WIND-TUNNEL TESTS OF AILERONS AT VARIOUS SPEEDS I - AILERONS OF 0.20 AIRFOIL CHORD AND TRUE CONTOUR WITH 0.35 AILERON-CHORD EXTREME BLUNT NOSE BALANCE ON THE NACA 66,2-216 AIRFOIL

摘要

Hinge-moment, lift, and pressure-distribution measurements were made in the two-dimensional test section of the NACA stability tunnel on a blunt-nose balance-type aileron on an NACA 66, 2-216 airfoil at speeds up to 360 miles per hour corresponding to a Mach number of 0.475. The tests were made primarily to determine the effect of Speed on the action of this type of aileron. The balance nose radii of the aileron were varied from 0 to 0.02 of the airfoil chord and the gap width was varied from 0.0005 to 0.0107 of the airfoil chord. Tests were also made with the gap sealed.