def calc_hinges():
import aircraft
ac = aircraft.load('V0510')
fc = flightConditions()
CG = [1.824,0.0,-0.125]
I = ac.get_inertia()
m = 620.0
V = 75.0
rho = 1.2255
CD0 = ac.get_drag(V,0.0)
n = 1.0
fc.add_flight_condition('hinge',m,CG,I,V,rho,n,CD0,alpha=20.0,elevator=30.0)
aero3d = aero3d_VLM(ac)
rslt = aero3d.runVLM(fc)
rslt.results[0].hingeMoments.display()
def run_test3():
import aircraft
import matplotlib.pyplot as plt
ac = aircraft.load('V0510')
fc = flightConditions()
CG = ac.get_CG()
I = ac.get_inertia()
m = ac.get_mass_total()
V = 50.0
rho = 1.2255
CD0 = ac.get_drag(V,0.0)
ail = [-10,0,2,5,7,10]
ailDisp = list()
r = 15
for a in ail:
fc.add_flight_condition('untrimmed',m,CG,I,V,rho,CD0=CD0,aileron=a,rudder=r)
ailDisp.append(a)
aero3d = aero3d_VLM(ac)
rslt = aero3d.runVLM(fc)
cl = [rslt.results[i].coefficients.Cl for i in range(len(ail))]
plt.plot(ailDisp,cl,'ro-')
plt.show()
