Several airfoils, Including a conventional NACA 23021 and some low-drag airfoils for which the thickness had been increased to the point that they were considered doubtfully conservative with respect to separation, were investigated as smooth airfoils and after the application of a standard roughness. The results show some of the airfoils to be critical to separation resulting from such flow disturbances. It is concluded, pending the further investigation of separation difficulties, that airfoil sections falling definitely within the conservative range should be used.
Investigation of Extreme Leading-Edge Roughness on Thick Low-Drag Airfoils to Indicate Those Critical to Separation
1942-06-01
Miscellaneous
No indication
English
AIRFOILS - NACA 65,2-422 (APPROX ) - CHAR & MOMENTS - LOW-DRAG , Aerodynamics , WIND TUNNEL TESTS - NACA - PRESSURE, LOW-TURBULENCE (7 1/2' X-3') , AIRFOILS SURFACES - ROUGHNESS , AIRFOILS - NACA 65,3-418 - CHAR & MOMENTS - LOW-DRAG , AIRFOILS - BOEING 7 - SERIES - CHAR & MOMENTS , AIRFOILS - NACA 23021 - CHAR & MOMENTS , AIRFOILS, LOW-DRAG - THICK - EFFECT OF LEADING EDGE ROUGHNESS , BOUNDARY LAYER SEPARATION - AIRFOILS , AIRFOILS - NACA 65,2-222 (APPROX ) - CHAR & MOMENTS - LOW-DRAG