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The Effect of Boundary-layer Control by Suction and Several High-lift Devices on the Longitudinal Aerodynamic Characteristics of a 47.5 Degree Sweptback Wing-fuselage CombinationAn investigation has been made in the Langley full-scale tunnel of a 47.5 degree sweptback wing-fuselage combination equipped for boundary-layer control by suction. The wing aspect ratio was 3.5, the taper ratio was 0.5, and the airfoil sections normal to the quarter-chord line were NACA 64(sub 1)-A112. The wing configurations tested included the wing with various combinations of extensible leading-edge and split flaps. The effect of Reynolds number, suction-slot location and suction flow coefficient on the aerodynamic characteristics was determined for the model at zero yaw over a range of angle of attack.
Document ID
19930085410
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Pasamanick, Jerome
Proterra, Anthony J
Date Acquired
August 16, 2013
Publication Date
November 4, 1948
Report/Patent Number
NACA-RM-L8E18
Report Number: NACA-RM-L8E18
Accession Number
93R14700
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
WING-FUSELAGE COMBINATIONS - AIRPLANES
BOUNDARY LAYER - COMPLETE WINGS
STABILITY, LONGITUDINAL - STATIC
HIGH-LIFT DEVICES - COMPLETE WINGS
REYNOLDS NUMBER EFFECTS - COMPLETE WINGS

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