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  • 1
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    High-flaps for natural laminar flow airfoils (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A review of the NACA and NASA low-drag airfoil research is presented with particular emphasis given to the development of mechanical high-lift flap systems and their application to general aviation aircraft. These flap systems include split, plain, single-slotted, and double-slotted trailing-edge flaps plus slat and Krueger leading-edge devices. The recently developed continuous variable-camber high-lift mechanism is also described. The state-of-the-art of theoretical methods for the design and analysis of multi-component airfoils in two-dimensional subsonic flow is discussed, and a detailed description of the Langley MCARF (Multi-Component Airfoil Analysis Program) computer code is presented. The results of a recent effort to design a single- and double-slotted flap system for the NASA high speed natural laminar flow (HSNLF) (1)-0213 airfoil using the MCARF code are presented to demonstrate the capabilities and limitations of the code.
    Keywords: AERODYNAMICS
    Type: Laminar Flow Aircraft Certification; p 31-6
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Pressure distributions from subsonic tests of an advanced laminar-flow-control wing with leading- and trailing-edge flaps (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An unswept, semispan wing model equipped with full-span leading- and trailing-edge flaps was tested in the Langley 14- by 22-Foot Subsonic Tunnel to determine the effect of high-lift components on the aerodynamics of an advanced laminar-flow-control (LFC) airfoil section. Chordwise pressure distributions near the midsemispan were measured for four configurations: cruise, trailing-edge flap only, and trailing-edge flap with a leading-edge Krueger flap of either 0.10 or 0.12 chord. Part 1 of this report (under separate cover) presents a representative sample of the plotted pressure distribution data for each configuration tested. Part 2 presents the entire set of plotted and tabulated pressure distribution data. The data are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4040-PT-2 , L-16405 , NAS 1.15:4040-PT-2
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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