# WingGeometry spw = 2 numpos = 50 z_fac_1 = -0.3 z_fac_2 = -0.7 y = np.sin(np.linspace(0, np.pi / 2, numpos)) * spw / 2 x = [0.0 for _ in y] z = [i ** 2 * z_fac_1 + i ** 6 * z_fac_2 for i in y] mirror = lambda xyz: [xyz[0], -xyz[1], xyz[2]] wing = list(zip(x, y, z)) wing = list(map(mirror, wing))[::-1] + list(wing)[1:] wing = [paraBEM.Vector3(*i) for i in wing] # LiftingLine lifting_line = LiftingLine(wing) lifting_line.v_inf = paraBEM.Vector3(1, 0, 0) lifting_line.solve_for_best_gamma(1) gamma = [i.best_gamma for i in lifting_line.segments] gamma_max = max(gamma) # Plot gamma_el = lambda y: gamma_max * (1 - (y / spw * 2) ** 2) ** (1 / 2) mids = [[i.mids.x, i.mids.y, i.mids.z] for i in lifting_line.segments] x, y, z = zip(*mids) fig = plt.figure() ax1 = fig.add_subplot(3, 1, 1) ax1.plot(y, z) ax2 = fig.add_subplot(3, 1, 2)
symmetric=False,
distribution=Distribution.from_cos_2_distribution,
num_average=0,
)
case = DirichletDoublet0Source0Case3(panels, trailing_edge)
case.v_inf = paraBEM.Vector3(*glider2d.v_inf)
case.create_wake(1000, 100)
case.trefftz_cut_pos = case.v_inf * 20
case.run()
gamma_pan = -np.array([edge.vorticity for edge in case.trailing_edge])
######################LiftingLine############################
te_line = [paraBEM.Vector3(0, i.y, i.z) for i in trailing_edge]
lifting_line = LiftingLine(te_line)
lifting_line.v_inf = case.v_inf
lifting_line.solve_for_best_gamma(1)
gamma = [line.best_gamma for line in lifting_line.segments]
gamma_max = max(gamma)
gamma_pan *= gamma_max / max(gamma_pan)
line_segment_length = np.array([0] + [line.b for line in lifting_line.segments])
line_segment_length = line_segment_length.cumsum()
spw = max(line_segment_length)
spw_proj = abs(lifting_line.segments[0].v1.y) * 2
line_segment_length -= spw / 2
#####################Plottin#################################
# WingGeometry spw = 2 numpos = 50 z_fac_1 = -0.3 z_fac_2 = -0.7 y = np.sin(np.linspace(0, np.pi/2, numpos)) * spw/2 x = [0. for _ in y] z = [i**2 * z_fac_1 + i**6 * z_fac_2 for i in y] mirror = lambda xyz: [xyz[0], -xyz[1], xyz[2]] wing = list(zip(x, y, z)) wing = list(map(mirror, wing))[::-1] + list(wing)[1:] wing = [paraBEM.Vector3(*i) for i in wing] # LiftingLine lifting_line = LiftingLine(wing) lifting_line.v_inf = paraBEM.Vector3(1, 0, 0) lifting_line.solve_for_best_gamma(1) gamma = [i.best_gamma for i in lifting_line.segments] gamma_max = max(gamma) # Plot gamma_el = lambda y: gamma_max * (1 - (y / spw * 2)**2)**(1 / 2) mids = [[i.mids.x, i.mids.y, i.mids.z] for i in lifting_line.segments] x, y, z = zip(*mids) fig = plt.figure() ax1 = fig.add_subplot(3, 1, 1) ax1.plot(y, z) ax2 = fig.add_subplot(3, 1, 2)
midribs=0,
profile_numpoints=20,
symmetric=False,
distribution=Distribution.from_cos_2_distribution,
num_average=0)
case = DirichletDoublet0Source0Case3(panels, trailing_edge)
case.v_inf = paraBEM.Vector3(*glider2d.v_inf)
case.create_wake(1000, 100)
case.trefftz_cut_pos = case.v_inf * 20
case.run()
gamma_pan = -np.array([edge.vorticity for edge in case.trailing_edge])
######################LiftingLine############################
te_line = [paraBEM.Vector3(0, i.y, i.z) for i in trailing_edge]
lifting_line = LiftingLine(te_line)
lifting_line.v_inf = case.v_inf
lifting_line.solve_for_best_gamma(1)
gamma = [line.best_gamma for line in lifting_line.segments]
gamma_max = max(gamma)
gamma_pan *= gamma_max / max(gamma_pan)
line_segment_length = np.array([0] +
[line.b for line in lifting_line.segments])
line_segment_length = line_segment_length.cumsum()
spw = max(line_segment_length)
spw_proj = abs(lifting_line.segments[0].v1.y) * 2
line_segment_length -= spw / 2
#####################Plottin#################################