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  • 1
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    Considerations for stability and control of V/STOL aircraft: A review of AGARD report 577 (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: Revisions which have been made to previous V/STOL handling qualities requirments based on criteria are discussed. A discussion of the pilot's desire for a particular characteristic is given. In addition, data and reference material are provided to back up the proposed criteria to permit the user to understand the limitations of the data on which the criteria are based. A review is included of several controversial areas including pitch control sensitivity, static longitudinal stability, roll control power, roll-yaw cross coupling, and vertical flight path control.
    Keywords: AIRCRAFT
    Type: AGARD Stability and Control te]; 10 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Revisions to V/STOL handling qualities criteria of AGARD report 408 (1972)
    In:  CASI
    Details
    Publication Date: 2012-05-23
    Description: A brief review of selected handling qualities criteria for V/STOL aircraft shows that although a clearer understanding of the requirements for controversial areas such as roll control power, vertical flight path control, and transition is in hand, considerably more research is needed to refine these criteria for operational IFR activity. Because many items interact to influence the pilots' overall impression of the aircraft's behaviour, additional work of a systematic nature must be done to clarify this aspect. A better definition of a gust model which includes discrete gust effects is needed to firm up criteria for both hover and STOL operation.
    Keywords: AIRCRAFT
    Type: AGARD Handling Qualities Criteria; 8 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The XV-15 tilt rotor research aircraft (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The XV-15 tilt rotor has shown good handling qualities in all modes of flight; in the helicopter mode it allows precision hover and agility with low pilot workload. Vibration and noise levels are low; the conversion procedure is easy, with satisfactory acceleration or deceleration. The XV-15 handling demonstrated its potential for many civil and military applications.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The XV-15 tilt rotor research aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The design characteristics of the XV-15 Tilt rotor research aircraft are presented. Particular attention is given to the following: control system; conversion system; and propulsion system. Flight test results are also reported.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-81244 , AVRADCOM-TR-80-A-15 , A-8343
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A review of facilities and test techniques used in low-speed flight. (1968)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Test facilities and techniques for low speed flight problems of aircraft handling qualities, stability, control and performance
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NEW YORK ACADEMY OF SCIENCES, INTERNATIONAL CONGRESS ON SUBSONIC AERONAUTICS; Apr 03, 1967 - Apr 06, 1967; NEW YORK, NY|; ACE(
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Wind tunnel and flight test of the XV-15 Tilt Rotor Research Aircraft (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The XV-15 Tilt Rotor Research Aircraft Project involves design, fabrication, and flight testing of two aircraft. This program is currently in the test phase for concept evaluation and substantiation of design. As part of this evaluation, one of the aircraft was tested in the NASA-Ames 40- by 80-foot wind tunnel. The status of testing to date and some of the results of the wind tunnel and flight tests are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AHS 79-54 , American Helicopter Society, Annual National Forum; May 21, 1979 - May 23, 1979; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    A simple method for estimating minimum autorotative descent rate of single rotor helicopters (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight test results of minimum autorotative descent rate are compared with calculations based on the minimum power required for steady level flight. Empirical correction factors are derived that account for differences in energy dissipation between these two flight conditions. A method is also presented for estimating the minimum power coefficient for level flight for any helicopter for use in the empirical estimation procedure of autorotative descent rate.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-78452 , A-7134
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A piloted simulation study of the effects of controller force gradient in VTOL hovering flight (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A study of the effect of control force gradient on the VTOL visual hovering task was conducted on the NASA-Ames Research Center Six-Degree-of-Freedom Motion Simulator. Lateral control force-gradient characteristics were evaluated in combination with three different types of stabilization systems: An unstabilized (acceleration) system, a rate-stabilized system, and two attitude-stabilized systems. The effects of gust disturbances were included in the control force evaluation for the attitude systems. A force gradient of 1.0 lb/in was within the optimum range for all control systems and conditions evaluated in this study.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-62230
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Dynamic structural aeroelastic stability testing of the XV-15 tilt rotor research aircraft (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: For the past 20 years, a significant effort has been made to understand and predict the structural aeroelastic stability characteristics of the tilt rotor concept. Beginning with the rotor-pylon oscillation of the XV-3 aircraft, the problem was identified and then subjected to a series of theoretical studies, plus model and full-scale wind tunnel tests. From this data base, methods were developed to predict the structural aeroelastic stability characteristics of the XV-15 Tilt Rotor Research Aircraft. The predicted aeroelastic characteristics are examined in light of the major parameters effecting rotor-pylon-wing stability. Flight test techniques used to obtain XV-15 aeroelastic stability are described. Flight test results are summarized and compared to the predicted values. Wind tunnel results are compared to flight test results and correlated with predicted values.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-84293 , A-9081 , NAS 1.15:84293 , USAAVRADCOM-82-A-17
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A Review of Facilities and Test Techniques Used in Low-Speed Flight (1967)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: Flight test facilities and techniques for low speed flight
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TM-X-60088 , INTERN. CONGR. OF SUBSONIC AERON.; Apr 03, 1967 - Apr 06, 1967; NEW YORK
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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