Influence Of Airfoil Trailing Edge Angle And Trailing Edge Thickness Variation On The Effectiveness Of A Plain Flap At High Subsonic Mach Numbers
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Influence of Airfoil Trailing-edge Angle and Trailing-edge Thickness Variation on the Effectiveness of a Plain Flap at High Subsonic Mach Numbers
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.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
language: en
Publisher:
Release Date: 1954
Research Abstracts
Author: United States. National Advisory Committee for Aeronautics
language: en
Publisher:
Release Date: