The linearized equations of motion underlying the dynamic stability of aircraft, spinning projectiles, and symmetrical missiles

A. C. Charters
naca-tn-3350
Jan 1955


Linearized equations of motion are derived for both conventional aircraft having mirror symmetry and spinning projectiles or missiles having rotational and mirror symmetry. The aerodynamic coefficients are introduced as a formal series expansion in the customary variables, with additional terms being included to account for the aerodynamic effects of spin.

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