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  • 1
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    Unique flight characteristics of the AD-1 oblique-wing research airplane (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 19, p. 2977, Accession no. A82-39106
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: (ISSN 0021-8669)
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flight-determined aerodynamic derivatives of the AD-1 oblique-wing research airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The AD-1 is a variable-sweep oblique-wing research airplane that exhibits unconventional stability and control characteristics. In this report, flight-determined and predicted stability and control derivatives for the AD-1 airplane are compared. The predictions are based on both wind tunnel and computational results. A final best estimate of derivatives is presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2222 , H-1179 , NAS 1.60:2222
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    In-flight total forces, moments and static aeroelastic characteristics of an oblique-wing research airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low-speed flight investigation has provided total force and moment coefficients and aeroelastic effects for the AD-1 oblique-wing research airplane. The results were interpreted and compared with predictions that were based on wind tunnel data. An assessment has been made of the aeroelastic wing bending design criteria. Lateral-directional trim requirements caused by asymmetry were determined. At angles of attack near stall, flow visualization indicated viscous flow separation and spanwise vortex flow. These effects were also apparent in the force and moment data.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2224 , H-1181 , NAS 1.60:2224
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flight-determined stability and control characteristics of the M2-F3 lifting body vehicle (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight data were obtained over a Mach number range from 0.4 to 1.55 and an angle-of-attack range from -2 deg to 16 deg. Lateral-directional and longitudinal derivatives, reaction control rocket effectiveness, and longitudinal trim information obtained from flight data and wind-tunnel predictions are compared. The effects of power, configuration change, and speed brake are discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-TN-D-7511 , H-791
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Results of a feasibility study using the Newton-Raphson digital computer program to identify lifting body derivatives from flight data (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A brief study was made to assess the applicability of the Newton-Raphson digital computer program as a routine technique for extracting aerodynamic derivatives from flight tests of lifting body types of vehicles. Lateral-direction flight data from flight tests of the HL-10 lifting body reserch vehicle were utilized. The results in general, show the computer program to be a reliable and expedient means for extracting derivatives for this class of vehicles as a standard procedure. This result was true even when stability augmentation was used. As a result of the study, a credible set of HL-10 lateral-directional derivatives was obtained from flight data. These derivatives are compared with results from wind-tunnel tests.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-56017
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Flight evaluation of the M2-F3 lifting body handling qualities at Mach numbers from 0.30 to 1.61 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Percentage distributions of 423 pilot ratings obtained from 27 flights are used to indicate the general level of handling qualities of the M2-F3 lifting body. Percentage distributions are compared on the basis of longitudinal and lateral-directional handling qualities, control system, control system status, and piloting task. Ratings of longitudinal handling qualities at low speed were slightly better than those for transonic and supersonic speed. The ratings of lateral-directional handling qualities were unaffected by speed and configuration. Specific handling qualities problems are discussed in detail, and comparisons are made with pertinent handling qualities criteria.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TN-D-8027 , H-852
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight characteristics of a manned, low-speed, controlled deep stall vehicle (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A successful manned, low-speed, controlled deep stall flight research program was conducted at NASA Ames Research Center's Dryden Flight Research Facility. Piloting techniques were established that enabled the pilot to attain and stabilize on an angle of attack in the 30 to 72 deg range. A flight-determined aerodynamic data base was established for angles of attack as high as 72 deg. Poor lateral-directional flying qualities were encountered at angles of attack above 60 deg. Insight into the high angle-of-attack, lateral-directional dynamics was gained through a basic root-locus analysis.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 84-2074
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    A comparison of Wortmann airfoil computer-generated lift and drag polars with flight and wind tunnel results (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Computations of drag polars for a low-speed Wortmann sailplane airfoil are compared with both wind tunnel and flight test results. Excellent correlation was shown to exist between computations and flight results except when separated flow regimes were encountered. Smoothness of the input coordinates to the PROFILE computer program was found to be essential to obtain accurate comparisons of drag polars or transition location to either the flight or wind tunnel flight results.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86035 , H-1231 , NAS 1.15:86035
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Flight-determined stability and control derivatives for the F-111 Tact research aircraft (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was conducted to provide a stability and control derivative data base for the F-111 transonic aircraft technology research aircraft. Longitudinal and lateral-directional data were obtained as functions of Mach number, angle of attack, and wing sweep. For selected derivatives, the flight results were correlated with derivatives calculated based on vehicle geometry. The validity of the angle of attack measurement was independently verified at a Mach number of 0.70 for angles of attack between 3 and 10 degrees.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1350 , H-1004
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Flight characteristics of a manned, low-speed, controlled deep stall vehicle (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A successful manned, low speed, controlled deep stall flight research program was conducted at NASA Ames Research Center's Dryden Flight Research Facility. Piloting techniques were established that enabled the pilot to attain and stabilize on an angle of attack in the 30 deg to 72 deg range. A flight determined aerodynamic data base was established for angles of attack as high as 72 deg. Poor lateral directional flying qualities were encountered at angles of attack above 60 deg. Insight into the high angle of attack lateral directional dynamics was gained through a basic root locus analysis.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86041 , H-1242 , NAS 1.15:86041 , AIAA Atmospheric Flight Mech. Conf,; Aug 21, 1984 - Aug 23, 1984; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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