Investigation made in Langley stability tunnel; all wings had aspect ratios of 2.61 and had NACA 0012 airfoil sections normal to quarter-chord lines; taper ratios of 1.00, 0.50, and 0.25 investigated; experimental results compared with available theory.
Effect of taper ratio on low-speed static and yawing stability derivatives of 45° sweptback wings with aspect ratio of 2.61
Nat Advisory Committee Aeronautics -- Tech Note
1948
20 pages
Article (Journal)
English
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