Accession Number:

AD0274580

Title:

LOW-SPEED AERODYNAMIC CHARACTERISTICS OF A CANARD AIRPLANE CONFIGURATION HAVING SPLIT FLAPS LOCATED AHEAD OF THE WING TRAILING EDGE AND LEADING-AND TRAILING-EDGE FLAPS ON THE CANARD CONTROL

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1962-04-01

Pagination or Media Count:

1.0

Abstract:

The investigation was conducted at low subsonic speeds in the Langley 300-MPH 7- by 10-foot tunnel. The basic wing was trapezoidal in planform with an aspect ratio of 3.0, a taper ratio of 0.143, and a leading-edge sweep of 38.52 degrees. Modifications to the basic wing included deflectable partial-span leading-edge chord-extensions, plain lift flaps located at the trailing edge, and split flaps located forward of the trailing edge. A trapezoidal canard surface similar in planform to the wing, a 60 degrees delta surface and a modified 60 degree delta canard suface were tested in conjunction with the wing. Use of trailing-edge flaps located on the 60 degrees delta and trapezoidal canard surfaces was also investigated as possible longitudinal controls. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE