def example1(): # run trim analysis import aircraft ac = aircraft.load('V0510') fc = flightConditions() CG = numpy.array([1.7,0,0]) I = numpy.array([500., 1000, 1000]) M = 600. V = 50. density = 1.2255 Cd0 = ac.get_drag(V,0.0) fc.addTrimmedFlightCondition('cruise1',M,CG,I,V,density,CmTrim=0.0,Cd0=Cd0) a3d = aero3d_VLM(ac) rslt = a3d.runVLM(fc,False) print 'GENERAL' rslt.results[0].display() print 'PHUGOID' rslt.results[0].dynamicStability.phugoid.display() print 'SHORT PERIOD' rslt.results[0].dynamicStability.shortPeriod.display() print 'DUTCH ROLL' rslt.results[0].dynamicStability.dutchRoll.display() print 'SPIRAL' rslt.results[0].dynamicStability.spiral.display() print 'ROLL' rslt.results[0].dynamicStability.roll.display()
def run_test(): import aircraft ac = aircraft.load('V0510') fc = flightConditions() CG = ac.get_CG(False) I = ac.get_inertia(False) M = ac.get_mass_total(False) V = 1.0 rho = 1.2255 Cd0 = ac.get_drag(V,0.0) fc.addTrimmedFlightCondition('trim',M, CG, I, V, rho) fc.flightConditionList[0].setRudder(0.) aero3D = aero3d_VLM(ac) rslt = aero3D.runVLM(fc) rslt.results[0].display()