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  • Other Sources  (207)
  • AIRCRAFT  (113)
  • MACHINE ELEMENTS AND PROCESSES  (94)
  • 1970-1974  (207)
  • 1965-1969
  • 1950-1954
  • 1935-1939
  • 1973  (115)
  • 1970  (92)
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  • Other Sources  (207)
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  • 1970-1974  (207)
  • 1965-1969
  • 1950-1954
  • 1935-1939
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  • 1
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    Noncontacting devices to indicate deflection and vibration of turbopump internal rotating parts (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The research is reported which was conducted to develop devices for measuring vibrations and deflections of parts, such as impellers, shafts, turbine wheels, and inducers in operating turbopumps. Three devices were developed to the breadboard stage: ultrasonic Doppler transducer, flash X-rays, and light-pipe reflectance. It was found that the X-ray technique is applicable to the shaft assembly and the turbine seal of the J-2 pump, and the light-pipe-reflectance device appears to be ideal for cryogenic pump sections.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-124208
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind tunnel investigation of a large-scale 25 deg swept-wing jet transport model with an external blowing triple-slotted flap (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation has been conducted to determine the aerodynamic characteristics of a large-scale subsonic jet transport model with an externally blown triple-slotted flap. The lift of the model was augmented by the turbofan engine exhaust impingement on the flap surface. The model had a 25 deg swept wing of aspect ratio 7.28 and four turbofan engines. The model was tested with two flap extents. One extended from 0.11 to 1.00 of the wing semispan, and the other extended from 0.11 to 0.75 of the wing semispan with a single-slotted aileron from 0.75 to 1.00 of the wing semispan. The results were obtained for several flap deflections with and without the horizontal tail at gross thrust coefficients from 0 to 4.0. Longitudinal and lateral data are presented with three and four engines operating.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62197
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Acoustic characteristics of a large-scale augmentor wing model at forward speed (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The augmentor wing concept is being studied as one means of attaining short takeoff and landing (STOL) performance in turbofan powered aircraft. Because of the stringent noise requirements for STOL operation, the acoustics of the augmentor wing are undergoing extensive research. The results of a wind tunnel investigation of a large-scale swept augmentor model at forward speed are presented. The augmentor was not acoustically treated, although the compressor supplying the high pressure primary air was treated to allow the measurement of only the augmentor noise. Installing the augmentor flap and shroud on the slot primary nozzle caused the acoustic dependence on jet velocity to change from eighth power to sixth power. Deflecting the augmentor at constant power increased the perceived noise level in the forward quadrant. The effect of airspeed was small. A small aft shift in perceived noise directivity was experienced with no significant change in sound power. Sealing the lower augmentor slot at a flap deflection of 70 deg reduced the perceived noise level in the aft quadrant. The seal prevented noise from propagating through the slot.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2940 , A-4964
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Point and path performance of light aircraft: A review and analysis (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The literature on methods for predicting the performance of light aircraft is reviewed. The methods discussed in the review extend from the classical instantaneous maximum or minimum technique to techniques for generating mathematically optimum flight paths. Classical point performance techniques are shown to be adequate in many cases but their accuracies are compromised by the need to use simple lift, drag, and thrust relations in order to get closed form solutions. Also the investigation of the effect of changes in weight, altitude, configuration, etc. involves many essentially repetitive calculations. Accordingly, computer programs are provided which can fit arbitrary drag polars and power curves with very high precision and which can then use the resulting fits to compute the performance under the assumption that the aircraft is not accelerating.
    Keywords: AIRCRAFT
    Type: NASA-CR-2272
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Some observations of the relationship between film thickness and load in high Hertz pressure sliding elastohydrodynamic contacts. (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: ASME PAPER 73-LUB-D
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Acoustic characteristics of a large-scale wind tunnel model of an upper-surface blown flap transport having two engines (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The upper-surface blown (USB) flap as a powered-lift concept has evolved because of the potential acoustic shielding provided when turbofan engines are installed on a wing upper surface. The results from a wind tunnel investigation of a large-scale USB model powered by two JT15D-1 turbofan engines are-presented. The effects of coanda flap extent and deflection, forward speed, and exhaust nozzle configuration were investigated. To determine the wing shielding the acoustics of a single engine nacelle removed from the model were also measured. Effective shielding occurred in the aft underwing quadrant. In the forward quadrant the shielding of the high frequency noise was counteracted by an increase in the lower frequency wing-exhaust interaction noise. The fuselage provided shielding of the opposite engine noise such that the difference between single and double engine operation was 1.5 PNdB under the wing. The effects of coanda flap deflection and extent, angle of attack, and forward speed were small. Forward speed reduced the perceived noise level (PNL) by reducing the wing-exhaust interaction noise.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62319
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Full-scale wind-tunnel investigation of the static longitudinal and lateral characteristics of a light single-engine airplane (1970)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Full scale wind tunnel investigation of static longitudinal and lateral stability and control characteristics of light single-engine low-wing monoplane
    Keywords: AIRCRAFT
    Type: NASA-TN-D-5700 , L-7012
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A pilot-vehicle systems approach to longitudinal flight director design (1970)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Pilot/vehicle feedback systems with flight director computer for transport aircraft longitudinal control during landing, discussing design by manual control displays theory
    Keywords: AIRCRAFT
    Type: AIAA PAPER 70-1001 , AMERICAN INST. OF AERONAUTICS AND ASTRONAUTICS, GUIDANCE, CONTROL AND FLIGHT MECHANICS CONFERENCE; Aug 17, 1970 - Aug 19, 1970; SANTA BARBARA, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Optical analysis of ball bearing starvation (1970)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Optical measurement of oil film thickness in elastohydrodynamic rolling point contact of ball bearing
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TM-X-52869 , PROPOSED FOR PRESENTATION AT LUBRICATION CONF.; Oct 12, 1970 - Oct 15, 1970; CINCINNATI, OH; UNITED STATES
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    High transonic speed transport aircraft study (1973)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An initial design study of high-transonic-speed transport aircraft has been completed. Five different design concepts were developed. These included fixed swept wing, variable-sweep wing, delta wing, double-fuselage yawed-wing, and single-fuselage yawed-wing aircraft. The boomless supersonic design objectives of range=5560 Km (3000 nmi), payload-18 143 kg (40 000lb), Mach=1.2, and FAR Part 36 aircraft noise levels were achieved by the single-fuselage yawed-wing configuration with a gross weight of 211 828 Kg (467 000 lb). A noise level of 15 EPNdB below FAR Part 36 requirements was obtained with a gross weight increase to 226 796 Kg (500 000 lb). Although wing aeroelastic divergence was a primary design consideration for the yawed-wing concepts, the graphite-epoxy wings of this study were designed by critical gust and maneuver loads rather than by divergence requirements. The transonic nacelle drag is shown to be very sensitive to the nacelle installation. A six-degree-of-freedom dynamic stability analysis indicated that the control coordination and stability augmentation system would require more development than for a symmetrical airplane but is entirely feasible. A three-phase development plan is recommended to establish the full potential of the yawed-wing concept.
    Keywords: AIRCRAFT
    Type: NASA-CR-114658
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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