Investigation of Boundary-layer Transition on Flat-faced Bodies of Revolution at High Supersonic Speeds
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Canning, Thomas N↗
Engineering topics
Canning, Thomas N
Publications and source records attributed to Canning, Thomas N.
Some Experiments at High Supersonic Speeds on the Aerodynamic and Boundary-layer Transition Characteristics of High-drag Bodies of Revolution
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Seiff, Alvin↗
Drag and Rolling-moment Effectiveness of Trailing-edge Spoilers at Mach Numbers 2.2 and 5.0
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Canning, Thomas N↗
Investigation of the lift, center of pressure, and drag of a projectile at a Mach number of 8.6 and a Reynolds number of 17 million
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Canning, Thomas N↗
A simple mechanical analogue for studying the dynamic stability of aircraft having nonlinear moment characteristics
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Canning, Thomas N↗
Investigation of Lift and Center of Pressure of Low-aspect-ratio, Cruciform, Triangular, and Rectangular Wings in Combination with a Slender Fuselage at High Supersonic Speeds
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Canning, Thomas N↗
The Ames Supersonic Free-flight Wind Tunnel
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Seiff, Alvin↗
Investigation of downwash and wake characteristics at a Mach number of 1.53 III : swept wings
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Perkins, Edward W↗
Investigation of Downwash and Wake Characteristics at a Mach Number of 1.53 II : Triangular Wing
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Perkins, Edward W↗
Investigation of Downwash and Wake Characteristics at a Mach Number of 1.53 I : Rectangular Wing
The results of an experimental investigation of the downwash and wake characteristics behind a rectangular plan-form wing of aspect ratio 3.5 are presented. The airfoil section was a 5-percent-thick, symmetrical double wedge. The tests were made at a Mach number of 1.53 and a Reynolds number of 1.25 million. A comparison between experimental and theoretical values of the downwash angles is made.
STABILITY, LONGITUDINAL - STATIC↗