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  • 1975-1979  (5)
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  • 1
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    Unknown
    Tabulated pressure measurements on an executive-type jet transport model with a supercritical wing (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 1/9 scale model of an existing executive type jet transport refitted with a supercritical wing was tested on in the 8 foot transonic pressure tunnel. The supercritical wing had the same sweep as the original airplane wing but had maximum thickness chord ratios 33 percent larger at the mean geometric chord and almost 50 percent larger at the wing-fuselage juncture. Wing pressure distributions and fuselage pressure distributions in the vicinity of the left nacelle were measured at Mach numbers from 0.25 to 0.90 at angles of attack that generally varied from -2 deg to 10 deg. Results are presented in tabular form without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72701 , NAS 1.15:X-72701
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Effects of landing gear, speed brake and protuberances on the longitudinal aerodynamic characteristics of an NASA supercritical-wing research airplane model (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley Research Center 8-foot transonic pressure tunnel to determine the effects of the landing gear, speed brake and the major airplane protuberances on the longitudinal aerodynamic characteristics of an 0.087-scale model of the TF-8A supercritical-wing research airplane. For the effects of the landing gear and speed brake, tests were conducted at Mach numbers of 0.25 and 0.35 with a flap deflection of 20 degrees and a horizontal-tail angle of -10 degrees. These conditions simulated those required for take-off and landing. The effects of the protuberances were determined with the model configured for cruise (i.e., horizontal-tail angle of -2.5 degrees and no other control deflection), and these tests were conducted at Mach numbers from 0.50 to 1.00. The angle-of-attack range for all tests varied from about -5 degrees to 12 degrees.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72684 , NAS 1.15:X-72684
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Effects of differential and symmetrical aileron deflection on the aerodynamic characteristics of an NASA supercritical-wing research airplane model (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation has been conducted in the Langley 8 foot transonic pressure tunnel to determine the effects of differential and symmetrical aileron deflection on the longitudinal and lateral directional aerodynamic characteristics of an 0.087 scale model of an NASA supercritical wing research airplane (TF-8A). Tests were conducted at Mach numbers from 0.25 to 0.99 in order to determine the effects of differential aileron deflection and at Mach numbers of 0.25 and 0.50 to determine the effects of symmetrical aileron (flap) deflection. The angle of attack range for all tests varied from approximately -12 deg to 20 deg.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-3231 , L-10220 , NAS 1.15:X-3231
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind-tunnel investigation of several high aspect-ratio supercritical wing configurations on a wide-body-type fuselage (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted in the Langley 8-foot transonic pressure tunnel on two aspect-ratio 11.95 supercritical wings that were tested in combination with a representative wide-body-type fuselage. The two supercritical wings have identical planforms for equal sweep angles and differ only in thickness. Each wing was tested at quarter-chord sweep angles of 27 deg and 30 deg. At the higher sweep angle, the aspect ratio is reduced to 11.36. At 27 deg of quarter-chord sweep, the thicker supercritical wing (SCW-1) has maximum streamwise thickness-to-chord ratios of 0.16 at the wing-fuselage juncture, 0.14 at the planform break station, and 0.12 at the tip. The thinner wing (SCW-2) has maximum streamwise thickness-to-chord ratios of 0.144, 0.12, and 0.10 at the same stations respectively. Tests were also conducted on the thinner supercritical wing at the 27 deg sweep angle with a 15.24 cm (6.0 in.) shorter span which results in an aspect ratio of 10.25. For comparison, data were obtained on a current wide-body transport wing (AR=7) that was tested on the same fuselage used with the supercritical wings.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-71996 , NAS 1.15:X-71996
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    The NASA supercritical-wing technology (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A number of high aspect ratio supercritical wings in combination with a representative wide body type fuselage were tested in the Langley 8 foot transonic pressure tunnel. The wing parameters investigated include aspect ratio, sweep, thickness to chord ratio, and camber. Subsequent to these initial series of tests, a particular wing configuration was selected for further study and development. Tests on the selected wing involved the incorporation of a larger inboard trailing edge extension, an inboard leading edge extension, and flow through nacelles. Range factors for the various supercritical wing configurations are compared with those for a reference wide body transport configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78731 , L-12341 , NAS 1.15:78731 , CTOL Transport Technol. Conf.; Feb 28, 1978 - Mar 03, 1978; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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