Page 306 - Aeronautical Engineer Data Book
P. 306
248
Comments
∂ 1 C D Drag and thrust effects due to velocity ∂ + 1 perturbation V ∂ V ∂ V 0 S 2 Lift and drag effects due to incidence perturbation Tailpl
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
