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  • 1
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    Piloting and operational aspets of the F-8 supercritical wing airplane (1972)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Keywords: AERODYNAMICS
    Type: Supercritical Wing Technol.: A Report on Flight Evaluation; p 97-110
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight evaluation of the transonic stability and control characteristics of an airplane incorporating a supercritical wing (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A TF-8A airplane was equipped with a transport type supercritical wing and fuselage fairings to evaluate predicted performance improvements for cruise at transonic speeds. A comparison of aerodynamic derivatives extracted from flight and wind tunnel data showed that static longitudinal stability, effective dihedral, and aileron effectiveness, were higher than predicted. The static directional stability derivative was slower than predicted. The airplane's handling qualities were acceptable with the stability augmentation system on. The unaugmented airplane exhibited some adverse lateral directional characteristics that involved low Dutch roll damping and low roll control power at high angles of attack and roll control power that was greater than satisfactory for transport aircraft at cruise conditions. Longitudinally, the aircraft exhibited a mild pitchup tendency. Leading edge vortex generators delayed the onset of flow separation, moving the pitchup point to a higher lift coefficient and reducing its severity.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1167 , H-916
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight investigation of approach and flare from simulated breakout altitude of a subsonic jet transport and comparison with analytical models (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Satisfactory and optimum flare windows are defined from pilot ratings and comments. Maximum flare normal accelerations, touchdown rates of sink, and total landing maneuver time increments are summarized as a function of approach airspeed margin (with respect to reference airspeed) and flare initiation altitude. The effects of two thrust management techniques are investigated. Comparisons are made with predictions from three analytical models and the results of a simulator study. The approach speed margin was found to have a greater influence on the flare initiation altitude than the absolute airspeed. The optimum airspeed was between the reference airspeed and the reference airspeed plus 10 knots. The optimum flare initiation altitude range for unrestricted landings was from 11 meters to 20 meters (36 feet to 66 feet), and the landing time in the optimum window was 8 seconds. The duration of the landing maneuver increased with increasing flare initiation altitude and with increasing speed margins on the approach.
    Keywords: AIRCRAFT
    Type: NASA-TN-D-7645 , H-803
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Preliminary flight evaluation of the stability and control derivatives and dynamic characteristics of the unaugmented XB-70-1 airplane including comparisons with predictions (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Aerodynamic stability and control characteristics of supersonic aircraft
    Keywords: AIRCRAFT
    Type: NASA-TN-D-4578
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Precision controllability of the F-15 airplane (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flying qualities evaluation conducted on a preproduction F-15 airplane permitted an assessment to be made of its precision controllability in the high subsonic and low transonic flight regime over the allowable angle of attack range. Precision controllability, or gunsight tracking, studies were conducted in windup turn maneuvers with the gunsight in the caged pipper mode and depressed 70 mils. This evaluation showed the F-15 airplane to experience severe buffet and mild-to-moderate wing rock at the higher angles of attack. It showed the F-15 airplane radial tracking precision to vary from approximately 6 to 20 mils over the load factor range tested. Tracking in the presence of wing rock essentially doubled the radial tracking error generated at the lower angles of attack. The stability augmentation system affected the tracking precision of the F-15 airplane more than it did that of previous aircraft studied.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-72861 , H-1073
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    HiMAT aerodynamic design and flight test experience (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Consideration is given to the design phase of the highly maneuverable aircraft technology program. Design objectives are examined, noting full-scale design and the remotely piloted research vehicle. Attention is given to subsonic, transonic, and supersonic design. Design results are discussed with reference to aerodynamic efficiency, aeroelastic tailoring, and the flight test program.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-2433 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
    Format: text
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    NASA TECHNICAL REPORTS
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