Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

101Table 3-1 Model parameters for the first investigated model.i x CN (i) x Cl (i) x dyn (i)1 C N0 y l @ φ = 0°a 32 a 1 y l @ φ = 10°b 33 b 1 y l @ φ = 20°c 34 c 1 y l @ φ = 30°a 45 a 2 y r @ φ = 0°b 46 b 2 y r @ φ = 10°c 47 c 2 y r @ φ = 20°a 58∗α D@φ = 0°y r @ φ = 30°b 59∗α D@φ = 10°- c 510∗α D@φ = 20°- τ111∗α D@φ = 30°- τ212∗α U@φ = 0°- -13∗α U@φ = 10°- -14∗α U@φ = 20°- -15∗α U@φ = 30°- -16 σ D@ φ = 0°- -17 σ D@ φ = 10°- -18 σ D@ φ = 20°- -19 σ D@ φ = 30°- -20 σ U@φ = 0°- -21 σ U@φ = 10°- -22 σ U@φ = 20°- -23 σ U@φ = 30°- -