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  • 1
    Electronic Resource
    Electronic Resource
    PERFORMANCE CONSIDERATIONS OF GROUND EFFECT TAKE-OFF AND LANDING (GETOL) TRANSPORT AIRCRAFT (1963)
    Oxford, UK : Blackwell Publishing Ltd
    Annals of the New York Academy of Sciences 107 (1963), S. 0 
    Details
    ISSN: 1749-6632
    Source: Blackwell Publishing Journal Backfiles 1879-2005
    Topics: Natural Sciences in General
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1111/j.1749-6632.1963.tb13290.x
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Investigation of a rotor system incorporating a constant lift tip (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel test of a 16.8 ft. model of a rotor having passively controlled pivotable tips is described. Performance and vibratory hub load data are presented which compare the performance of the rotor with the tips free and fixed. A brief analysis of the experimental findings is included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166361 , NAS 1.26:166361
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    V/STOL tilt rotor aircraft study. Volume 10: Performance and stability test of A 1-14.622 Froude scaled Boeing Vertol Model 222 tilt rotor aircraft (Phase 1) (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel test data obtained from a 1/4.622 Froude scale Boeing Model 222 with a full span, two prop, tilt rotor, powered model in the Boeing V/STOL wind tunnel are reported. Data were taken in transition and cruise flight conditions and include performance, stability and control and blade loads information. The effects of the rotors, tail surfaces and airframe on the performance and stability are isolated as are the effects of the airframe on the rotors.
    Keywords: AIRCRAFT
    Type: NASA-CR-114603 , D222-10053-1-VOL-10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Variable camber rotor study (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Deployment of variable camber concepts on helicopter rotors was analytically assessed. It was determined that variable camber extended the operating range of helicopters provided that the correct compromise can be obtained between performance/loads gains and mechanical complexity. A number of variable camber concepts were reviewed on a two dimensional basis to determine the usefulness of leading edge, trailing edge and overall camber variation schemes. The most powerful method to vary camber was through the trailing edge flaps undergoing relatively small motions (-5 deg to +15 deg). The aerodynamic characteristics of the NASA/Ames A-1 airfoil with 35% and 50% plain trailing edge flaps were determined by means of current subcritical and transonic airfoil design methods and used by rotor performance and loads analysis codes. The most promising variable camber schedule reviewed was a configuration with a 35% plain flap deployment in an on/off mode near the tip of a blade. Preliminary results show approximately 11% reduction in power is possible at 192 knots and a rotor thrust coefficient of 0.09. The potential demonstrated indicates a significant potential for expanding the operating envelope of the helicopter. Further investigation into improving the power saving and defining the improvement in the operational envelope of the helicopter is recommended.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166382 , NAS 1.26:166382 , D210-11938-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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