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Effect of fuselage and engine nacelles on some aerodynamic properties of an airplane wingWith the aid of the method of J. Lotz, the writer undertook to solve theoretically the lift distribution along the span of an airplane wing, when the outline of the wing is uneven. This problem arises in the case of a mid-wing monoplane with embedded engine nacelles. The fuselage and the nacelles were considered as aerodynamically profiled, that is, as lift-producing parts. The task was therefore to determine not only the disturbance caused by the fuselage and nacelles, but also their share in the total lift of the wing. After the above-mentioned calculations, the induced velocity, due to the vortex system by which the wing was replaced, was also calculated and measured at the points corresponding, in an airplane, to the location of the horizontal tail surfaces.
Document ID
19930094681
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Vladea, Joan
Date Acquired
September 6, 2013
Publication Date
February 1, 1934
Report/Patent Number
NACA-TM-736
Accession Number
93R23601
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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