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()
