A Langley low-turbulence wind-tunnel investigation of a porous NACA 64A010 airfoil section has been made to determine the effectiveness of area suction in maintaining full-chord laminar flow behind finite disturbances and at angles of attacks other than 0 degrees. Aero suction resulted in only a small increase in the size of a finite disturbance required to cause premature boundary-layer transition as compared with that for the airfoil without suction. Combined wake and suction drags lower than the drag of the plain airfoil were obtained through a range of low lift coefficient by the use of area suction.
Experimental Study of the Effects of Finite Surface Disturbances and Angle of Attack on the Laminar Boundary Layer of an NACA 64A010 Airfoil with Area Suction
1952-10-01
Miscellaneous
No indication
English
Engineering Index Backfile | 1952
|Engineering Index Backfile | 1950
|Engineering Index Backfile | 1949
|Boundary-layer and stalling characteristics of NACA 64a010 airfoil section
Engineering Index Backfile | 1950
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