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()
