CALCULATION OF ATTACHED OR PARTIALLY SEPARATED FLOW AROUND AIRFOIL SECTIONS

Two-dimensional airfoil theory is developed for incompressible flow, for which most aspects of the solution are found in a "mapped plan." Althougn the airfoil contour has large slopes in the physical plane when the airfoil has a round leading edge, the slopes in the mapped plane are small and uniformly approach zero as the airfoil thickness and camber ratios are made to approach zero by an affine transformation on the airfoil shape. Because of the small slopes in the mapped plane, a perturbation series is appropriate there. A relatively unified theory is given for attached and partially separated (trainling-edge separation) flows. The results of calculations by this theory are compared with the results of other theories and with measurements. The attached-flow theory is shown to be especially appropriate for thim marine propeller sections with blunted leading edges. Some new data on the pressure distribution across the wake at the trailing edge of an airfoil in partially separated flow are presented.

  • Availability:
  • Corporate Authors:

    Society of Naval Architects and Marine Engineers

    601 Pavonia Avenue
    Jersey City, NJ  USA  07306-2907
  • Authors:
    • Milgram, J H
  • Publication Date: 1977-6

Media Info

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Filing Info

  • Accession Number: 00165465
  • Record Type: Publication
  • Source Agency: Journal of Ship Research
  • Files: TRIS
  • Created Date: Nov 23 1977 12:00AM