Pressure distributions on a rectangular aspect-ratio-6, slotted supercritical airfoil wing with externally blown flaps /
William G. Johnson, Jr. ; Langley Research Center, Hampton, Va.

Description

Main Author

Johnson, William G. (William Garland), 1944-

Related Names

Langley Research Center.
United States. National Aeronautics and Space Administration.

Language(s)

English

Published

Washington : U.S. National Aeronautics and Space Administration ; 1976.

Subjects

Wind tunnel tests.
Short takeoff aircraft.
Lift devices.
Angle of attack.
Supercritical wings.
Pressure distribution.
Externally blown flaps.
Flaps (Airplanes)
Aspect ratio (Aerofoils)
Short take-off and landing aircraft.

Summary

An investigation was made in the 5.18 m (17 ft) test section of the Langley 300 MPH 7 by 10 foot tunnel on a rectangular, aspect ratio 6 wing which had a slotted supercritical airfoil section and externally blown flaps. The 13 percent thick wing was fitted with two high lift flap systems: single slotted and double slotted. The designations single slotted and double slotted do not include the slot which exists near the trailing edge of the basic slotted supercritical airfoil. Tests were made over an angle of attack range of -6 deg to 20 deg and a thrust-coefficient range up to 1.94 for a free-stream dynamic pressure of 526.7 Pa (11.0 lb/sq ft). The results of the investigation are presented as curves and tabulations of the chordwise pressure distributions at the midsemispan station for the wing and each flap element.

Note

Cover title.

Physical Description

[1], 252 p. : ill. ; 27 cm.

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