# Vertical tail #============================================================================== VTail = Aircraft.VTail VTail.Airfoil = 'NACA0012' #VTail.VC = 0.09 #VTail.AR = 2 VTail.b = 20 * IN VTail.TR = 0.75 VTail.Axis = (0, 1) #(0,1) VTail.L = HTail.L #Setting Vtail at distance back From Wing VTail.o_eff = 0.96 VTail.S = 210 * IN**2 VTail.FullWing = False VTail.Symmetric = False Aircraft.VTailPos = 0 # # Rudder properties VTail.Rudder.Fc = 0.5 VTail.Rudder.Weight = 0.05 * LBF VTail.Rudder.WeightGroup = "VTail" VTail.Rudder.SgnDup = -1.0 VTail.Rudder.Servo.Fc = 0.3 VTail.Rudder.Servo.Fbc = 0 #VTail.Rudder.Servo.Weight = 5*GRAM*gacc VTail.Rudder.Servo.Weight = 0.3 * OZF VTail.Rudder.Servo.WeightGroup = "Controls" VTail.Rudder.Servo.Torque = 33.3 * IN * OZM #Set the sweep about the rudder hinge VTail.SweepFc = 1.0 #- VTail.Rudder.Fc
HTail.WingWeight.AddSpar('TrailingEdge2', 1 / 32 * IN, 2 * IN, (0.25, 1), 1.0,
False)
HTail.WingWeight.TrailingEdge2.SparMat = Balsa.copy(
) #.LinearForceDensity = .008*LBF/(1*IN)
HTail.WingWeight.TrailingEdge2.Position = (0.45, 0.55)
HTail.WingWeight.TrailingEdge2.ScaleToWing = [False, False]
HTail.WingWeight.TrailingEdge2.WeightGroup = "HTail"
#==============================================================================#
# VERTICAL TAIL
#==============================================================================#
# VERTICAL TAIL
VTail = Aircraft.VTail
VTail.Airfoil = 'NACA0012'
Aircraft.VTailPos = 0.0 # spanwise along the horiz tail semi-span
VTail.Axis = (
0.0, 1.0
) # (0,1) full wing (or vert above centerline); (0,-1) for vert below centerline
VTail.L = HTail.L #-6*IN # match the LE of the horiz and vert tails
VTail.S = 185 * IN**2
VTail.b = 15 * IN
VTail.TR = 0.85417
VTail.o_eff = 0.96
VTail.FullWing = False # top and bottom of centerline
VTail.Symmetric = False # duplicates the vtail on the opposite side of tail
# Rudder properties