import pylab as pyl import numpy as npy # # Set-up AVL Controls Run # Controls = ACControls(Aircraft) Controls.RunDir = 'AVLControls/' Controls.AddRun('Stab', 'AVLAircraft.avl', WriteAVLInput = True) Controls.Stab.DumpStability('AVLDeriv.txt') Controls.Stab.Exit() Controls.ExecuteAVL() Controls.ReadAVLFiles() Controls.Ixx = 0.314*SLUG*FT**2 Controls.Iyy = 0.414*SLUG*FT**2 Controls.Izz = 0.570*SLUG*FT**2 Controls.Weight = 7.4*LBF Deriv = Controls.Deriv[0] Deriv.StabilityTable(fig=1) print "\n Aircraft MOI: ",Aircraft.MOI() print 'Steady state roll rate: ', AsUnit( Deriv.RollDueToAileron(20 * ARCDEG, 'Aileron'), 'deg/s' ) Aircraft.Draw(2) pyl.show()