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
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1962
- Accession Number
- AD0274580
Entities
People
- Bernard Jr. Spencer
Organizations
- National Aeronautics and Space Administration