Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

0( α )x static dependence function between the position of the point where theflow separates and the angle of attack.yinternal state variable related to the non-dimensional spanwise position ofthe leading edge vortex core.0( φ)y function that represents the static dependence function between thespanwise position of the leading edge vortex core and the roll angle.tˆconvective timexGreek Alphabetαangle of attack∗αβθv0( φ)angle of attack value at which the separation reaches half of the chord, andused to position the logistic function that represents the static dependenceof the separation point coordinate with the angle of attack.sideslip anglepitch angleinternal state variable related to both the vortex core vertical position andvortex strength.v function that represents the static dependence between the internal stateφvariable v and the roll angle.roll angle∗φστ1τ2ξψroll angle value that gives the position of the logistic function thatrepresents the static dependence of either the vortex core spanwiseposition or the combination of vertical position and vortex strength.slope of the logistic functiontransient time of flow adjustmenttime-delay for flow adjustmentairplane side of the lifting surface panel considered.head angle