An Investigation At Mach Numbers From 020 To 463 Of The Aerodynamic Performance Static Stability And Trimming Characteristics Of A Canard Configuration Designed For Efficient Supersonic Cruise Flight
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Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Trangular Wing and Canard with Twin Vertical Tails
| Author | : Victor L. Peterson |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1961 |
| Genre | : Aerodynamics |
| ISBN | : |
Aerodynamic Characteristics at Mach Numbers of 1.5, 1.8, and 2.0 of a Blended Wing-body Configuration with and Without Integral Canards
| Author | : A. Warner Robins |
| Publisher | : |
| Total Pages | : 68 |
| Release | : 1979 |
| Genre | : Hypersonic planes |
| ISBN | : |
Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 - Longitudinal Characteristics of an Unswept Wing and Canard
| Author | : Victor L. Peterson |
| Publisher | : |
| Total Pages | : 29 |
| Release | : 1958 |
| Genre | : Airplanes |
| ISBN | : |
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 3.1 unswept wing, an aspect ratio 3.0 unswept canard, a low aspect ratio vertical tail, and a Sears-Haack body. The hinge line of the canard was in the extended chord plane of the wing, 1.33 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 - Longitudinal Characteristics of a Triangular Wing and Unswept Canard
| Author | : Victor L. Peterson |
| Publisher | : |
| Total Pages | : 31 |
| Release | : 1958 |
| Genre | : Airplanes |
| ISBN | : |
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.
