# Visualization & Results
#==============================================================================#
if __name__ == '__main__':
import pylab as pyl
print "V lift off : ", AsUnit(Wing.GetV_LO(), 'ft/s')
print "V stall : ", AsUnit(Wing.V_Stall, 'ft/s')
print "Wing Area : ", AsUnit(Wing.S, 'in**2')
print "Wing Span : ", AsUnit(Wing.b, 'in')
print "Wing AR : ", Wing.AR
print "Wing MAC : ", AsUnit(Wing.MAC(), 'in')
print "Wing Xac : ", AsUnit(Wing.Xac(), 'in')
print "Wing dCM_da : ", Wing.dCM_da()
print "Wing dCL_da : ", Wing.dCL_da()
print "Lift off Load: ", AsUnit(Wing.Lift_LO, 'lbf')
print "Wing Thk : ", AsUnit(Wing.Thickness(0 * FT), 'in')
print "Wing Chord : ", AsUnit(Wing.Chord(0 * FT), 'in')
print "Wing Lift : ", AsUnit(Wing.Lift_LO, 'lbf')
print "Wing MOI : ", AsUnit(Wing.MOI(), 'slug*ft**2')
print
print "WEIGHT CALCULATIONS"
print "Main Spar Wt : ", AsUnit(Wing.WingWeight.MainSpar.Weight, 'ozf')
print "2nd Spar Wt : ", AsUnit(Wing.WingWeight.SecondSpar.Weight, 'ozf')
print "L.E. Weight : ", AsUnit(Wing.WingWeight.LeadingEdge.Weight+\
Wing.WingWeight.LeadingEdgeBent1.Weight+\
Wing.WingWeight.LeadingEdgeBent2.Weight,'ozf')
print "T.E. Weight : ", AsUnit(Wing.WingWeight.TrailingEdge1.Weight+\
Wing.WingWeight.TrailingEdge2.Weight,'ozf')
print "Rib Weight : ", AsUnit(Wing.WingWeight.RibWeight(), 'ozf')
print "Skin Weight : ", AsUnit(Wing.WingWeight.SkinWeight(), 'ozf')
print "Servos Weight: ", AsUnit(2 * Wing.Aileron.Servo.Weight, 'ozf')
Wing.Aileron.Servo.Fc = 0.3 Wing.Aileron.Servo.Weight = 0.01 * LBF ############################################################################### # # Structural properties # ############################################################################### # # Spar material (basswood, 1/4in width at max airfoil thickness + d-spar skin, balsa 1/16in) # sparw = 0.25 * IN Basswood = Basswood.copy() Balsa = Balsa.copy() Wing.Refresh() # refresh so the thicknesses can be calculated Wthick = Wing.Thickness(0 * FT) sparFD = Basswood.ForceDensity * sparw * Wthick # Dspar density as balsa at 1/16in thick and the distance around the front of the airfoil # approximated as 2 times the airfoil thickness at the root DsparFD = Balsa.ForceDensity * 0.0625 * IN * 2.0 * Wthick # # Rib material (1/8in balsa) # BWRibMat = Balsa.copy() BWRibMat.Thickness = 0.125 * IN Wing.SetWeightCalc(ACRibWing) Wing.WingWeight.SkinMat = Monokote.copy() Wing.WingWeight.RibMat = BWRibMat