The spanwise lift-distribution measurements in straight air flow on a straight and a 35 deg swept-back tapered wing (NACA airfoil section 0012) are compared with theory for two angles of attack each (alpha approx. 6 deg and alpha approx. 12 deg) in the unstalled range of flow. The complete pressure distribution for the greater of the two angles is indicated.
Pressure-Distribution Measurements on a Straight and on a 35 Degree Swept-Back Tapered Wing
1947-01-01
Miscellaneous
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English