Accession Number:

AD0256076

Title:

LOW-SPEED WIND-TUNNEL INVESTIGATION OF A REFLECTION PLANE WING MODEL EQUIPPED WITH PARTIAL-SPAN JET-AUGMENTED FLAPS

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-05-01

Pagination or Media Count:

1.0

Abstract:

An investigation was made in the Langley 300-MPH 7- by 10-foot tunnel with a semispan, rectangular unswept wing of full-span aspect ratio 8.3 and thickness-to-chord ratio of 0.167. Three 50-percent partial-span jet-augmented-flap configurations located inboard, outboard, and at the midsemispan position were tested through a momentum coefficient range from 0 to about 10 and an angle-of-attack range from -10 degrees to approximately 28 degrees. The corresponding flow-field characteristics are presented for a longitudinaltail position of 4 wing chords behind the trailing edge of the wing through a range of tailheight locations of or - 2 chords. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE