Aircraft Stability Analysis Including Unsteady Aerodynamic Effects

105Table 3-6 Continuation of Table 3-5.i x CN (i) θ 0 = 20 deg θ 0 = 27 deg θ 0 = 38 deg θ 0 = 45 deg21∗φ 2.1314e-002 3.1542e-002 2.4476e-002 2.2465e-002v , l,D22∗φ -3.5402e-002 2.6730e-002 3.1913e-002 -3.4784e-002v , l,U23 σv , l,D1.4597e+001 6.3498e+000 8.4220e+000 1.6358e+00124 σv , l,U1.0026e-001 5.9295e+000 7.4075e+000 8.6172e-00225∗φ 6.1938e-002 2.0780e-001 1.9686e-001 6.0358e-002v , r,D26∗φ 5.7646e-002 5.2698e-001 5.6696e-001 5.6214e-002v , r,U27 σv , r,D1.3842e+001 3.7205e+000 3.6031e+000 1.5137e+00128 σv , r,U1.1438e+001 1.5301e+001 1.7665e+001 1.2999e+001Table 3-7 Identified values of the second investigated model parameters stored as x Cli x Cl (i) θ 0 = 20 deg θ 0 = 27 deg θ 0 = 38 deg θ 0 = 45 deg1∗y , l,D2∗y , l,U3y , l,D4y , l,U5∗y , r,D6∗y , r,U7y , r,Dφ 1.2602e+001 -1.9827e-001 -2.0148e-001 1.2446e+001φ 1.2602e+001 -1.9827e-001 -2.0148e-001 1.2446e+001σ -1.2015e+003 -5.3463e+000 -4.4443e+000 -1.2232e+003σ -7.8353e+000 -1.0263e+001 -5.0803e+000 -7.8896e+000φ -1.6449e+003 -2.5374e+002 -2.4108e+002 -1.7883e+003φ -1.6449e+003 -2.5374e+002 -2.4108e+002 -1.7883e+003σ 2.8408e-001 4.9048e-003 4.9760e-003 2.6722e-001