from Aircraft import Aircraft # from Aircraft_Models.Reg2014Aircraft_AeroCats.TradeStudies.WeightTrade.Aircraft_NickSchwartz import Aircraft 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. #