Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of a Triangular Wing and Unswept Canard

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of a Triangular Wing and Unswept Canard
Author: Victor L. Peterson
Publisher:
Total Pages: 31
Release: 1958
Genre: Airplanes
ISBN:
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The results of an investigation of the static longitudinal stability and control characteristics of a canard airplane configuration are presented without analysis for the Mach number range from 0.70 to 2.22. The configuration consisted of an aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.15 wing mean aerodynamic chords ahead of the reference center of moments. The ratio of the area of the exposed canard panels to the total area of the wing is 8.1 percent. Data are presented for various combinations of the canard, wing, and vertical tail for an angle-of-attack range from -6 to 18 degrees. The canard deflection angles ranged from 0 to 20 degrees.

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22

Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22
Author: Victor L. Peterson
Publisher:
Total Pages: 1
Release: 1961
Genre:
ISBN:
GET BOOK

The static aerodynamic characteristics of a canard airplane configuration having twin vertical stabilizing surfaces are presented. The model consisted of a wing and canard both of triangular plan form and aspect ratio 2 mounted on a Sears-Haack body of fineness ratio 12.5 and two swept and tapered wing-mounted vertical tails of aspect ratio 1.35. Data are presented for Mach numbers from 0.70 to 2.22 and for angles of attack from -6 degrees to +18 degrees at 0 degrees and 5 degrees sideslip. Tests were made with the canard off and with the canard on. Nominal canard deflection angles ranged from 0 degrees to 10 degrees. The Reynolds number was 3.68 times 10 to the 6th power based on the wing mean aerodynamic chord. Selected portions of the data obtained in this investigation are compared with previously published results for the same model having a single vertical tail instead of twin vertical tails. (Author).