Publication Date:
2019-08-16
Description:
A 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.
Keywords:
Aircraft Stability and Control
Type:
NASA-MEMO-1-15-59L
Format:
application/pdf
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