Aircraft.CMSlopeAt = (2 * ARCDEG, 10 * ARCDEG) # shiggins: what does this do?
Aircraft.CLSlopeAt = (3 * ARCDEG, 14 * ARCDEG) # shiggins: what does this do?
Aircraft.CLHTSlopeAt = (-5 * ARCDEG, 10 * ARCDEG
) # shiggins: what does this do?
Aircraft.DWSlopeAt = (3 * ARCDEG, 15 * ARCDEG) # shiggins: what does this do?
Aircraft.Alpha_Zero_CM = 5.0 * ARCDEG # for steady level flight
Aircraft.StaticMargin = 0.005 # this is driving wing position (higher values move the wing farther aft)
Aircraft.WingXMaxIt = 60 # this is the no. of iterations to solve
Aircraft.VmaxPlt = 100 * FT / SEC # Maximum velocity for plotting purposes
Aircraft.RotationTime = 0.5 * SEC # Est time aircraft rotates on ground during takeoff
Aircraft.NoseGearOffset = 0.12 * M
#==============================================================================#
# HORIZONTAL TAIL
#==============================================================================#
HTail = Aircraft.HTail # set up the horizontal tail class
HTail.Airfoil = 'NACA0012'
Aircraft.HTailPos = 0.0 # T-Tail = 1 (horiz tail at top of vert tail);
# reg = 0 (horiz tail at same lvl as middle of tail bulk)
HTail.FullWing = True # Full wing surface (i.e. top and bottom tail)
HTail.Inverted = True # Invert the airfoil section
HTail.b = 48 * IN # horizontal tail span #MJZ was 50 in sholsinger
#HTail.S = 590.4 * IN**2 # horizontal tail planform area was 600 in**2 sholsinger
HTail.S = 650 * IN**2 # horizontal tail planform area was 650 in**2 sholsinger
Aircraft.CLSlopeAt = (0 * ARCDEG, 15 * ARCDEG) Aircraft.CLHTSlopeAt = (0 * ARCDEG, 15 * ARCDEG) Aircraft.DWSlopeAt = (0 * ARCDEG, 15 * ARCDEG) Aircraft.Alpha_Zero_CM = 3.0 * ARCDEG #for steady level flight Aircraft.StaticMargin = 0.05 # Location of Wing Aircraft.WingXMaxIt = 50 Aircraft.WingXOmega = 1 # # Maximum velocity for plotting purposes Aircraft.VmaxPlt = 75 * FT / SEC # # Estimate for the time the aircraft rotates on the ground during takeoff Aircraft.RotationTime = 0.5 * SEC Aircraft.NoseGearOffset = 9 * IN ############################################################################### # # Tail surfaces # ############################################################################### #============================================================================== # Horizontal tail #============================================================================== HTail = Aircraft.HTail HTail.Airfoil = 'NACA0012' #HTail.AR = 3 HTail.b = 42 * IN HTail.TR = 1.0 HTail.o_eff = 0.96
Aircraft.CLSlopeAt = (0 * ARCDEG, 15 * ARCDEG) Aircraft.CLHTSlopeAt = (0 * ARCDEG, 15 * ARCDEG) Aircraft.DWSlopeAt = (0 * ARCDEG, 15 * ARCDEG) Aircraft.Alpha_Zero_CM = 3.0 * ARCDEG #for steady level flight Aircraft.StaticMargin = 0.06 # Location of Wing Aircraft.WingXMaxIt = 50 Aircraft.WingXOmega = 1 # # Maximum velocity for plotting purposes Aircraft.VmaxPlt = 75 * FT / SEC # # Estimate for the time the aircraft rotates on the ground during takeoff Aircraft.RotationTime = 0.5 * SEC Aircraft.NoseGearOffset = 7.5 * IN ############################################################################### # # Tail surfaces # ############################################################################### #============================================================================== # Horizontal tail #============================================================================== HTail = Aircraft.HTail HTail.Airfoil = 'NACA0012' #HTail.AR = 3 HTail.b = 42 * IN HTail.TR = 1.0 HTail.o_eff = 0.96