Page 310 - Aeronautical Engineer Data Book
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Table A3.2 Small perturbation derivatives referred to aircraft wind axes
S Always negative and hence S stabilizing 1 F� y B – F � B S S s 1 Lateral static stability, determined by �c y a y ydy – s 0 S total dihedral eff
Expression (i) wing with dihedral (ii) wing with aft sweep (iii) fin contribution (i) fin contribution (i) fin contribution
Description Sideforce due to sideslip Rolling moment due to sideslip Yawing moment due to sideslip Sideforce due to roll rate
Derivative Y v L v N v Y p
