import pylab as pyl
if __name__ == "__main__":
Aircraft.Wing.Draw2DAirfoilPolars(fig=1)
Aircraft.HTail.Draw2DAirfoilPolars(fig=2)
Aircraft.PlotPolarsSlopes(fig=3)
Aircraft.PlotCMPolars(
4, (-12 * ARCDEG, -5 * ARCDEG, 0 * ARCDEG, +5 * ARCDEG, +12 * ARCDEG),
XcgOffsets=(+0.02, -0.02))
Aircraft.PlotCLCMComponents(fig=5,
del_es=(-10 * ARCDEG, -5 * ARCDEG, 0 * ARCDEG,
+5 * ARCDEG, +10 * ARCDEG))
Aircraft.Refresh()
print "Xnp : ", AsUnit(Aircraft.Xnp(), 'in')
print "Wing X : ", AsUnit(Aircraft.Wing.X[0], 'in')
print 'HTail Incidence : ', AsUnit(Aircraft.HTail.i, 'deg')
print 'HTail VC : ', Aircraft.HTail.VC
pyl.show()
#
# The green linear slop approximations should agree well with the blue polars.
# The slope is adjusted with the *SlopeAt variables.
#
# The CM vs. alpha curve for the neutral point should be horizontal.
#
