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  • AIRCRAFT PROPULSION AND POWER  (223)
  • GENERAL
  • 1975-1979  (237)
  • 1960-1964  (59)
  • 1955-1959  (17)
  • 1
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    Full scale upper surface blown flap noise (1975)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A highly noise suppressed TF 34 engine was used to investigate the noise of several powered lift configurations involving upper surface blown (USB) flaps. The configuration variables were nozzle type (i.e. slot and circular with deflector), flap chord length, and flap angle. The results of velocity surveys at both the nozzle exit and the flap trailing edge are also presented and used for correlation of the noise data. Configurations using a long flap design were 4 db quieter than a short flap typical of current trends in USB flap design. The lower noise for the long flap is attributed primarily to the greater velocity decay of the jet at the flap trailing edge. The full-scale data revealed substantially more quadrupole noise in the region near the deflected jet than observed in previous sub-scale tests.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71708 , E-8322 , Natl. Air Transportation Meeting; May 06, 1975 - May 08, 1975; Hartford, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Micro-motor evaluation of specific impulse (1962)
    In:  CASI
    Details
    Publication Date: 2004-10-01
    Keywords: GENERAL
    Type: APL Bull. of the 18th Meeting of the JANAF-ARPA-NASA Solid Propellant Group, Vol. 3; p 51-70
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    External-store drag reduction at transonic and low supersonic Mach numbers by application of Baldwin's moment-of-area rule (1955)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Keywords: GENERAL
    Type: NACA Conf. on Aerodyn. of High Speed Aircraft; p 93-103
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of endwall cooling on secondary flows in turbine stator vanes (1977)
    In:  CASI
    Details
    Publication Date: 2012-05-19
    Description: An experimental investigation was performed to determine the effect of endwall cooling on the secondary flow behavior and the aerodynamic performance of a coreturbine stator vane. The investigation was conducted in a cold-air, full-annular cascade, where three-dimensional effects could be obtained. Two endwall cooling configurations were tested. In the first configuration, the cooling holes were oriented so that the coolant was injected in line with the inviscid streamline direction. In the second configuration, the coolant was injected at an angle of 15 deg to the inviscid streamline direction and oriented toward the vane pressure surface. In both cases the stator vanes were solid and uncooled so that the effect of endwall cooling could be obtained directly. Total-pressure surveys were taken downstream of the stator vanes over a range of cooling flows at the design, mean-radius, critical velocity ratio of 0.778. Changes in the total-pressure contours downstream of the vanes were used to obtain the effect of endwall cooling on the secondary flows in the stator. Comparisons were made between the two cooled-endwall configurations and with the results obtained previously for solid endwalls.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Secondary Flows in Turbomachines; 29 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Propulsion system noise reduction (1975)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The progress in propulsion system noise reduction is reviewed. The noise technology areas discussed include: fan noise; advances in suppression including conventional acoustic treatment, high Mach number inlets, and wing shielding; engine core noise; flap noise from both under-the-wing and over-the-wing powered-lift systems; supersonic jet noise suppression; and the NASA program in noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeron. Propulsion; p 1-63
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Dynamic stability and control characteristics of parawings (1962)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Compilation of Papers Presented to Meeting on Space Vehicle Landing and Recovery Res. and Technol.; 22 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Application of Paragliders to S-1 Booster Recovery for C-1 and C-2 Class Vehicles (1962)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Compilation of Papers Presented to Meeting on Space Vehicle Landing and Recovery Res. and Technol.; 30 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Modeling of premixing-prevaporizing fuel-air mixing passages (1979)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of a computer program for the analytical prediction of the distribution of liquid and vapor fuel in the premixing-prevaporizing passage by the direct injection method is described. The technical approach adopted for this program is to separate the problem into three parts each with its own computer code. These three parts are: calculation of the two-dimensional or axisymmetric air flow; calculation of the three-dimensional fuel droplet evaporation; and calculation of the fuel vapor diffusion. This method of approach is justified because premixing passages operate at lean equivalence ratios. Hence, a weak interaction assumption can be made wherein the airflow can affect the fuel droplet behavior but the fuel droplet behavior does not affect the airflow.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Res. Center Premixed Prevaporized Combustor Technol. Forum; p 57-65
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Cold-air annular-cascade investigation of aerodynamic performance of core-engine-cooled turbine vanes. 2: Pressure surface trailing edge ejection and split trailing edge ejection (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic performance of two trailing edge ejection cooling configurations of a core-engine stator vane were experimentally determined in an ambient inlet-air full-annular cascade where three-dimensional effects could be obtained. The tests were conducted at the design mean-radius ideal aftermixed critical velocity ratio of 0.778. Overall vane aftermixed thermodynamic and primary efficiencies were obtained over a range of coolant flows to about 10 percent of the primary flow at a primary to coolant total temperature ratio of 1.0. The radial variation in efficiency and the circumferential and radial variations in vane-exit total pressure were determined. Comparisons are made with the solid (uncooled) vane.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3369 , E-8566
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Hypersonic research engine project. Phase 2: Aerothermodynamic Integration Model (AIM) test report (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The Hypersonic Research Engine-Aerothermodynamic Integration Model (HRE-AIM) was designed, fabricated, and tested in the Hypersonic Tunnel Facility. The HRE-AIM is described along with its installation in the wind tunnel facility. Test conditions to which the HRE-AIM was subjected and observations made during the tests are discussed. The overall engine performance, component interaction, and ignition limits for the design are evaluated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-132655 , AIRESEARCH-74-10784
    Format: application/pdf
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