer for the model studied.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-RM-E53F02
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  • 11
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    A Method for Rapid Determination of the Icing Limit of a Body in Terms of the Stream Conditions (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The effects of existing frictional heating were analyzed to determine the conditions under which ice formations on aircraft surfaces can be prevented. A method is presented for rapidly determining by means of charts the combination of-Mach number, altitude, and stream temperature which will maintain an ice-free surface in an icing cloud. The method can be applied to both subsonic and supersonic flow. The charts presented are for Mach numbers up to 1.8 and pressure altitudes from sea level to 45,000 feet.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-2914
    Format: application/pdf
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  • 12
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    A Method for Determining Cloud-Droplet Impingement on Swept Wings (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The general effect of wing sweep on cloud-droplet trajectories about swept wings of high aspect ratio moving at subsonic speeds is discussed. A method of computing droplet trajectories about yawed cylinders and swept wings is presented, and illustrative droplet trajectories are computed. A method of extending two-dimensional calculations of droplet impingement on nonswept wings to swept wings is presented. It is shown that the extent of impingement of cloud droplets on an airfoil surface, the total rate of collection of water, and the local rate of impingement per unit area of airfoil surface can be found for a swept wing from two-dimensional data for a nonswept wing. The impingement on a swept wing is obtained from impingement data for a nonswept airfoil section which is the same as the section in the normal plane of the swept wing by calculating all dimensionless parameters with respect to flow conditions in the normal plane of the swept wing.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-2931
    Format: application/pdf
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  • 13
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    Impingement of Droplets in 90 deg Elbows with Potential Flow (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: Trajectories were determined for droplets in air flowing through 90 deg elbows especially designed for two-dimensional potential motion with low pressure losses. The elbows were established by selecting as walls of each elbow two streamlines of the flow field produced by a complex potential function that establishes a two-dimensional flow around a 90 deg bend. An unlimited number of elbows with slightly different shapes can be established by selecting different pairs of streamlines as walls. The elbows produced by the complex potential function selected are suitable for use in aircraft air-intake ducts. The droplet impingement data derived from the trajectories are presented along with equations in such a manner that the collection efficiency, the area, the rate, and the distribution of droplet impingement can be determined for any elbow defined by any pair of streamlines within a portion of the flow field established by the complex potential function. Coordinates for some typical streamlines of the flow field and velocity components for several points along these streamlines are presented in tabular form.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-2999
    Format: application/pdf
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  • 14
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    Impingement of Water Droplets on NACA 65A004 Airfoil and Effect of Change in Airfoil Thickness from 12 to 4 Percent at 4 deg Angle of Attack (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: The trajectories of droplets in the air flowing past an NACA 65A004 a irfoil at an angle of attack of 4 deg were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. The effect of a change in airfoil thickness from 12 to 4 percent at 4 deg angle of attack is presented by comparing the impingement calculations for the NACA 65A004 airfoil with those for the NACA 65(sub 1)-208 and 65(sub 1)-212 airfoils. The rearward limit of impingement on the upper surface decreases as the airfoil thickness decreases. The rearward limit of impingement on the lower surface increases with a decrease in airfoil t hickness. The total water intercepted decreases as the airfoil thickness is decreased.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-3047
    Format: application/pdf
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  • 15
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    Investigation of Aerodynamic and Icing Characteristics of a Flush Alternate Inlet Induction System Air Scoop (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet. The investigation was made over a range of mass-air- flow ratios of 0 to 0.8, angles of attack of 0 and 4 deg airspeeds of 150 to 270 miles per hour, air temperatures of 0 and 25 F various liquid-water contents, and droplet sizes. The ram inlet gave good pressure recovery in both clear air and icing but rapid blockage of the top-deck screen occurred during icing. The flush alternate inlet had poor pressure recovery in both clear air and icing. The greatest decreases in the alternate-inlet pressure recovery were obtained at icing conditions of low air temperature and high liquid-water content. No serious screen icing was observed with the alternate inlet. Pressure and temperature distributions on the carburetor top deck were determined using the preheat-air supply with the preheat- and alternate-inlet doors in various positions. No screen icing occurred when the preheat-air system was operated in combination with alternate-inlet air flow.
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-RM-E53E07
    Format: application/pdf
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  • 16
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    Preliminary Evaluation of Turbine Performance with Variable-Area Turbine Nozzles in a Turbojet Engine (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-09-20
    Beschreibung: The performance of a two-stage turbine with variable-area first-stage turbine nozzles was determined in the NACA Lewis altitude wind tunnel over a range of simulated altitudes from 15,000 to 44,000 feet and engine speeds from 50 to 100 percent of rated speed. The variable-area turbine nozzles used in this investigation were primarily a test device for compressor research purposes and were not necessarily of optimum aerodynamic design. The results of this investigation are indicative of effects of turbine-nozzle-area variation on turbine performance within the operating range allowed by the engine. The variable-area turbine nozzles were found to be mechanically reliable and to have negligible leakage losses. Increasing the turbine-nozzle-throat area from 1.15 to 1.67 square feet increased the corrected turbine gas flow or effective turbine nozzle area about 10 percent. At a given corrected turbine speed and turbine pressure ratio, changing the turbine nozzle area from 1.30 to 1. 67 square feet lowered the turbine efficiency 3 or 4 percent. The effect of increasing the turbine nozzle area from 1.15 to 1.67 square feet (decreasing the turning angle about 7 1/2 degrees) would be to lower the turbine efficiency about 5 or 6 percent.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E52J20
    Format: application/pdf
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  • 17
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    Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: The performance of a 13-stage development comressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised to favor part-speed performance,
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE53D17
    Format: application/pdf
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  • 18
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    Altitude Performance and Operational Characteristics of YJ71-A-7 Turbojet Engine (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: Altitude performance of a YJ71-A-7 turbojet engine, with afterburner inoperative, was determined in the NACA Lewis altitude wind tunnel over a wide range of flight conditions. Engine speed and exhaust-nozzle area were controlled independently during this investigation. The variation of corrected values of air flow, net thrust, and fuel flow with corrected engine speed was not defined by a single curve with changes in altitude at given flight Mach number. Changes in altitude had very little effect on minimum specific fuel consumption at altitudes up to 45,000 feet. There is one exhaust-nozzle schedule that is nearly optimum for all flight conditions. Performance calculated from pumping characteristics agreed with experimental values and can therefore be used to extend engine performance data.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-E53E13
    Format: application/pdf
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  • 19
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    Preliminary Transient Performance Data on the J73 Turbojet Engine. II - Altitude, 35,000 Feet (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits encountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engine performance parameters with changes in engine fuel flow. The data presented in this report are for step changes in fuel flow at an altitude of 35,000 feet, at flight Mach numbers of 0.3, 0.8, and 1.2, and at several engine-inlet temperatures,
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE53F29
    Format: application/pdf
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  • 20
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    Preliminary Transient Performance Data on the J73 Turbojet Engine (1953)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits enc ountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engi ne parameters with changes in engine fuel flow. The data presented in this report are for step and ramp changes in fuel flow at an altitude of 45,000 feet and flight Mach numbers of 0 and 0.8.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE53F30
    Format: application/pdf
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  • 21
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    Relation Between Inflammables and Ignition Sources in Aircraft Environments (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: A literature survey was conducted to determine the relation between aircraft ignition sources and inflammables. Available literature applicable to the problem of aircraft fire hazards is analyzed and, discussed herein. Data pertaining to the effect of many variables on ignition temperatures, minimum ignition pressures, and minimum spark-ignition energies of inflammables, quenching distances of electrode configurations, and size of openings incapable of flame propagation are presented and discussed. The ignition temperatures and the limits of inflammability of gasoline in air in different test environments, and the minimum ignition pressure and the minimum size of openings for flame propagation of gasoline - air mixtures are included. Inerting of gasoline - air mixtures is discussed.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-TN-2227
    Format: application/pdf
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  • 22
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    Investigation of the NACA 4-(3)(8)-045 Two-blade Propellers at Forward Mach Numbers to 0.725 to Determine the Effects of Compressibility and Solidity on Performance (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: As part of a general investigation of propellers at high forward speeds, tests of two 2-blade propellers having the NACA 4-(3)(8)-03 and NACA 4-(3)(8)-45 blade designs have been made in the Langley 8-foot high-speed tunnel through a range of blade angle from 20 degrees to 60 degrees for forward Mach numbers from 0.165 to 0.725 to establish in detail the changes in propeller characteristics due to compressibility effects. These propellers differed primarily only in blade solidity, one propeller having 50 percent and more solidity than the other. Serious losses in propeller efficiency were found as the propeller tip Mach number exceeded 0.91, irrespective of forward speed or blade angle. The magnitude of the efficiency losses varied from 9 percent to 22 percent per 0.1 increase in tip Mach number above the critical value. The range of advance ratio for peak efficiency decreased markedly with increase of forward speed. The general form of the changes in thrust and power coefficients was found to be similar to the changes in airfoil lift coefficient with changes in Mach number. Efficiency losses due to compressibility effects decreased with increase of blade width. The results indicated that the high level of propeller efficiency obtained at low speeds could be maintained to forward sea-level speeds exceeding 500 miles per hour.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-TR-999
    Format: application/pdf
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  • 23
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    The Supersonic Axial-Flow Compressor (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation has been made to explore the possibilities of axial-flow compressors operating with supersonic velocities into the blade rows. Preliminary calculations showed that very high pressure ratios across a stage, together with somewhat increased mass flows, were apparently possible with compressors which decelerated air through the speed of sound in their blading. The first phase of the investigation was the development of efficient supersonic diffusers to decelerate air through the speed of sound. The present report is largely a general discussion of some of the essential aerodynamics of single-stage supersonic axial-flow compressors. As an approach to the study of supersonic compressors, three possible velocity diagrams are discussed briefly. Because of the encouraging results of this study, an experimental single-stage supersonic compressor has been constructed and tested in Freon-12. In this compressor, air decelerates through the speed of sound in the rotor blading and enters the stators at subsonic speeds. A pressure ratio of about 1.8 at an efficiency of about 80 percent has been obtained.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-TR-974 , NACA-ACR-L6D02 , NACA-AR-36
    Format: application/pdf
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  • 24
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    Penetration of Air Jets Issuing from Circular, Square, and Elliptical Orifices Directed Perpendicularly to an Air Stream (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An experimental investigation was conducted to determine the penetration of air jets d.irected perpendicularlY to an air stream. Jets Issuing from circular, square, and. elliptical orifices were investigated. and. the jet penetration at a position downstream of the orifice was determined- as a function of jet density, jet velocity, air-stream d.enaity, air-stream velocity, effective jet diameter, and. orifice flow coeffIcient. The jet penetrations were determined for nearly constant values of air-stream density at three tunnel-air velocities arid for a large range of Jet velocities and. densities. The results were correlated in terms of dimensionless parameters and the penetrations of the various shapes were compared. Greater penetration was obtained. with the square orifices and the elliptical orifices having an axis ratio of 4:1 at low tunnel-air velocities and low jet pressures than for the other orifices investigated. The square orifices gave the best penetrations at the higher values of tunnel-air velocity and jet total pressure.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-TN-2019
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  • 25
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    Investigation of Power Requirements for Ice Prevention and Cyclical De-Icing of Inlet Guide Vanes with Internal Electric Heaters (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-28
    Beschreibung: An investigation was conducted to determine the electric power requirements necessary for ice protection of inlet guide vanes by continuous heating and by cyclical de-icing. Data are presented to show the effect of ambient-air temperature, liquid-water content, air velocity, heat-on period, and cycle times on the power requirements for these two methods of ice protection. The results showed that for a hypothetical engine using 28 inlet guide vanes under similar icing conditions, cyclical de-icing can provide a total power saving as high as 79 percent over that required for continuous heating. Heat-on periods in the order of 10 seconds with a cycle ratio of about 1:7 resulted in the best over-all performance with respect to total power requirements and aerodynamic losses during the heat-off period. Power requirements reported herein may be reduced by as much as 25 percent by achieving a more uniform surface-temperature distribution. A parameter in terms of engine mass flow, vane size, vane surface temperature, and the icing conditions ahead of the inlet guide vanes.was developed by which an extension of the experimental data to icing conditions and inlet guide vanes, other than those investigated was possible.
    Schlagwort(e): FLUID MECHANICS AND HEAT TRANSFER
    Materialart: NACA-RM-E50H29
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  • 26
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    The spanwise distribution of lift for minimum induced drag of wings having a given lift and a given bending moment (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-06-27
    Beschreibung: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems. Expressions for the minimum drag and the corresponding spanwise load distributions are also given for the case in which the lift and the bending moment about the wing root are fixed while the span is allowed to vary. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span as compared with results for an elliptically loaded wing having the same total lift and bending moment.
    Schlagwort(e): AERODYNAMICS
    Materialart: NACA-TN-2249 , Collected Works of Robert T. Jones; p 539-556
    Format: application/pdf
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  • 27
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    Theoretical Investigations on the Efficiency and the Conditions for the Realization of Jet Engines (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-08-16
    Beschreibung: Contents: Preliminary notes on the efficiency of propulsion systems; Part I: Propulsion systems with direct axial reaction rockets and rockets with thrust augmentation; Part II: Helicoidal reaction propulsion systems; Appendix I: Steady flow of viscous gases; Appendix II: On the theory of viscous fluids in nozzles; and Appendix III: On the thrusts augmenters, and particularly of gas augmenters
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-TM-1259
    Format: application/pdf
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  • 28
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    Performance of J33-A-27 Turbojet-Engine Compressor (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: An investigation was conducted to determine the effects of water injection on the over-all performance of a modified J33-A-27 turbojet-engine compressor at the design equivalent speed of 11,800 rpm. The water-air ratio by weight was 0.05. With water injection the peak pressure ratio increased 9.0 per- cent, the maximum efficiency decreased 15 percent (actual numerical difference 0.12), and. the maximum total weight flow increased 9.3 percent.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE50F14
    Format: application/pdf
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  • 29
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    Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine. II - Performance of Revised Compressor at Design Equivalent Speed (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The compressor from the XT-46 turbine-propeller engine was revised by removing the last two rows of stator blades and by eliminating the interstage leakage paths described in a previous report. With the revised compressor, the flow choking point shifted upstream into the last rotor-blade row but the maximum weight flow was not increased over that of the original compressor. The flow range of the revised compressor was reduced to about two-thirds that obtained with the original compressor. The later stages of the compressor did not produce the design static-pressure increase probably because of excessive boundary-layer build-up in this region. Measurements obtained in the ninth-stage stator showed that the performance up to this station was promising but that the last three stages of the compressor were limiting the useful operating range of the preceding stages. Some modifications in flow-passage geometry and blade settings are believed to be necessary, however, before any major improvements in over-all compressor performance can be obtained.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE50J10
    Format: application/pdf
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  • 30
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    Summary of Investigations of Mark 25 Aerial-Torpedo Turbine (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: The power plant from a Mark 25 aerial torpedo was investigated both as a two-stage turbine and as a single-stage modified turbine to determine the effect on overall performance of nozzle size and shape, first-stage rotor-blade configuration, and axial nozzle-rotor running clearance. Performance was evaluated in terms of brake, rotor, and blade efficiencies. All the performance data were obtained for inlet total to outlet static pressure ratios of 8, 15 (design), and 20 with inlet conditions maintained constant at 95 pounds per square inch gage and 1000 F for rotor speeds from approximately 6000 to 18,000 rpm.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE50D12
    Format: application/pdf
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  • 31
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    Preliminary Performance Data on General Electric Integrated Electronic Control Operating on J47 RX1-3 Turbojet Engine in NACA Altitude Wind Tunnel (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: Performance data obtained with recording oscillographs are presented to show the transient response of the General Electric Integrated Electronic Control operating on the J47 RXl-3 turbo-Jet engine over a range of altitudes from 10,000 to 45,000 feet and at ram pressure ratios of 1.03 and 1.4. These data represent the performance of the final control configuration developed after an investigation of the engine transient behavior in the NACA altitude wind tunnel. Oscillograph traces of controlled accelerations (throttle bursts),oontrolled decelerations (throttle chops), and controlled altitude starts are presented.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE50G12
    Format: application/pdf
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  • 32
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    Performance of J33-A-27 Turbojet-Engine Compressor (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-11
    Beschreibung: A modified J33-A-27 compressor was operated over a range of equivalent impeller speeds from 6100 to 13,250 rpm in order to obtain the over-all compressor performance. At the equivalent design speed of 11,800 rpm, the maximum efficiency of 0.764 and peak pressure ratio of 4.56 occurred at an equivalent weight flow of 104.07 pounds per second. At the highest equivalent speed (13,250 rpm) a maximum efficiency of 0.711, a maximum equivalent weight flow of 123.00 pounds per second, and a peak pressure ratio of 5.76 were obtained.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE50D25
    Format: application/pdf
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  • 33
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    Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine. I - Preliminary Investigation at 50-,70-, and 100-Percent Design Equivalent Speed (1950)
    In:  CASI
    Details
    Publikationsdatum: 2019-07-12
    Beschreibung: An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations. The station near the entrance section of the combustors indicated a peak pressure ratio of 6.3 at an adiabatic efficiency of 0.63 for a corrected weight flow of 23.1 pounds per second. The other, located one blade-chord downstream of the last stator row, indicated a peak pressure ratio of 6.97 at an adiabatic efficiency of 0.81 for a corrected weight flow of 30.4 pounds per second. The difference in performance obtained at the two stations is attributed to shock waves in the vicinity of the last stator row. These shock waves and the accompanying flow choking, together with interstage circulatory flows, shift the compressor operating curves into the region where surge would normally occur. The inability of the compressor to meet design pressure ratio is probably due to boundary-layer buildup in the last stages, which cause axial velocities greater than design values that, in turn, adversely affect the angles of attack and turning angles in these blade rows.
    Schlagwort(e): Aircraft Propulsion and Power
    Materialart: NACA-RM-SE50E22
    Format: application/pdf
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