def test_KatzPlotkin(self):
"""Test final unsteady lift/drag to TAT for high AR problem using
generalised Katz and Plotkin method."""
M = 1
N = 1
Mstar = 200
VMOPTS = VMopts(M, N, True, Mstar, False, False)
# Define wing geometry parameters."
c = 1
b = 10000 #semi-span
# Define free-stream conditions."
U_mag = 0.0
alpha = 0.0 * np.pi / 180.0
theta = 1.0 * np.pi / 180.0
VMINPUT = VMinput(c, b, U_mag, alpha, theta)
# Define unsteady simulation parameters.
WakeLength = 200.0
DeltaS = 1.0
NumChordLengths = 200.0
VelA_A = np.array([0, 1.0, 0])
OmegaA_A = np.array([0, 0, 0])
VMUNST = VMUnsteadyInput(VMOPTS,VMINPUT,\
WakeLength,\
DeltaS,\
NumChordLengths,\
VelA_A, OmegaA_A)
# Define 'aeroelastic' parameters
AELOPTS = AeroelasticOps(ElasticAxis=-0.5,
InertialAxis=0.0,
AirDensity=1.0)
# Run C++ solver."
CoeffHistory = Run_Cpp_Solver_UVLM(VMOPTS, VMINPUT, VMUNST, AELOPTS)
# Check forces from Katz and Plotkin method."
self.assertAlmostEqual(CoeffHistory[-1, 3],
2 * np.pi * VMINPUT.theta,
delta=1e-3)
self.assertAlmostEqual(-CoeffHistory[-1, 2], 0, delta=1e-5)
N = 10
Mstar = 10 * M
U_mag = 25.0
alpha = 1.0 * np.pi / 180.0
theta = 0.0 * np.pi / 180.0
imageMeth = True
# Define wing geometry parameters.
c = 1
b = 2000 #16 #semi-span
# Physical time-step
DeltaS = c / (M * U_mag)
# Solver options
VMOPTS = VMopts(M, N, imageMeth, Mstar, False, True, True, DeltaS, False,
4)
# Solver inputs
WakeLength = Mstar / M # specified in chord lengths
ctrlSurf = None #ControlSurf(3, 4, 6, 9, 'sin', 1*np.pi/180.0, 2*np.pi)
VMINPUT = VMinput(c, b, U_mag, alpha, theta, WakeLength, ctrlSurf)
# Define unsteady solver parameters.
NumChordLengths = 100.0
VelA_A = np.array([0, 0, 0])
OmegaA_A = np.array([0, 0, 0])
VMUNST = VMUnsteadyInput(VMOPTS,VMINPUT,\
WakeLength,\
DeltaS*U_mag/c,\
NumChordLengths,\
VelA_A, OmegaA_A)
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()
def test_KatzPlotkin(self):
"""Test final unsteady lift/drag for AR8 problem."""
M = 4
N = 13
Mstar = 160
VMOPTS = VMopts(M, N, True, Mstar, False, False, True, 0.0, False, 4)
# Define wing geometry parameters.
c = 1
b = 4 #semi-span
# Define free-stream conditions.
U_mag = 0.0
alpha = 0.0 * np.pi / 180.0
theta = 5.0 * np.pi / 180.0
NumChordLengths = 10.0
VMINPUT = VMinput(c, b, U_mag, alpha, theta, NumChordLengths)
# Define unsteady solver parameters.
WakeLength = 10.0
DeltaS = 1.0 / 16.0
VelA_A = np.array([0, 1.0, 0])
OmegaA_A = np.array([0, 0, 0])
VMUNST = VMUnsteadyInput(VMOPTS, VMINPUT, WakeLength, DeltaS,
NumChordLengths, VelA_A, OmegaA_A)
# Define 'aeroelastic' options.
AELOPTS = AeroelasticOps(ElasticAxis=-0.5,
InertialAxis=0.0,
AirDensity=1.0)
# Run C++ solver.
CoeffHistory = Run_Cpp_Solver_UVLM(VMOPTS, VMINPUT, VMUNST, AELOPTS)
# Check force for Katz and Plotkin method against textbook at final
# time.
CD = np.loadtxt('testData/Katz1p492_AR8_CD.dat', ndmin=2)
CL = np.loadtxt('testData/Katz1p492_AR8_CL.dat', ndmin=2)
self.assertAlmostEqual(CoeffHistory[-1, 3], CL[-1, 1], delta=1e-3)
self.assertAlmostEqual(-CoeffHistory[-1, 2], CD[-1, 1], delta=1e-3)
Plotting = False
if Plotting == True:
plt.figure(1)
a = plt.plot(CD[:, 0], CD[:, 1], 'ks')
b = plt.plot(CoeffHistory[:, 0], -CoeffHistory[:, 2], 'k-')
plt.xlim((0, 10.0))
plt.ylim((0, 0.03))
plt.xlabel('U*t/c [-]')
plt.ylabel('C_D')
plt.legend(('Katz and Plotkin (2001)', 'SHARPy'),
'upper right',
shadow=True,
prop={'size': 12})
plt.figure(2)
c = plt.plot(CL[:, 0], CL[:, 1], 'ks')
d = plt.plot(CoeffHistory[:, 0], CoeffHistory[:, 3], 'k-')
plt.xlim((0, 10.0))
plt.ylim((0, 0.6))
plt.xlabel('U*t/c [-]')
plt.ylabel('C_L')
plt.legend(('Katz and Plotkin (2001)', 'SHARPy'),
'lower right',
shadow=True,
prop={'size': 12})
lines = a, b, c, d
plt.setp(lines, linewidth=2, markersize=6)
plt.show()
ZetaStar[:, :] += VMINPUT.U_infty * VMOPTS.DelTime.value
# END for iTimeStep
# Close tecplot file object.
PostProcess.CloseAeroTecFile(FileObject)
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)
n = 1
Umag = 1.0
alpha = 1.0 * np.pi / 180.0
chord = 1.0
span = 2.e3
WakeLength = 10.0
imageMeth = True
VMINPUT = DerivedTypesAero.VMinput(chord,
b=span,
U_mag=Umag,
alpha=alpha,
theta=0.0,
WakeLength=WakeLength,
ctrlSurf=None)
VMOPTS = VMopts(m, n, imageMeth, Mstar=1, Steady=True, KJMeth=True)
# run solver
Coeffs, Zeta, ZetaStar, Gamma, GammaStar, foo, Uext = Run_Cpp_Solver_VLM(
VMOPTS, VMINPUT)[0:7]
del foo
# unsteady params
mW = 10 * m
delS = 2 / m
# transform states/inputs
gam, gamW, gamPri, zeta, zetaW, zetaPri, nu, beam2aero = nln2linStates(
Zeta, ZetaStar, Gamma, GammaStar, Uext, m, n, mW, chord)
# generate linear model
E, F, G, C, D = genSSuvlm(gam, gamW, gamPri, zeta, zetaW, zetaPri, nu, m,