Pressure measurements made at Mach number of 0.13 and Reynolds number of 2.4 million based on mean aerodynamic chord; values of section and wing lift coefficients, and centers of pressure derived from pressure data, also given.
Chordwise and spanwise loadings measured at low speed on triangular wing having aspect ratio of two and NACA 0012 airfoil section
Nat Advisory Committee Aeronautics -- Tech Note
1948
12 pages
16 Supp plates
Article (Journal)
English
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