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  • 1
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    Effect of Ice Formations on Section Drag of Swept NACA 63A-009 Airfoil with Partial-Span Leading-Edge Slat for Various Modes of Thermal Ice Protection (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid increases in section drag coefficient and that the rate of change in section drag coefficient for the swept 63A-009 airfoil was about 2-1 times that for an unswept 651-212 airfoil. Removal of the primary ice formations by cyclic de-icing caused the drag to return almost to the bare-airfoil drag value. A comprehensive study of the slat icing and de-icing characteristics was prevented by limitations of the heating system and wake interference caused by the slat tracks and hot-gas supply duct to the slat. In general, the studies showed that icing on a thin swept airfoil will result in more detrimental aerodynamic characteristics than on a thick unswept airfoil.
    Keywords: AERODYNAMICS
    Type: NACA-RM-E53J30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of Ice and Frost Formations on Drag of NACA 65(sub 1) -212 Airfoil for Various Modes of Thermal Ice Protection (1953)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of primary and. runback icing and frost formations on the drag of an 8-foot-chord NACA 651-212 airfoil section were investigated over a range of angles of attack from 20 to 80 and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.25 to 1.4 grams per cubic meter and datum air temperatures of -30 to 30 F. The results showed that glaze-ice formations, either primary or runback, on the upper surface near the leading edge of the airfoil caused large and rapid increases in drag, especially at datum air temperatures approaching 32 F and in the presence of high rates of water catch. Ice formations at lower temperatures (rime ice) did not appreciably increase the drag coefficient over the initial (standard roughness) drag coefficient. Cyclic de-icing of the primary Ice formations on the airfoil leading-edge section permitted the drag coefficient to return almost to the bare airfoil drag value. Runback icing on the lower surface did not present a serious drag problem except when heavy spanwise ridges of runback ice occurred aft of the heatable area. Frost formations caused rapid and large increases in drag with incipient stalling of the airfoil.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2962
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic forces, moments, and stability derivatives for slender bodies of general cross section (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-TN-3283
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Theoretical Investigation of Submerged Inlets at Low Speeds (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The general characteristics of the flow field in a submerged air inlet are investigated by theoretical, wind-tunnel, and visual-flow studies. Equations are developed for calculating the laminar and turbulent boundary-layer growth along the ramp floor for parallel, divergent, and convergent ramp walls, and a general equation is derived relating the boundary-layer pressure losses to the boundary-layer thickness. It is demonstrated that the growth of the boundary layer on the floor of the divergent-ramp inlet is retarded and that a vortex pair is generated in such an inlet. Functional relationships are established between the pressure losses in the vortices and the geometry of the inlet. A general discussion of the boundary layer and vortex formations is included, in which variations of the various losses and of the incremental external drag with mass-flow ratio are considered. Effects of compressibility are also discussed.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2323
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A flight investigation of the practical problems associated with porous-leading-edge suction (1954)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79864 , NACA-TN-3062
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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