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  • 1
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    STOL propulsion systems (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: The selection and the characteristics of quiet, clean propulsion systems for STOL aircraft are discussed. Engines are evaluated for augmentor wing and externally blown flap STOL aircraft with the engines located both under and over the wings. Some supporting test data are presented. Optimum engines are selected based on achieving the performance, economic, acoustic, and pollution goals presently being considered for future STOL aircraft. The data and results presented were obtained from a number of contracted studies and some supporting NASA inhouse programs, most of which began in early 1972. The contracts include: (1) two aircraft and mission studies, (2) two propulsion system studies, (3) the experimental and analytic work on the augmentor wing, and (4) the experimental programs on Q-Fan. Engines are selected and discussed based on aircraft economics using the direct operating cost as the primary criterion. This cost includes the cost of the crew, fuel, aircraft, and engine maintenance and depreciation.
    Keywords: PROPULSION SYSTEMS
    Type: STOL Technol.; p 475-509
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Status of advanced turboprop technology (1978)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Research is reviewed in the following areas: turboprop powered transport aircraft; wind tunnel aerodynamic and acoustics tests of model propellers; turboprop maintenance; and wind tunnel tests on airframe-turboprop interactions. Continued development of the technology for advanced turboprop transport was emphasized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Res. Center CTOL Transport Technol., 1978; p 139-166
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Reverse-thrust technology for variable-pitch fan propulsion systems (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Tests conducted to develop the technology necessary to meet the unique reverse-thrust performance requirements of a variable pitch fan propulsion system are discussed. The losses and distortion associated with the air entering the fan and core compressor from the rear of the engine, the direction of fan blade pitch rotation for best reverse-thrust aeroacoustic performance, and engine response and operating characteristics during forward- to reverse-thrust transients are among the factors studied. The test results of several scale fan models as well as a full-size variable pitch fan engine are summarized. Results show the following: a flared exhaust nozzle makes a good reverse-thrust inlet; acceptable core inlet duct recovery and distortion levels in reverse flow were demonstrated; adequate thrust levels were achieved; forward- to reverse-thrust response time achieved was better than the goal; thrust and noise levels strongly favor reverse through feather pitch; and finally, flight-type inlets make the establishment of reverse flow more difficult.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 387-402
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Large-scale advanced propfan (LAP) program progress report (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The propfan is an advanced propeller concept which maintains the high efficiencies traditionally associated with conventional propellers at the higher aircraft cruise speeds associated with jet transports. The large-scale advanced propfan (LAP) program extends the research done on 2 ft diameter propfan models to a 9 ft diameter article. The program includes design, fabrication, and testing of both an eight bladed, 9 ft diameter propfan, designated SR-7L, and a 2 ft diameter aeroelastically scaled model, SR-7A. The LAP program is complemented by the propfan test assessment (PTA) program, which takes the large-scale propfan and mates it with a gas generator and gearbox to form a propfan propulsion system and then flight tests this system on the wing of a Gulfstream 2 testbed aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 85-1187
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Empirical expressions for estimating length and weight of axial-flow components of VTOL powerplants (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simplified equations are presented for estimating the length and weight of major powerplant components of VTOL aircraft. The equations were developed from correlations of lift and cruise engine data. Components involved include fan, fan duct, compressor, combustor, turbine, structure, and accessories. Comparisons of actual and calculated total engine weights are included for several representative engines.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-2406 , E-6191
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effect of forward velocity and crosswind on the reverse-thrust performance of a variable-pitch fan engine (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Variable-pitch-fan engines may be attractive for future short-haul aircraft if sufficient reverse thrust is available for aircraft deceleration after touchdown. Thrust reversal is obtained in these engines by changing fan blade pitch about 90 deg, which causes the fan airflow to enter the fan duct nozzle and exhaust through the fan inlet. This capability would eliminate the heavy and costly thrust reverser system required for current fixed-pitch turbofan engines. NASA has, therefore, supported the development of advanced technology for a quiet, clean, high-bypass-ratio turbofan engine for future short-haul aircraft. In connection with this program, tests were conducted to determine the effect of forward velocity and angle of attack on steady-state reverse-thrust performance. Other objectives of the tests were related to the determination of the effect of forward velocity on forward-to-reverse thrust transient performance and the determination of the effectiveness of an overshoot blade angle technique to establish reverse thrust during a transient. The results of the tests are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 79-0105 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Large-scale Advanced Propfan (LAP) program (1985)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The propfan is an advanced propeller concept which maintains the high efficiencies traditionally associated with conventional propellers at the higher aircraft cruise speeds associated with jet transports. The large-scale advanced propfan (LAP) program extends the research done on 2 ft diameter propfan models to a 9 ft diameter article. The program includes design, fabrication, and testing of both an eight bladed, 9 ft diameter propfan, designated SR-7L, and a 2 ft diameter aeroelastically scaled model, SR-7A. The LAP program is complemented by the propfan test assessment (PTA) program, which takes the large-scale propfan and mates it with a gas generator and gearbox to form a propfan propulsion system and then flight tests this system on the wing of a Gulfstream 2 testbed aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-87067 , E-2637 , NAS 1.15:87067 , AIAA PAPER 85-1187 , Joint Propulsion Conf.; Jul 08, 1985 - Jul 10, 1985; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    High-Speed Propeller for Aircraft (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Engine efficiency increased. Propeller blades required to be quite thin and highly swept to minimize compressibility losses and propeller noise during high-speed cruise. Use of 8 or 10 blades with highpropeller-power loading allows overall propeller diameter to be kept relatively small. Area-ruled spinner and integrated nacelle shape reduce compressibility losses in propeller hub region. Finally, large modern turboshaft engine and gearbox provide power to advanced propeller. Fuel savings of 30 to 50 percent over present systems anticipated. Propfan system adaptable to number of applications, such as highspeed (subsonic) business and general-aviation aircraft, and military aircraft including V/STOL.
    Keywords: MACHINERY
    Type: LEW-14241 , NASA Tech Briefs (ISSN 0145-319X); 10; 3; P. 115
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    The NASA high-speed turboprop program (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: NASA's Advanced Turboprop Project is a three-phase effort initiated in 1978 to provide technology readiness for Mach 0.7 to 0.8 turboprop-powered aircraft; with the potential for fuel savings and DOC reductions of up to 30 and 15%, respectively, relative to current in-service aircraft. This paper reviews the status of Phase I in the areas of propeller aeroacoustics, propeller structures, turboprop installed performance, aircraft cabin environment, and turboprop engine and aircraft studies. Current plans to establish large-scale propeller characteristics and to conduct high-speed propeller flight research tests using a modified testbed aircraft are also presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 801120 , Aerospace Congress and Exposition; Oct 13, 1980 - Oct 16, 1980; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    The NASA high-speed turboprop program (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Technology readiness for Mach 0.7 to 0.8 turboprop powered aircraft with the potential for fuel savings and DOC reductions of up to 30 and 15 percent respectively relative to current in-service aircraft is addressed. The areas of propeller aeroacoustics, propeller structures, turboprop installed performance, aircraft cabin environment, and turboprop engine and aircraft studies are emphasized. Large scale propeller characteristics and high speed propeller flight research tests using a modified testbed aircraft are also considered.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81561 , E-452 , Aerospace Congr.; Oct 13, 1980 - Oct 16, 1980; Los Angeles
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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