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.
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 Section
1959-01-01
Miscellaneous
No indication
English
Engineering Index Backfile | 1943
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