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Aerodynamics of the FuselageThe present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something like a neutral stability point the position of which on oblong fuselages appears to be associated with the lift increase of the fuselage in proximity to the zero lift, according to the present experiments. The Pitching moments of the fuselage can be determined with comparatively great reliability so far as the flow conditions in the neighborhood of the axis of the fuselage can be approximated if the fuselage were absent, which, in general, is not very difficult. For the unstable contribution of the fuselage to the static longitudinal stability of the airplane it affords comparatively simple formulas, the evaluation of which offers little difficulty. On the engine nacelles there is, in addition a very substantial wing moment contribution induced by the nonuniform distribution of the transverse displacement flow of the nacelle along the wing chord; this also can be represented by a simple formula. A check on a large number of dissimilar aircraft types regarding the unstable fuselage and nacelle moments disclosed an agreement with the wind-tunnel tests, which should be sufficient for practical requirements. The errors remained throughout within the scope of instrumental accuracy.
Document ID
20000004246
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Memorandum
Authors
Multhopp, H.
Date Acquired
September 7, 2013
Publication Date
December 1, 1942
Publication Information
Publication: Luftfahrtforschung
Volume: 18
Issue: 3-Feb
Subject Category
Aerodynamics
Report/Patent Number
NACA-TM-1036
Report Number: NACA-TM-1036
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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