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  • 1
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    Unknown
    Hamilton Standard Q-fan demonstrator dynamic pitch change test program, volume 1 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests of a full scale variable pitch fan engine to obtain data on the structural characteristics, response times, and fan/core engine compatibility during transient changes in blade angle, fan rpm, and engine power is reported. Steady state reverse thrust tests with a take off nozzle configuration were also conducted. The 1.4 meter diameter, 13 bladed controllable pitch fan was driven by a T55 L 11A engine with power and blade angle coordinated by a digital computer. The tests demonstrated an ability to change from full forward thrust to reverse thrust in less than one (1) second. Reverse thrust was effected through feather and through flat pitch; structural characteristics and engine/fan compatibility were within satisfactory limits.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134861 , HSER-6700-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Hamilton Standard Q-fan demonstrator dynamic pitch change test program, volume 2 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see vol. 1.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134862 , HSER-6700-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic design and performance testing of an advanced 30 deg swept, eight bladed propeller at Mach numbers from 0.2 to 0.85 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The increased emphasis on fuel conservation in the world has stimulated a series of studies of both conventional and unconventional propulsion systems for commercial aircraft. Preliminary results from these studies indicate that a fuel saving of from 15 to 28 percent may be realized by the use of an advanced high speed turboprop. The turboprop must be capable of high efficiency at Mach 0.8 above 10.68 km (35,000 ft) altitude if it is to compete with turbofan powered commercial aircraft. An advanced turboprop concept was wind tunnel tested. The model included such concepts as an aerodynamically integrated propeller/nacelle, blade sweep and power (disk) loadings approximately three times higher than conventional propeller designs. The aerodynamic design for the model is discussed. Test results are presented which indicate propeller net efficiencies near 80 percent were obtained at high disk loadings at Mach 0.8.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3047
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Prop-fan airfoil icing characteristics (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An icing test program was carried out during the 1986-87 and 1987-88 icing seasons at the Fluidyne Icing Tunnel. The testing consisted of evaluating the icing characteristics and aerodynamic performance characteristics of two thin, two-dimensional airfoil sections. The two airfoils were a NACA Series 16-203 and a Hamilton Standard PF1-304, 3 and 4 percent thickness-to-chord ratio airfoils, respectively. These airfoils are representative of the thin airfoils currently being evaluated for Prop-Fan propulsion systems. The tests were conducted over a wide range of icing conditions, angles-of-attack, and Mach numbers (0.3 to 0.8).
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AIAA PAPER 89-0753
    Format: text
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    NASA TECHNICAL REPORTS
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