Page 307 - Aeronautical Engineer Data Book

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Drag and thrust effects due to velocity Lift and drag effects due to incidence Tailplane drag effect, usually negligible Tailplane drag due to downwash lag effect Lift effects due

Comments perturbation perturbation (added mass effect) perturbation

V ∂
∂
1 1 V 0 S 2 d q d
+ � X
C D V C L V
∂ ∂ ∂ d d T ∂ ∂ C L
Expression – 2C D – V 0 C D ∂ C L – ∂ C D˚ r˚ ∂ – V r � T ∂ C D ˚r˚ ∂ – V r � – 2C L – V 0 ∂ – C D – ∂

Small perturbation derivatives referred to aircraft wind axes
Table A3.1 Longitudinal aerodynamic stability derivatives

Axial force due to velocity Axial force due to incidence Axial force due to pitch rate Axial force due to downwash lag Normal force due to velocity Normal force due to ‘inciden

Description

Derivative X u X w X q X w ˚ Z u Z w