Pressure distributions and oil-flow patterns for a swept circulation-control wing

Keener, Earl R.; Sanderfer, Dwight T.; Wood, Norman J.

Pressure distributions and photographs of oil flow patterns are presented for a circulation control wing. The model was an aspect ratio four semispan wing mounted on the side wall of the NASA Ames Transonic Wind Tunnel. The airfoil was a 20 percent thick ellipse, modified with circular leading and trailing edges of 4 percent radius, and had a 25.4 cm constant chord. This configuration does not represent a specific wing design, but is generic. A full span, tangetial, rearward blowing, circulation control slot was incorporated ahead of the trailing edge on the upper surface. The wing was tested at Mach numbers from 0.3 to 0.75 at sweep angle of 0 to 45 deg with internal to external pressure ratios of 1.0 to 3.0. Lift and pitching momemt coefficients were obtained from measured pressure distributions at five span stations. When the conventional corrections resulting from sweep angle are applied to the lift and moment of circulation control sections, no additional corrections are necessary to account for changes in blowing efficiency. This is demonstrated for an aft sweep angle of 45 deg. An empirical technique for estimating the downwash distribution of a swept wing was validated.

Document ID

19880008212

Acquisition Source

Legacy CDMS

Document Type

Conference Paper

Authors

Date Acquired

September 5, 2013

Publication Date

May 1, 1987

Publication Information

Publication: Proceedings of the Circulation-Control Workshop, 1986

Subject Category

Accession Number

88N17596

Distribution Limits

Public

Work of the US Gov. Public Use Permitted.

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19880008212.pdf

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