Download or read book Influence of Airfoil Trailing-edge Angle and Trailing-edge Thickness Variation on the Effectiveness of a Plain Flap at High Subsonic Mach Numbers written by Albert D. Hemenover and published by . This book was released on 1954 with total page 764 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.