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  • 1
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    Simulator evaluation of the flying qualities of externally blown flap and augmentor wing transport configurations (1972)
    In:  CASI
    Details
    Publication Date: 2006-03-27
    Description: Concurrent simulations of powered-lift STOL transport aircraft having either an externally blown flap configuration or an augmentor wing configuration were conducted. The following types of simulators of varying sophistication were used: (1) a simple fixed-base simulation with a simple visual display, (2) a more complex fixed-base simulation using a realistic transport cockpit and a high-quality visual display, and (3) a six-degree-of-freedom motion simulator that had a realistic transport cockpit and a sophisticated visual display. The unaugmented flying qualities determined from these simulations were rated as unacceptable for both the externally blown flap and augmentor wing configurations. The longitudinal, lateral-directional, and single-engine-failure characteristics were rated satisfactory with extensive augmentation, including pitch and roll command systems, flight-path (or speed) augmentation, turn coordination, and effective yaw damping. However, the flare and landing characteristics from any approach glide-path angle in excess of 4 deg were rated as unsatisfactory but acceptable.
    Keywords: AERODYNAMICS
    Type: STOL Technol.; p 157-800
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Simulator study of the low-speed handling qualities of a supersonic cruise arrow-wing transport configuration during approach and landing (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A fixed-based simulator study was conducted to determine the low-speed flight characteristics of an advanced supersonic cruise transport having an arrow wing, a horizontal tail, and four dry turbojets with variable geometry turbines. The primary piloting task was the approach and landing. The statically unstable (longitudinally) subject configuration has unacceptable low-speed handling qualities with no augmentation. Therefore, a hardened stability augmentation system is required to achieve acceptable handling qualities, should the normal operational stability and control augmentation system fail. In order to achieve satisfactory handling qualities, considerable augmentation was required.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Proc. of the SCAR Conf., Part 1; p 215-248
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    ANALYTICAL INVESTIGATION AND PREDICTION OF SPIN AND RECOVERY CHARACTERISTICS OF THE NORTH AMERICAN X-15 AIRPLANE (1960)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Spin and recovery characteristics of north american x-15 aircraft
    Keywords: BIOSCIENCES
    Type: NASA-TM-X-294
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Development of SCR Aircraft takeoff and landing procedures for community noise abatement and their impact on flight safety (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Piloted simulator studies to determine takeoff and landing procedures for a supersonic cruise transport concept that result in predicted community noise levels which meet current Federal Aviation Administration (FAA) standards are discussed. The results indicate that with the use of advanced procedures, the subject simulated aircraft meets the FAA traded noise levels during takeoff and landing utilizing average flight crew skills. The advanced takeoff procedures developed involved violating three of the current Federal Aviation Regulations (FAR) noise test conditions. These were: (1) thrust cutbacks at altitudes below 214 meters (700 ft); (2) thrust cutback level below those presently allowed; and (3) configuration change, other than raising the landing gear. It was not necessary to violate any FAR noise test conditions during landing approach. It was determined that the advanced procedures developed do not compromise flight safety. Automation of some of the aircraft functions reduced pilot workload, and the development of a simple head-up display to assist in the takeoff flight mode proved to be adequate.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Supersonic Cruise Res. 1979, Pt. 1; p 299-333
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Large aircraft handling qualities (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The short period frequency requirements of MIL-F-8785C are applicable to the very large transport aircraft simulated. The large aircraft simulated meet the requirements of NASA CR-159236 for effective time delay and pitch transient peak ratio. However, the requirements of this reference for the effective rise time parameter are believed to be too convservative for very large transport aircraft. Data obtained to date as well as other data indicate that MIL-SPEC requirements for the parameter t(phi=30 degrees) are too conservative for very large transport aircraft. The results of the present study indicate that t(phi=30 degrees) of less than 6 sec should result in ""acceptable'' roll response characteristics, and t(phi=30 degrees) of less than 4.0 sec should result in ""satisfactory'' roll response.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA Aircraft Controls Research, 1983; p 37-50
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Effects of aircraft relative density on spin and recovery characteristics of some current configurations (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Relative density effect on spin and recovery characteristics of aircraft configurations
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-2243
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Simulator study of flight characteristics of a large twin-fuselage cargo transport airplane during approach and landing (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A six degree-of-freedom, ground-based simulator study was conducted to evaluate the low speed flight characteristics of a twin fuselage cargo transport airplane and to compare these characteristics with those of a large, single fuselage (reference) transport configuration which was similar to the Lockheed C-5C airplane. The primary piloting task was the approach and landing. The results indicated that in order to achieve "acceptable' low speed handling qualities on the twin fuselage concept, considerable stability and control augmentation was required, and although the augmented airplane could be landed safely under adverse conditions, the roll performance of the aircraft had to be improved appreciably before the handling qualities were rated as being "satisfactory.' These ground-based simulation results indicated that a value of t sub phi = 30 (time required to bank 30 deg) less than 6 sec should result in "acceptable' roll response characteristics, and when t sub phi = 30 is less than 3.8 sec, "satisfactory' roll response should be attainable on such large and unusually configured aircraft as the subject twin fuselage cargo transport concept.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2183 , L-15505 , NAS 1.60:2183
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Simulator study of flight characteristics of several large, dissimilar, cargo transport airplanes during approach and landing (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A six-degree-of-freedom, ground based simulator study is conducted to evaluate the low-speed flight characteristics of four dissimilar cargo transport airplanes. These characteristics are compared with those of a large, present-day (reference) transport configuration similar to the Lockheed C-5A airplane. The four very large transport concepts evaluated consist of single-fuselage, twin-fuselage, triple-fuselage, and span-loader configurations. The primary piloting task is the approach and landing operation. The results of his study indicate that all four concepts evaluated have unsatisfactory longitudinal and lateral directional low speed flight characteristics and that considerable stability and control augmentation would be required to improve these characteristics (handling qualities) to a satisfactory level. Through the use of rate command/attitude hold augmentation in the pitch and roll axes, and the use of several turn-coordination features, the handling qualities of all four large transports simulated are improved appreciably.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2357 , L-15805 , NAS 1.60:2357
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A simulator study for the development and evaluation of operating procedures on a supersonic cruise research transport to minimize airport-community noise (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Piloted-simulator studies were conducted to determine takeoff and landing operating procedures for a supersonic cruise research transport concept that result in predicted noise levels which meet current Federal Aviation Administration (FAA) certification standards. With the use of standard FAA noise certification test procedures, the subject simulated aircraft did not meet the FAA traded-noise-level standards during takeoff and landing. However, with the use of advanced procedures, this aircraft meets the traded-noise-level standards for flight crews with average skills. The advanced takeoff procedures developed involved violating some of the current Federal Aviation Regulations (FAR), but it was not necessary to violate any FAR noise-test conditions during landing approach. Noise contours were also determined for some of the simulated takeoffs and landings in order to indicate the noise-reduction advantages of using operational procedures other than standard.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA-TP-1742 , L-13881
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Noise and economic characteristics of an advanced blended supersonic transport concept (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Noise and economic characteristics were obtained for an advanced supersonic transport concept that utilized wing body blending, a double bypass variable cycle engine, superplastically formed and diffusion bonded titanium in both the primary and secondary structures, and an alternative interior arrangement that provides increased seating capacity. The configuration has a cruise Mach number of 2.62, provisions for 290 passengers, a mission range of 8.19 Mm (4423 n.mi.), and an average operating cruise lift drag ratio of 9.23. Advanced operating procedures, which have the potential to reduce airport community noise, were explored by using a simulator. Traded jet noise levels of 105.7 and 103.4 EPNdB were obtained by using standard and advanced takeoff operational procedures, respectively. A new method for predicting lateral attenuation was utilized in obtaining these jet noise levels.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TP-2073 , L-15297 , NAS 1.60:2073
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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