ImageMethod=True,
Mstar=Mstar,
Steady=False,
KJMeth=True,
NewAIC=True,
DelTime=delTime,
NumCores=4)
# Aero inputs.
iMin = M - M / 4
iMax = M
jMin = 16 #N - N/4
jMax = N
typeMotion = 'asInput'
betaBar = 0.0 * np.pi / 180.0
omega = 30.0
ctrlSurf = ControlSurf(iMin, iMax, jMin, jMax, typeMotion, betaBar, omega)
# Gust inputs
gust = Gust(uMag=17.07, l=10.0, r=0.0)
VMINPUT = DerivedTypesAero.VMinput(c=c,
b=XBINPUT.BeamLength,
U_mag=0.0,
alpha=0.0 * np.pi / 180.0,
theta=0.0,
WakeLength=WakeLength,
ctrlSurf=ctrlSurf,
gust=gust)
# Aerolastic simulation.
AELAOPTS = AeroelasticOps(ElasticAxis=ElasticAxis,
def test_ctrlSurf(self):
"""Test K&P then Joukowski methods unsteady lift and drag."""
# Declare UVLM solver options.
VMOPTS = VMopts(M=25,
N=2,
ImageMethod=True,
Mstar=250,
Steady=False,
KJMeth=False,
NewAIC=True,
DelTime=0.0,
Rollup=False,
NumCores=4)
# Define wing geometry parameters.
c = 1.0
b = 1000.0
theta = 0.0 * np.pi / 180.0
# Define free-stream conditions.
U_mag = 1.0
alpha = 0.0 * np.pi / 180.0
# Define Control Surface
k = 1.0
omega = 2 * U_mag * k / c
betaBar = 0.1 * np.pi / 180.0
ctrlSurf = ControlSurf(20, 25, 0, 2, 'sin', betaBar, omega)
# Length of simulation.
nT = 2.0
NumChordLengths = nT * np.pi / k
VMINPUT = VMinput(c,
b,
U_mag,
alpha,
theta,
WakeLength=NumChordLengths,
ctrlSurf=ctrlSurf)
# Define unsteady solver parameters.
VMUNST = VMUnsteadyInput(VMOPTS,
VMINPUT,
WakeLength=10.0,
DelS=1.0 / 25.0,
NumChordLengths=NumChordLengths,
VelA_G=np.array([0, 0, 0]),
OmegaA_G=np.array([0, 0, 0]))
# Define 'aeroelastic' options.
ElasticAxis = -0.5
AELOPTS = AeroelasticOps(ElasticAxis=ElasticAxis) # Quarter chord.
# Run C++ solver.
CoeffHistoryKatz = Run_Cpp_Solver_UVLM(VMOPTS, VMINPUT, VMUNST,
AELOPTS)
# Run from Joukowski method.
VMOPTS.KJMeth.value = True
CoeffHistoryJouk = Run_Cpp_Solver_UVLM(VMOPTS, VMINPUT, VMUNST,
AELOPTS)
# Set parameters for analytical result.
alphaBar = 0.0
hBar = 0.0
phi0 = 0.0
phi1 = 0.0
phi2 = 0.0
a = ElasticAxis
e = 0.6
k = 1.0
Cl, Cd, alpha, beta, hDot, s = TheoGarrAerofoil(
alphaBar, betaBar, hBar, phi0, phi1, phi2, a, e, k, nT + 0.1)
# Delete unused variables
del hDot
# Interpolate analytical result onto simulated time steps.
ClTheo = np.interp(CoeffHistoryKatz[:, 0] * U_mag / (c / 2.0), s, Cl)
CdGarr = np.interp(CoeffHistoryKatz[:, 0] * U_mag / (c / 2.0), s, Cd)
# Calculate error as function of time in last period.
kTimeMid = len(CoeffHistoryKatz[:, 0]) / 2
ClErr = CoeffHistoryKatz[kTimeMid:, 3] - ClTheo[kTimeMid:]
CdErr = -CoeffHistoryKatz[kTimeMid:, 2] - CdGarr[kTimeMid:]
ClErrJouk = CoeffHistoryJouk[kTimeMid:, 3] - ClTheo[kTimeMid:]
CdErrJouk = -CoeffHistoryJouk[kTimeMid:, 2] - CdGarr[kTimeMid:]
# RMS error
rmsCl = np.sqrt(np.mean(pow(ClErr, 2.0))) / max(CoeffHistoryKatz[:, 3])
rmsCd = np.sqrt(np.mean(pow(CdErr,
2.0))) / max(-CoeffHistoryKatz[:, 2])
rmsClJouk = (np.sqrt(np.mean(pow(ClErrJouk, 2.0))) /
max(CoeffHistoryJouk[:, 3]))
rmsCdJouk = (np.sqrt(np.mean(pow(CdErrJouk, 2.0))) /
max(-CoeffHistoryJouk[:, 2]))
# Check RMS is same as on 23/05/13
self.assertAlmostEqual(rmsCl, 0.0241589106969, 6, 'RMS error in lift.')
self.assertAlmostEqual(rmsCd, 0.136290106597, 5, 'RMS error in drag.')
Plotting = False
if Plotting == True:
# Define beta here for plotting purposes.
betaSim = betaBar * np.sin(omega * CoeffHistoryKatz[:, 0])
plt.subplot(2, 1, 1)
plt.grid()
plt.plot(betaSim, -CoeffHistoryKatz[:, 2], 'ko-', beta, Cd, 'k-.')
plt.xlabel(r'$\beta$')
plt.ylabel(r'$C_d$')
plt.subplot(2, 1, 2)
plt.grid()
plt.plot(betaSim, CoeffHistoryKatz[:, 3], 'ko-', beta, Cl, 'k-.')
plt.xlabel(r'$\beta$')
plt.ylabel(r'$C_l$')
plt.show()
return CoeffHistory
if __name__ == '__main__':
# Define options for aero solver.
M = 4
N = 10
Mstar = 80
VMOPTS = VMopts(M, N, True, Mstar, False, False, True, 0.0, True, 4)
# Define wing geometry parameters.
c = 1
b = 4 #semi-span
# Define Control Surface
ctrlSurf = ControlSurf(3, 4, 6, 9, 'sin', 1 * np.pi / 180.0, 2 * np.pi)
# Define free stream conditions.
U_mag = 1.0
alpha = 0.0 * np.pi / 180.0
theta = 10.0 * np.pi / 180.0
VMINPUT = VMinput(c, b, U_mag, alpha, theta, 0.0, 15.0, ctrlSurf)
# Define unsteady solver parameters.
WakeLength = 10.0
DeltaS = 1.0 / 4.0
NumChordLengths = 10.0
VelA_A = np.array([0, 0, 0])
OmegaA_A = np.array([0, 0, 0])
VMUNST = VMUnsteadyInput(VMOPTS,VMINPUT,\