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  • 1
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    Application of laminar flow control to the High Speed Civil Transport - The NASA Supersonic Laminar Flow Control Program (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The NASA Supersonic Laminar Flow Control (SLFC) program encompasses the development of refined CFD methods and boundary layer stability codes for the highly 3D supersonic flow conditions encountered by the F-16XL technology demonstration aircraft and the prospective High Speed Civil Transport (HSCT). While the F-16XL-1 aircraft continues to gather SLFC data, work is under way on the F-16XL-2 aircraft: which will furnish attach-line design criteria, code-calibration data, and an improved understanding of the flowfield over a wing that will add confidence to the design of HSCTs' boundary layer-controlling air-suction panels.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 912115
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Optimization of natural laminar flow airfoils for high section lift-to-drag ratios in the lower Reynolds number range (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Relatively thin natural-laminar-flow airfoils were arranged optimally for different design lift coefficients in the wing chord Reynolds number ranges of 200,000-600,00 and 0.875 x 10 to the 6th to 2 x 10 to the 6th. The 9.5 percent thick airfoil ASM-LRN-010, the 7.9 percent thick airfoil ASM-LRN-012, the 10.4 percent thick airfoil ASM-LRN-015, and the 8.2 percent thick airfoil ASM-LRN-017 were designed for high lift-to-drag ratios using Drela's design and analysis.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0539
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    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
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    NASA TECHNICAL REPORTS
  • 4
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    Evaluation of an analysis method for low-speed airfoils by comparison with wind tunnel results (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Results obtained by the airfoil analysis method of Drela (1980) for three airfoils are compared with wind tunnel test results. The method is shown to be accurate in predicting the aerodynamic characteristics of low-speed airfoils in the chord Reynolds number range from 200,000 to 3 million. It is noted that a high value for the transition criterion was necessary to accurately study the case of laminar separation.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0266
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Design philosophy of long range LFC transports with advanced supercritical LFC airfoils (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The achievement of 70 percent laminar flow using modest boundary layer suction on the wings, empennage, nacelles, and struts of long-range LFC transports, combined with larger wing spans and lower span loadings, could make possible an unrefuelled range halfway around the world up to near sonic cruise speeds with large payloads. It is shown that supercritical LFC airfoils with undercut front and rear lower surfaces, an upper surface static pressure coefficient distribution with an extensive low supersonic flat rooftop, a far upstream supersonic pressure minimum, and a steep subsonic rear pressure rise with suction or a slotted cruise flap could alleviate sweep-induced crossflow and attachment-line boundary-layer instability. Wing-mounted superfans can reduce fuel consumption and engine tone noise.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: ICAS Congress; Aug 28, 1988; Jerusalem; Israel
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Design aspects of long range supersonic LFC airplanes with highly swept wings (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The achievement of natural LFC in SST configurations featuring externally braced, very highly swept, high structural aspect ratio wing planforms results in outstandingly high cruise L/D ratios while maintaining low sonic-boom overpressures. A conceptual design study has been conducted with a view to range capability maximization in SSTs. A three-body configuration employing a highly swept, strut-braced planform, in which a central fuselage and two smaller outboard bodies alleviate structural wing bending and torsion, is noted to allow further increases in wingspan and aspect ratio which commensurately reduce lift-induced wave-plus-vortex drag and volume-induced wave drag.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 881397 , Aerospace Technology Conference and Exposition; Oct 03, 1988 - Oct 06, 1988; Anaheim, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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