Investigation of NACA 65(112)A111 (Approx.) Airfoil with 0.35-Chord Slotted Flap at Reynolds Numbers up to 25 Million.

摘要

Wind-tunnel investigation of the NACA 65 (112) A111 airfoil with 0.35-chord slotted flap was made at Reynolds Numbers ranging from 2.4 x 10 6, Results indicated that for this airfoil and flap, the flap deflection for highest maximum section lift coefficient decreased, and the flap position for highest c max moved rearward and upward as Reynolds number increased from 2.4 x 10 6 to 9.0 x 10 6. Maximum life coefficient for this airfoil with flap retracted and with flap deflected generally increased with Reynolds number up to about 15.0 x 10 6 and then decreased slightly.