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  • Other Sources  (4)
  • Aircraft Design, Testing and Performance
  • Aircraft Propulsion and Power
  • Organic Chemistry
  • 1985-1989  (1)
  • 1955-1959  (3)
  • 1925-1929
  • 1
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    A Preliminary Investigation of the Performance of a Short-length Turbojet Combustor Using Vaporized Hydrocarbon Fuels (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors. The over-all combustion lengths, for the two configurations were 13.5 and 11.0 inches, approximately one-half the length of the shortest conventional combustors. These short combustors did not provide combustion efficiencies as high as those for conventional combustors at low pressures. However, over the range of combustor-inlet total-pressures expected in aircraft capable of flight at Mach numbers of 2.5 and above, these short combustors gave very high efficiencies. A combustion efficiency of 97 percent was obtained at a combustor-inlet total-pressure of 25.0 inches of mercury absolute, reference velocity of 120 feet per second, and inlet-air total temperature of 1160 deg R. By proportioning the fuel flow between the manifold rows of can combustor elements, control of the combustor-outlet radial total-temperature profile was demonstrated. Combustor totalpressure loss varied from 0.75 percent of the inlet total pressure at isothermal conditions and a reference velocity of 75 feet per second to 5.5 percent at a total-temperature ratio of 1.8 and a reference velocity of 180 feet per second.
    Keywords: Aircraft Propulsion and Power
    Type: NACA-RM-E57J03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Turbine Engines for High-Speed Flight (1958)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This analysis investigates the application of gas turbine engines at a cruise Mach number of 4.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-60935 , NACA-C-8548
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Evaluation of Several Approximate Methods for Calculating the Symmetrical Bending-Moment Response of Flexible Airplanes to Isotropic Atmospheric Turbulence (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Several approximate procedures for calculating the bending-moment response of flexible airplanes to continuous isotropic turbulence are presented and evaluated. The modal methods (the mode-displacement and force-summation methods) and a matrix method (segmented-wing method) are considered. These approximate procedures are applied to a simplified airplane for which an exact solution to the equation of motion can be obtained. The simplified airplane consists of a uniform beam with a concentrated fuselage mass at the center. Airplane motions are limited to vertical rigid-body translation and symmetrical wing bending deflections. Output power spectra of wing bending moments based on the exact transfer-function solutions are used as a basis for the evaluation of the approximate methods. It is shown that the force-summation and the matrix methods give satisfactory accuracy and that the mode-displacement method gives unsatisfactory accuracy.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-MEMO-2-18-59L , L-143
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Transition Flight Experiments on a Swept Wing with Suction (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Flight boundary-layer transition experiments were conducted on a 30 degree swept wing with a perforated leading-edge suction panel. The transition location on the panel was changed by systematically varying the location and amount of suction. Transition from laminar to turbulent flow was due to leading-edge turbulence contamination or crossflow disturbance growth and/or Tollmien-Schlichting disturbance growth, depending on flight condition and suction variation. Amplification factor correlations with transition location were made for various suction configurations using a state-of-the-art linear stability theory which accounts for body and streamline curvature and compressibility.
    Keywords: Aircraft Design, Testing and Performance
    Type: IUTAM Third Symposium on Laminar-Turbulent Transition; Sep 11, 1989 - Sep 15, 1989; Toulouse; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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