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  • 1
    facet.materialart.
    Unknown
    An analysis of prop-fan/airframe aerodynamic integration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An approach to aerodynamic integration of turboprops and airframes, with emphasis placed upon wing mounted installations is addressed. Potential flow analytical techniques were employed to study aerodynamic integration of the prop fan propulsion concept with advanced, subsonic, commercial transport airframes. Three basic configurations were defined and analyzed: wing mounted prop fan at a cruise Mach number of 0.8, wing mounted prop fan in a low speed configuration, and aft mounted prop fan at a cruise Mach number of 0.8.
    Keywords: AERODYNAMICS
    Type: NASA-CR-152186 , NAS 1.26:152186 , D6-47113
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Effect of Reynolds number on stability characteristics of a cruciform wing-body (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was conducted to determine the effect of Reynolds number on the stability characteristics of a body with cruciform wings at large angles of attack. Pressure distributions and force and moment data (axial force not measured) are presented for Mach 1.60 and 2.70, Reynolds numbers based on body diameter from approximately 130,000 to 2,800,000, and angles of attack from 0 deg to 50 deg. In general, the data show only small effects of Reynolds number throughout the range of test condition. Also discussed are force balance and pressure data that suggest a direct relationship between wind choking and the onset of a nonlinear stability variaton with angle of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1683 , L-13530
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Aerodynamic characteristics of a fixed arrow-wing supersonic cruise aircraft at Mach numbers of 2.30, 2.70, and 2.95 (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Tests were conducted in the Langley Unitary Plan wind tunnel at Mach numbers of 2.30. 2.70, and 2.95 to determine the performance, static stability, and control characteristics of a model of a fixed-wing supersonic cruise aircraft with a design Mach Number of 2.70 (SCAT 15-F-9898). The configuration had a 74 deg swept warped wing with a reflexed trailing edge and four engine nacelles mounted below the reflexed portion of the wing. A number of variations in the basic configuration were investigated; they included the effect of wing leading edge radius, the effect of various model components, and the effect of model control deflections.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78706 , L-12249
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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