Download Free Influence Of Airfoil Trailing Edge Angle And Trailing Edge Thickness Variation On The Effectiveness Of A Plain Flap At High Subsonic Mach Numbers Book in PDF and EPUB Free Download. You can read online Influence Of Airfoil Trailing Edge Angle And Trailing Edge Thickness Variation On The Effectiveness Of A Plain Flap At High Subsonic Mach Numbers and write the review.

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.
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.