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Effects of Fuselage Nose Length and a Canopy on the Low-Speed Oscillatory Yawing Derivatives of a Swept-Wing Airplane Model with a Fuselage of Circular Cross SectionA wind-tunnel investigation was made at low speed in the Langley stability tunnel in order to determine the effects of fuselage nose length and a canopy on the oscillatory yawing derivatives of a complete swept-wing model configuration. The changes in nose length caused the fuselage fineness ratio to vary from 6.67 to 9.18. Data were obtained at various frequencies and amplitudes for angles of attack from 0 deg. to about 32 deg. Static lateral and longitudinal stability data are also presented.
Document ID
19980228225
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Williams, James L. (NASA Langley Research Center Hampton, VA United States)
DiCamillo, Joseph R. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1959
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-MEMO-1-15-59L
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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