Influence of Airfoil Trailing-edge Angle and Trailing-edge Thickness Variation on the Effectiveness of a Plain Flap at High Subsonic Mach Numbers


Book Description

The effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap are appraised from wind-tunnel tests at Mach numbers from 0.3 to 0.9 and Reynolds numbers varying correspondingly from 1 to 2 million. The airfoil trailing-edge angle was varied from approximately 18 to 6 degrees, and the trailing-edge thickness from zero to the thickness at the flap hinge line.







Index of NACA Technical Publications


Book Description










Report


Book Description




Annual Report


Book Description







NASA Contractor Report


Book Description