Effects of Canards on Airplane Performance and Stability
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Hall, Charles F↗
Engineering topics
Boyd, John W
Publications and source records attributed to Boyd, John W.
Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : longitudinal characteristics of an unswept wing and canard
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Peterson, Victor L↗
Static stability and control of canard configurations at Mach numbers from 0.70 to 2.22 : triangular wing and canard on an extended body
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Boyd, John W↗
Static Stability and Control of Canard Configurations at Mach Numbers from 0.70 to 2.22 : Longitudinal Characteristics of a Triangular Wing and Canard
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Boyd, John W↗
Effects of conical camber on the lift, drag, and pitching-moment characteristics of a triangular wing of aspect ratio 3.0
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Peterson, Victor, L↗
A study of conical camber for triangular and sweptback wings
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Boyd, John W↗
Experimental Investigation of Aerodynamically Balanced Trailing-edge Control Surfaces on an Aspect Ratio 2 Triangular Wing at Subsonic and Supersonic Speeds
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Boyd, John W↗
Aerodynamic Characteristics of Two 25-percent-area Trailing-edge Flaps on an Aspect Ratio 2 Triangular Wing at Subsonic and Supersonic Speeds
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Boyd, John W↗
A Comparison of the Experimental and Theoretical Loading over Triangular Wings in Sideslip at Supersonic Speeds
The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 30-percent chord.
DIHEDRAL - COMPLETE WING↗
A Comparison of the Experimental and Theoretical Loading over Triangular Wings at Supersonic Speeds
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Boyd, John W↗
A Comparison of Theoretical and Experimental Loading on a 63 Degrees Swept-back Wing at Supersonic Speeds
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Stevens, Victor I↗
Investigation at Supersonic Speed (M = 1.53) of the Pressure Distribution over a 63 Degrees Swept Airfoil of Biconvex Section at Several Angles of Attack
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Katzen, Elliott D↗
Investigation at Supersonic Speed (M = 1.53) of the Pressure Distribution over a 63 Degrees Swept Airfoil of Biconvex Section at Zero Lift
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Boyd, John W↗