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  • 1985-1989  (5)
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  • 1
    facet.materialart.
    Unknown
    Boundary layer crossflow stabilization of high subsonic speed LFC transport airplanes (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: With a view to the elaboration of the design of Mach 0.83 and 0.97 cruise-speed long-range aircraft employing LFC, a study is conducted of the laminar flow characteristics of supercritical airfoils of blunt leading-edge X88 type, for the case of lightly loaded wings that dispense with leading-edge flaps for low-speed operations. The boundary layer crossflow in the front acceleration zone of these airfoils' upper surface is optimally stabilized by suction in the upstream portion of the zone, yielding a crossflow that is neutrally stable.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0275
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Suction laminarization of highly swept supersonic laminar flow control wings (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An evaluation is made of a suction-based method for the laminarization of highly-swept supersonic wings at cruise Mach numbers in the 2.0-2.5 range, in the interest of the reduction of wave drag due to lift. The laminar boundary layer development, as well as Tollmien-Schlichting and crossflow instabilities, have been analyzed for the case of an X66 supercritical airfoil at 60 and 72 deg sweep, for Mach numbers of 1.56 and 2.52, respectively. Strong suction is found to be needed at the front part of the upper surface and both the upper and lower rear pressure-rise areas.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-4471
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Analysis of wind-tunnel boundary-layer transition experiments on axisymmetric bodies at transonic speeds using compressible boundary-layer stability theory (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The design of laminar flow fuselages and advanced swept wings at high-subsonic compressible speeds can benefit from a correlation of compressible transition experiments with the e exp n transition-prediction method. A computational analysis has been conducted to investigate the detailed transition measurements obtained by Boltz et al. (1956, 1960) for two bodies-of-revolution. Nonadiabatic wall conditions were included in the analysis when wall-temperature measurements were available.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0008
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Design of low Reynolds number airfoils. II (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Low Reynolds number airfoils were designed for high lift-to-drag ratios. Design considerations of low Re-airfoils are discussed and design examples are presented. It is shown that the performance of advance low Reynolds airfoils critically depends on proper laminar separation and transition control for the minimum profile drag coefficient with minimum turbulator device drag. This transition control close to the laminar separation is possible by enforcing transition on the upper surface either directly by means of spanwise rows of three-dimensional roughness elements, bleed or suction holes, or indirectly by means of destabilizing the upper surface boundary layer by means of backward facing surface steps, two-dimensional or zig-zag tapes or weak boundary layer blowing. Pneumatic turbulators are found to be advantageous because they can be adjusted to different external flow conditions better than mechanical ones.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-3764 , AIAA, ASME, SIAM, and APS, National Fluid Dynamics Congress; Jul 25, 1988 - Jul 28, 1988; Cincinnati, OH; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Design of low Reynolds number airfoils. I (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The low Reynolds number airfoils designated ASM-LRN-003 and -007 have been designed for high section L/D ratios using Drela's (1985) design-and-analysis code; close to 70-percent laminar flow is maintained on the upper surfaces, and 100-percent on the lower, at coefficients of lift of 1.0-1.3, assuming optimum laminar separation and transition control on the upper surface by means of suitable turbulators. If peak performance is critical, airfoils of this type with an undercut front lower surface and a correspondingly sharper leading edge may be resorted to.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-2572 , AIAA Applied Aerodynamics Conference; Jun 06, 1988 - Jun 08, 1988; Williamsburg, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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