Wind Tunnel Investigation Of The Boundary Layer On An Naca 0009 Airfoil Having 0 25 And 0 50 Airfoil Chord Plain Sealed Flaps
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Wind-tunnel Investigation of the Boundary Layer on an NACA 0009 Airfoil Having 0.25- and 0.50-airfoil Chord Plain Sealed Flaps
An investigation was conducted in the Langley 4- by 6-foot tunnel to determine the boundary-layer characteristics of an NACA 0009 airfoil equipped with 0.25- and 0.50-airfoil chord plain sealed flaps. The tests were made to define as thoroughly as possible the characteristics of two of the configurations used in a comprehensive investigation of control surface characteristics and also to provide additional data for comparison with previous boundary-layer analyses. The measured velocity profiles and the boundary-layer parameters determined from them are presented.