Results of pressure-distribution tests on airfoil with conventional trailing edge flap, which were made in atmospheric wind tunnel; maximum chord loadings were obtained with flap displaced downward and with airfoil at large angles of attack; greater changes were produced in normal force and in center of pressure travel by upflap than by equal downflap displacement.
Wind tunnel pressure distribution tests on an airfoil with trailing edge flap
Nat. Advisory Committee Aeronautics -- Tech. Note
1929
10 pages
10 Figs., Bibliography
Article (Journal)
English
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Wind-tunnel tests of wing with trailing-edge auxiliary airfoil used as flap
Engineering Index Backfile | 1935
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