def geo_airfoil_high_angle(coords, ang, config):
# Calculo capa altura capa limite
height_bl = config.bl_first_cell * ((1 - math.pow(config.bl_prog_cell, config.bl_cell)) / (1 - config.bl_prog_cell))
# Regeneracion de puntos del Perfil
coords_airfoil = regenerate_points(coords, config.n_points, precision=6)
# Armado de puntos
start_point = 1 # Inicio de numeracion de puntos
# Analisis de separacion de puntos de borde de fuga, se debe tener un tratamiento de la malla diferente segun sea el caso.
if coords_airfoil[0] == coords_airfoil[len(coords_airfoil) - 1]:
separation = False
else:
separation = True
# Valores de X donde se realizara la division
separation_point = coords_airfoil.index(min(coords_airfoil)) # Separacion extrados-intrados
chord = coords_airfoil[0][0] - coords_airfoil[separation_point][0] # Determinar el valor de la cuerda
division = [chord*0.625 , chord*0.25 , chord*0.167 , chord*0.083] # Puntos de division, modificar con cuidado no agregar mas divisiones
with open(os.path.join("mesh", "perfil.geo"), "w") as file:
# Escritura de Puntos del perfil
count_point1 = start_point # count1 es sumador de puntos del perfil
coords_rotated = apply_rotation(coords_airfoil, ang) # Rotacion de puntos del perfil
file.write('// Puntos del Perfil\n')
for x, y in coords_rotated:
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point1, x, y))
count_point1 = count_point1 + 1
break_points_airfoil = found_division_index(coords_airfoil,division) # Busqueda de puntos de division del dominio
# Escritura de Puntos de la capa limite
if config.bl == True:
count_point2 = 1000 + start_point # count_point2 es sumador de puntos de la capa limite, se alinea la numeracion de puntos
# Calculo de puntos offset
coords_offset_bl = offset_airfoil(coords, height_bl,config.sharp)
coords_offset_bl = regenerate_points(coords_offset_bl, config.n_points, precision=6) # Regeneracion de puntos de la capa limite
coords_rotated_bl = apply_rotation(coords_offset_bl, ang) # Rotacion de puntos de la capa limite
file.write('\n// Boundary Layer Points\n')
for x, y in coords_rotated_bl:
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point2, x, y))
count_point2 = count_point2 + 1
# Escritura de Puntos del contorno exterior
count_point3 = 2000 + start_point # count_point3 es sumador de puntos de la capa limite, se alinea la numeracion de puntos
coords_offset_ol = offset_airfoil(coords, config.countour_airfoil_height,config.sharp) # Calculo de puntos offset
coords_offset_ol = regenerate_points(coords_offset_ol, config.n_points, precision=6) # Regeneracion de puntos del contorno exterior
coords_rotated_ol = apply_rotation(coords_offset_ol, ang) # Rotacion de puntos del contorno exterior
file.write('\n// Outer Layer Points\n')
for x, y in coords_rotated_ol:
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point3, x, y))
count_point3 = count_point3 + 1
# Armado de lineas
if config.bl == False:
# Armado de lineas del perfil
file.write('\n// Airfoil Lines\n')
count_line1 = 1 # count_line1 es sumador de lineas del perfil
for i in range(len(break_points_airfoil)-2):
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
# Procedimiento de cierre del perfil diferente segun exista o no separacion de puntos en el borde de fuga
i = len(break_points_airfoil) - 2
if separation == True:
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
else:
file.write("Line(%i) = {%i:%i,%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1], break_points_airfoil[0] + 1))
count_line1 = count_line1 + 1
# Armado de lineas del contorno exterior
file.write('\n// Outer Layer Lines\n')
count_line3 = 201 # count_line3 es sumador de lineas del contorno exterior
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i:%i};\n" % (count_line3, break_points_airfoil[i] + 2001, break_points_airfoil[i + 1] + 2001))
count_line3 = count_line3 + 1
# Armado de lineas de division de corte
file.write('\n// Division Lines\n')
count_line4 = 1101 # count_line4 es sumador de lineas de corte de perfil - contorno exterior
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 2001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
# El armado de la linea de division final es diferente segun exista separacion del borde de fuga o no
i = len(break_points_airfoil) - 1
if separation == True:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 2001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
else:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 2001, break_points_airfoil[0] + 1))
count_line4 = count_line4 + 1
# Armado de superficies
count_sup1 = 1 # count_sup1 es sumador de superficies
file.write("\n// Surfaces - Airfoil\n")
# Armado de Superficies del contorno del perfil
file.write("\n// Surfaces - Outer Layer\n")
for i in range(len(break_points_airfoil) - 1):
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, (i + 1), -(i + 1102) ,- (i + 201) , (i + 1101)))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite y Recombine de Superficies del contorno del perfil
file.write("\n// Surfaces Transfinite and Recombine - Outer Layer\n")
for i in range(1, len(break_points_airfoil)):
file.write(" Recombine Surface {%i};\n" % (i))
file.write(" Transfinite Surface {%i};\n" % (i))
else:
# Armado de lineas del perfil
file.write('\n// Airfoil Lines\n')
count_line1 = 1 # count_line1 es sumador de lineas del perfil
for i in range(len(break_points_airfoil)-2):
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
# Procedimiento de cierre del perfil diferente segun exista o no separacion de puntos en el borde de fuga
i = len(break_points_airfoil) - 2
if separation == True:
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
else:
file.write("Line(%i) = {%i:%i,%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1], break_points_airfoil[0] + 1))
count_line1 = count_line1 + 1
# Armado de lineas de la capa limite
file.write('\n// Boundary Layer Lines\n')
count_line2 = 101 # count_line2 es sumador de lineas de la capa limite
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i:%i};\n" % (count_line2, break_points_airfoil[i] + 1001, break_points_airfoil[i + 1] + 1001))
count_line2 = count_line2 + 1
# Armado de lineas del contorno exterior
file.write('\n// Outer Layer Lines\n')
count_line3 = 201 # count_line3 es sumador de lineas del contorno exterior
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i:%i};\n" % (count_line3, break_points_airfoil[i] + 2001, break_points_airfoil[i + 1] + 2001))
count_line3 = count_line3 + 1
# Armado de lineas de division de corte
file.write('\n// Division Lines Airfoil\n')
count_line4 = 1001 # count_line4 es sumador de lineas de corte de perfil - capa limite
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 1001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
# El armado de la linea de division final es diferente segun exista separacion del borde de fuga o no
i = len(break_points_airfoil) - 1
if separation == True:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 1001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
else:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 1001, break_points_airfoil[0] + 1))
count_line4 = count_line4 + 1
count_line5 = 1101 # count_line5 es sumador de lineas de corte de capa limite - contorno exterior
for i in range(len(break_points_airfoil)):
file.write("Line(%i) = {%i, %i};\n" % (count_line5, break_points_airfoil[i] + 2001, break_points_airfoil[i] + 1001))
count_line5 = count_line5 + 1
# Armado de superficies
count_sup1 = 1 # count_sup1 es sumador de superficies del contorno del perfil
file.write("\n// Surfaces - Airfoil\n")
# Armado de Superficies del contorno del perfil
file.write("\n// Surfaces - Boundary Layer\n")
for i in range(len(break_points_airfoil) - 1):
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, (i + 1), -(i + 1002) ,- (i + 101) , (i + 1001)))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite y Recombine de Superficies del contorno del perfil
file.write("\n// Surfaces Transfinite and Recombine - Boundary Layer\n")
for i in range(1, len(break_points_airfoil)):
file.write(" Recombine Surface {%i};\n" % (i))
file.write(" Transfinite Surface {%i};\n" % (i))
# Armado de Superficies del contorno del contorno exterior
file.write("\n// Surfaces - Outer Layer\n")
for i in range(len(break_points_airfoil) - 1):
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, (i + 101), -(i + 1102) ,- (i + 201) , (i + 1101)))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite y Recombine de Superficies del contorno exterior
file.write("\n// Surfaces Transfinite and Recombine - Outer Layer\n")
for i in range(len(break_points_airfoil), count_sup1):
file.write(" Recombine Surface {%i};\n" % (i))
file.write(" Transfinite Surface {%i};\n" % (i))
# Armado de Linea de union de borde de fuga abierto
if separation == True:
file.write("\n// Open Trailing Edge Line\n")
file.write("Line(%i) = {%i, %i};\n" % (count_line1, break_points_airfoil[len(break_points_airfoil)-1] + 1, break_points_airfoil[0] + 1))
count_line1 = count_line1 + 1
# Armado de puntos del dominio
file.write("\n// Domain Points\n")
count_point4 = 4001 # count_point4 es sumador de puntos del dominio
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, chord*0.25, config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4,-config.domain_height * chord, 0))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, chord*0.25, -config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), -config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), -config.domain_int_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), config.domain_int_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), config.domain_height * chord))
count_point4 = count_point4 + 1
# Armado de puntos del dominio interno
file.write("\n// Internal Domain Points\n")
count_point5 = 3001 # count_point5 es sumador de puntos del dominio interno
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point5, chord*0.25, config.domain_int_height * chord))
count_point5 = count_point5 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point5,-config.domain_int_height * chord, 0))
count_point5 = count_point5 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point5, chord*0.25, -config.domain_int_height * chord))
count_point5 = count_point5 + 1
# Armado de Lineas del dominio
file.write("\n// Domain Lines\n")
count_line7 = 1301 # count_line7 es sumador de lineas del borde exterior del dominio
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (10000, 0.25*chord, 0)) # Centro de la elipse
file.write("Ellipse(%i) = {%i, %i, %i, %i};\n" % (count_line7, 4001, 10000, 4002, 4002))
count_line7 = count_line7 + 1
file.write("Ellipse(%i) = {%i, %i, %i, %i};\n" % (count_line7, 4002, 10000, 4002, 4003))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 4003, 4004))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 4004, 4005))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 4005, 4006))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 4006, 4007))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 4007, 4001))
count_line7 = count_line7 + 1
# Armado de Lineas del dominio interno
file.write("\n// Internal Domain Lines\n")
count_line8 = 1401 # count_line7 es sumador de lineas del borde exterior del dominio
file.write("Line(%i) = {%i, %i};\n" % (count_line8, 4006, 3001))
count_line8 = count_line8 + 1
file.write("Ellipse(%i) = {%i, %i, %i, %i};\n" % (count_line8, 3001, 10000, 3002, 3002))
count_line8 = count_line8 + 1
file.write("Ellipse(%i) = {%i, %i, %i, %i};\n" % (count_line8, 3002, 10000, 3002, 3003))
count_line8 = count_line8 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line8, 3003, 4005))
count_line8 = count_line8 + 1
# Armado de Superficies del dominio interno
file.write('\n// Surface Internal Domain\n')
if separation == True:
if config.bl == True:
file.write("Line Loop(%i) = {1111, 1011, 11, -1001, -1101, 201, 202, 203, 204, 205, 206, 207, 208, 209, 210};\n" % (count_sup1))
count_sup1 = count_sup1 + 1
file.write("Curve Loop(%i) = {1401, 1402, 1403, 1404, 1305};\n" % (count_sup1))
file.write("Plane Surface(%i) = {%i, %i};\n" % (count_sup1 - 1, count_sup1, count_sup1 - 1))
count_sup1 = count_sup1 + 1
else:
file.write("Line Loop(%i) = {1111, 11, -1101, 201, 202, 203, 204, 205, 206, 207, 208, 209, 210};\n" % (count_sup1))
count_sup1 = count_sup1 + 1
file.write("Curve Loop(%i) = {1401, 1402, 1403, 1404, 1305};\n" % (count_sup1))
file.write("Plane Surface(%i) = {%i, %i};\n" % (count_sup1 - 1, count_sup1, count_sup1 - 1))
count_sup1 = count_sup1 + 1
else:
if config.bl == True:
file.write("Line Loop(%i) = {1111, 1011, -1001, -1101, 201, 202, 203, 204, 205, 206, 207, 208, 209, 210};\n" % (count_sup1))
count_sup1 = count_sup1 + 1
file.write("Curve Loop(%i) = {1401, 1402, 1403, 1404, 1305};\n" % (count_sup1))
file.write("Plane Surface(%i) = {%i, %i};\n" % (count_sup1 - 1, count_sup1, count_sup1 - 1))
count_sup1 = count_sup1 + 1
else:
file.write("Line Loop(%i) = {1111, -1101, 201, 202, 203, 204, 205, 206, 207, 208, 209, 210};\n" % (count_sup1, ))
count_sup1 = count_sup1 + 1
file.write("Curve Loop(%i) = {1401, 1402, 1403, 1404, 1305};\n" % (count_sup1))
file.write("Plane Surface(%i) = {%i, %i};\n" % (count_sup1 - 1, count_sup1, count_sup1 - 1))
count_sup1 = count_sup1 + 1
count_sup1 = count_sup1 + 1
# Armado de Superficies del dominio
file.write('\n// Surface Domain\n')
file.write("Curve Loop(%i) = {1306, 1307, 1301, 1302, 1303, 1304, -1404, -1403, -1402, -1401};\n" % (count_sup1))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1 - 2, count_sup1))
# Transfinite curvas airfoil - numero de celdas para el perfil
long_airfoil = dist_calc(coords_airfoil, 0, len(coords_airfoil)-1) # Longitud del contorno del perfil
transfin_airfoil = []
w = 0.2 # Cambio de peso en la cantidad de elementos entre el borde de ataque y el resto del perfil
weight = [(1-w),(1-w),(1-w),(1-w),(1+w*4),(1+w*4),(1-w),(1-w),(1-w),(1-w)]
for i in range(len(break_points_airfoil)-1):
long = dist_calc(coords_airfoil, break_points_airfoil[i], break_points_airfoil[i+1])
transfin = round((long/long_airfoil) * config.airfoil_cell * config.global_cell * weight[i]) + 1
if transfin < 2: # Minimo valor de celdas por seccion
transfin = 2
transfin_airfoil.append(transfin)
file.write('\n// Transfinite Airfoil\n')
if config.bl == True:
for i in range(len(transfin_airfoil)):
file.write("Transfinite Curve {%i, %i, %i} = %i Using Progression 1;\n" % (i + 1, i + 101, i + 201, transfin_airfoil[i]))
else:
for i in range(len(transfin_airfoil)):
file.write("Transfinite Curve {%i,%i} = %i Using Progression 1;\n" % (i + 1, i + 201,transfin_airfoil[i]))
# Transfinite capa limite
if config.bl == True:
file.write('\n// Transfinite Boundary Layer\n')
file.write("Transfinite Curve {%i, %i, %i, %i, %i, %i, %i, %i, %i, %i, %i} = %i Using Progression %2.3f;\n" % (tuple(range(1001,1012)) + (config.bl_cell + 1, 1/config.bl_prog_cell)))
# Transfinite contorno exterior
file.write('\n// Transfinite Outer Layer\n')
file.write("Transfinite Curve {%i, %i, %i, %i, %i, %i, %i, %i, %i, %i, %i} = %i Using Progression %2.3f;\n" % (tuple(range(1101,1112))+ ((config.ol_cell + 1) * config.global_cell, config.ol_prog_cell)))
# Transfinite curvas Dominio
file.write('\n// Transfinite Domain\n')
file.write("Transfinite Curve {%i, %i} = %i Using Progression 1;\n" % (1307, 1303, chord * (0.75 + config.wake_long) * config.domain_dens_cell * config.global_cell))
file.write("Transfinite Curve {%i, %i} = %i Using Progression 1;\n" % (1301, 1302, 0.5 * math.pi * config.domain_height * config.domain_dens_cell * config.global_cell))
file.write("Transfinite Curve {%i, %i} = %i Using Progression 1;\n" % (1304, 1306, (config.domain_height - config.domain_int_height) * config.domain_dens_cell * config.global_cell))
# Transfinite curvas Dominio interior
file.write('\n// Transfinite Interior Domain\n')
file.write("Transfinite Curve {%i, %i} = %i Using Progression 1;\n" % (1401, 1404, chord * (0.75 + config.wake_long) * config.domain_int_dens_cell * config.global_cell))
file.write("Transfinite Curve {%i, %i} = %i Using Progression 1;\n" % (1402, 1403, 0.5 * math.pi * config.domain_int_height * config.domain_int_dens_cell * config.global_cell))
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1305, 2 * config.domain_int_height * config.domain_int_dens_cell * config.global_cell))
# Definicion de las Physical Groups. No se pudo automatizar por tal caso se recomienda la version 4.5.6 del GMSH
file.write('\n// Physical Groups\n')
if config.bl == True:
file.write("ids [] = Extrude {0, 0, -0.1} {Surface{1:22}; Layers {1} ; Recombine;};\n")
file.write("""Physical Volume("Air") = {1:22};\n""")
if separation == True:
file.write("""Physical Surface("FrontandBack") = {21, 22, 20, 18, 17, 15, 12, 13, 16, 14, 11, 19, 9, 10, 1, 2, 3, 4, 8, 6, 7, 5, 1946, 1998, 1844, 1822, 1646, 1668, 1448, 1426, 1690, 1712, 1470, 1492, 1514, 1734, 1756, 1536, 1558, 1778, 1602, 1580, 1624, 1800};\n""")
file.write("""Physical Surface("Inlet") = {1969, 1973};\n""")
file.write("""Physical Surface("UpandDown") = {1965, 1977};\n""")
file.write("""Physical Surface("Outlet") = {1885, 1961, 1981};\n""")
file.write("""Physical Surface("Airfoil") = {1611, 1567, 1589, 1545, 1523, 1479, 1501, 1435, 1457, 1413, 1937};\n""")
else:
file.write("""Physical Surface("FrontandBack") = {21, 22, 20, 19, 18, 17, 16, 15, 14, 13, 12, 11, 1, 3, 2, 4, 5, 6, 7, 8, 9, 10, 1993, 1941, 1646, 1668, 1712, 1690, 1734, 1756, 1778, 1800, 1822, 1844, 1426, 1624, 1448, 1602, 1470, 1580, 1492, 1514, 1536, 1558};\n""")
file.write("""Physical Surface("Inlet") = {1968, 1964};\n""")
file.write("""Physical Surface("UpandDown") = {1960, 1972};\n""")
file.write("""Physical Surface("Outlet") = {1884, 1976, 1956};\n""")
file.write("""Physical Surface("Airfoil") = {1611, 1589, 1567, 1545, 1523, 1501, 1479, 1457, 1435, 1413};\n""")
else:
file.write("ids [] = Extrude {0, 0, -0.1} {Surface{1:12}; Layers {1} ; Recombine;};\n")
file.write("""Physical Volume("Air") = {1:12};\n""")
if separation == True:
file.write("""Physical Surface("FrontandBack") = {11, 12, 1, 10, 9, 8, 3, 2, 4, 5, 6, 7, 1716, 1768, 1426, 1448, 1470, 1492, 1514, 1536, 1558, 1580, 1602, 1624};\n""")
file.write("""Physical Surface("Inlet") = {1739, 1743};\n""")
file.write("""Physical Surface("UpandDown") = {1735, 1747};\n""")
file.write("""Physical Surface("Outlet") = {1731, 1751, 1663};\n""")
file.write("""Physical Surface("Airfoil") = {1435, 1413, 1457, 1479, 1501, 1523, 1545, 1567, 1589, 1611, 1711};\n""")
else:
file.write("""Physical Surface("FrontandBack") = {22, 11, 12, 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 1711, 1763, 1624, 1602, 1580, 1558, 1536, 1514, 1492, 1470, 1448, 1426};\n""")
file.write("""Physical Surface("Inlet") = {1734, 1738};\n""")
file.write("""Physical Surface("UpandDown") = {1730, 1742};\n""")
file.write("""Physical Surface("Outlet") = {1662, 1746, 1726};\n""")
file.write("""Physical Surface("Airfoil") = {1611, 1567, 1589, 1545, 1523, 1501, 1479, 1457, 1435, 1413};\n""")
def geo_airfoil_low_angle(coords, ang, config):
# Calculo capa altura capa limite
height_bl = config.bl_first_cell * ((1 - math.pow(config.bl_prog_cell, config.bl_cell)) / (1 - config.bl_prog_cell))
# Regeneracion de puntos del Perfil
coords_airfoil = regenerate_points(coords, config.n_points, precision=6)
# Armado de puntos
start_point = 1 # Inicio de numeracion de puntos
# Analisis de separacion de puntos de borde de fuga, se debe tener un tratamiento de la malla diferente segun sea el caso.
if coords_airfoil[0] == coords_airfoil[len(coords_airfoil) - 1]:
separation = False
else:
separation = True
# Valores de X donde se realizara la division
separation_point = coords_airfoil.index(min(coords_airfoil)) # Separacion extrados-intrados
chord = coords_airfoil[0][0] - coords_airfoil[separation_point][0] # Determinar el valor de la cuerda
division = [chord*0.625 , chord*0.25 , chord*0.167 , chord*0.083] # Puntos de division, modificar con cuidado no agregar mas divisiones
with open(os.path.join("mesh", "perfil.geo"), "w") as file:
# Escritura de Puntos del perfil
count_point1 = start_point # count1 es sumador de puntos del perfil
coords_rotated = apply_rotation(coords_airfoil, ang) # Rotacion de puntos del perfil
file.write('// Puntos del Perfil\n')
for x, y in coords_rotated:
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point1, x, y))
count_point1 = count_point1 + 1
break_points_airfoil = found_division_index(coords_airfoil,division) # Busqueda de puntos de division del dominio
# Escritura de Puntos de la capa limite
if config.bl == True:
count_point2 = 1000 + start_point # count_point2 es sumador de puntos de la capa limite, se alinea la numeracion de puntos
# Calculo de puntos offset
coords_offset_bl = offset_airfoil(coords, height_bl,config.sharp)
coords_offset_bl = regenerate_points(coords_offset_bl, config.n_points, precision=6) # Regeneracion de puntos de la capa limite
coords_rotated_bl = apply_rotation(coords_offset_bl, ang) # Rotacion de puntos de la capa limite
file.write('\n// Boundary Layer Points\n')
for x, y in coords_rotated_bl:
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point2, x, y))
count_point2 = count_point2 + 1
# Escritura de Puntos del contorno exterior
count_point3 = 2000 + start_point # count_point3 es sumador de puntos de la capa limite, se alinea la numeracion de puntos
coords_offset_ol = offset_airfoil(coords, config.countour_airfoil_height,config.sharp) # Calculo de puntos offset
coords_offset_ol = regenerate_points(coords_offset_ol, config.n_points, precision=6) # Regeneracion de puntos del contorno exterior
coords_rotated_ol = apply_rotation(coords_offset_ol, ang) # Rotacion de puntos del contorno exterior
file.write('\n// Outer Layer Points\n')
for x, y in coords_rotated_ol:
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point3, x, y))
count_point3 = count_point3 + 1
# Armado de lineas
if config.bl == False:
# Armado de lineas del perfil
file.write('\n// Airfoil Lines\n')
count_line1 = 1 # count_line1 es sumador de lineas del perfil
for i in range(len(break_points_airfoil)-2):
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
# Procedimiento de cierre del perfil diferente segun exista o no separacion de puntos en el borde de fuga
i = len(break_points_airfoil) - 2
if separation == True:
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
else:
file.write("Line(%i) = {%i:%i,%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1], break_points_airfoil[0] + 1))
count_line1 = count_line1 + 1
# Armado de lineas del contorno exterior
file.write('\n// Outer Layer Lines\n')
count_line3 = 201 # count_line3 es sumador de lineas del contorno exterior
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i:%i};\n" % (count_line3, break_points_airfoil[i] + 2001, break_points_airfoil[i + 1] + 2001))
count_line3 = count_line3 + 1
# Armado de lineas de division de corte
file.write('\n// Division Lines\n')
count_line4 = 1101 # count_line4 es sumador de lineas de corte de perfil - contorno exterior
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 2001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
# El armado de la linea de division final es diferente segun exista separacion del borde de fuga o no
i = len(break_points_airfoil) - 1
if separation == True:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 2001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
else:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 2001, break_points_airfoil[0] + 1))
count_line4 = count_line4 + 1
# Armado de superficies
count_sup1 = 1 # count_sup1 es sumador de superficies
file.write("\n// Surfaces - Airfoil\n")
# Armado de Superficies del contorno del perfil
file.write("\n// Surfaces - Outer Layer\n")
for i in range(len(break_points_airfoil) - 1):
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, (i + 1), -(i + 1102) ,- (i + 201) , (i + 1101)))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite y Recombine de Superficies del contorno del perfil
file.write("\n// Surfaces Transfinite and Recombine - Outer Layer\n")
for i in range(1, len(break_points_airfoil)):
file.write(" Recombine Surface {%i};\n" % (i))
file.write(" Transfinite Surface {%i};\n" % (i))
else:
# Armado de lineas del perfil
file.write('\n// Airfoil Lines\n')
count_line1 = 1 # count_line1 es sumador de lineas del perfil
for i in range(len(break_points_airfoil)-2):
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
# Procedimiento de cierre del perfil diferente segun exista o no separacion de puntos en el borde de fuga
i = len(break_points_airfoil) - 2
if separation == True:
file.write("Line(%i) = {%i:%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1] + 1))
count_line1 = count_line1 + 1
else:
file.write("Line(%i) = {%i:%i,%i};\n" % (count_line1, break_points_airfoil[i] + 1, break_points_airfoil[i + 1], break_points_airfoil[0] + 1))
count_line1 = count_line1 + 1
# Armado de lineas de la capa limite
file.write('\n// Boundary Layer Lines\n')
count_line2 = 101 # count_line2 es sumador de lineas de la capa limite
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i:%i};\n" % (count_line2, break_points_airfoil[i] + 1001, break_points_airfoil[i + 1] + 1001))
count_line2 = count_line2 + 1
# Armado de lineas del contorno exterior
file.write('\n// Outer Layer Lines\n')
count_line3 = 201 # count_line3 es sumador de lineas del contorno exterior
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i:%i};\n" % (count_line3, break_points_airfoil[i] + 2001, break_points_airfoil[i + 1] + 2001))
count_line3 = count_line3 + 1
# Armado de lineas de division de corte
file.write('\n// Division Lines Airfoil\n')
count_line4 = 1001 # count_line4 es sumador de lineas de corte de perfil - capa limite
for i in range(len(break_points_airfoil)-1):
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 1001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
# El armado de la linea de division final es diferente segun exista separacion del borde de fuga o no
i = len(break_points_airfoil) - 1
if separation == True:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 1001, break_points_airfoil[i] + 1))
count_line4 = count_line4 + 1
else:
file.write("Line(%i) = {%i, %i};\n" % (count_line4, break_points_airfoil[i] + 1001, break_points_airfoil[0] + 1))
count_line4 = count_line4 + 1
count_line5 = 1101 # count_line5 es sumador de lineas de corte de capa limite - contorno exterior
for i in range(len(break_points_airfoil)):
file.write("Line(%i) = {%i, %i};\n" % (count_line5, break_points_airfoil[i] + 2001, break_points_airfoil[i] + 1001))
count_line5 = count_line5 + 1
# Armado de superficies
count_sup1 = 1 # count_sup1 es sumador de superficies del contorno del perfil
file.write("\n// Surfaces - Airfoil\n")
# Armado de Superficies del contorno del perfil
file.write("\n// Surfaces - Boundary Layer\n")
for i in range(len(break_points_airfoil) - 1):
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, (i + 1), -(i + 1002) ,- (i + 101) , (i + 1001)))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite y Recombine de Superficies del contorno del perfil
file.write("\n// Surfaces Transfinite and Recombine - Boundary Layer\n")
for i in range(1, len(break_points_airfoil)):
file.write(" Recombine Surface {%i};\n" % (i))
file.write(" Transfinite Surface {%i};\n" % (i))
# Armado de Superficies del contorno del contorno exterior
file.write("\n// Surfaces - Outer Layer\n")
for i in range(len(break_points_airfoil) - 1):
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, (i + 101), -(i + 1102) ,- (i + 201) , (i + 1101)))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite y Recombine de Superficies del contorno exterior
file.write("\n// Surfaces Transfinite and Recombine - Outer Layer\n")
for i in range(len(break_points_airfoil), count_sup1):
file.write(" Recombine Surface {%i};\n" % (i))
file.write(" Transfinite Surface {%i};\n" % (i))
# Armado de puntos del dominio - No estela
file.write("\n// Domain Points\n")
count_point4 = 3001 # count_point4 es sumador de puntos del dominio
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, coords_rotated_ol[0][0], config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, chord*0.25, config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4,-config.domain_height * chord, 0))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, chord*0.25, -config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, coords_rotated_ol[len(coords_rotated_ol)-1][0], -config.domain_height * chord))
count_point4 = count_point4 + 1
# Armado de Lineas del dominio - No estela
file.write("\n// Domain Lines\n")
count_line7 = 1301 # count_line7 es sumador de lineas del borde exterior del dominio
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3001, 3002))
count_line7 = count_line7 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (10000, 0.25*chord, 0)) # Centro de la elipse
file.write("Ellipse(%i) = {%i, %i, %i, %i};\n" % (count_line7, 3002, 10000, 3003, 3003))
count_line7 = count_line7 + 1
file.write("Ellipse(%i) = {%i, %i, %i, %i};\n" % (count_line7, 3003, 10000, 3003, 3004))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3004, 3005))
count_line7 = count_line7 + 1
# Armado de Lineas de division del dominio - No estela
file.write("\n// Domain Division Lines\n")
count_line6 = 1201 # count_line6 es sumador de lineas de corte de contorno exterior-dominio
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3001, break_points_airfoil[0] + 2001))
count_line6 = count_line6 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3002, break_points_airfoil[2] + 2001))
count_line6 = count_line6 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3003, break_points_airfoil[5] + 2001))
count_line6 = count_line6 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3004, break_points_airfoil[8] + 2001))
count_line6 = count_line6 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3005, break_points_airfoil[10] + 2001))
count_line6 = count_line6 + 1
# Armado de Superficies, transfinite y recombine del contorno del contorno exterior. Se reutiliza count_sup1
count_sup1 = count_sup1 + 1
file.write("\n// Surfaces and Transfinite and Recombine - Domain\n")
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i};\n" % (count_sup1, 201, 202, -1202, -1301, 1201))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i}={%i, %i, %i, %i};\n" % (count_sup1, break_points_airfoil[0] + 2001, break_points_airfoil[2] + 2001, 3002, 3001))
count_sup1 = count_sup1 + 1
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i, %i};\n" % (count_sup1, 203, 204, 205, -1203, -1302, 1202))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i}={%i, %i, %i, %i};\n" % (count_sup1, break_points_airfoil[2] + 2001, break_points_airfoil[5] + 2001, 3003, 3002))
count_sup1 = count_sup1 + 1
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i, %i};\n" % (count_sup1, 206, 207, 208, -1204, -1303, 1203))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i}={%i, %i, %i, %i};\n" % (count_sup1, break_points_airfoil[5] + 2001, break_points_airfoil[8] + 2001, 3004, 3003))
count_sup1 = count_sup1 + 1
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i};\n" % (count_sup1, 209, 210, -1205, -1304, 1204))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i}={%i, %i, %i, %i};\n" % (count_sup1, break_points_airfoil[8] + 2001, break_points_airfoil[10] + 2001, 3005, 3004))
count_sup1 = count_sup1 + 1
# Armado de puntos de la estela (se reutiliza el contador count_point4)
file.write("\n// Wake Points;\n")
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), -config.domain_height * chord))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), coords_rotated_ol[len(coords_offset_ol)-1][1] + config.wake_long * math.sin(np.radians(config.adj_wake))))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), coords_rotated_ol[0][1] + config.wake_long * math.sin(np.radians(config.adj_wake))))
count_point4 = count_point4 + 1
file.write("Point(%i) = { %3.6f, %3.6f, 0.0};\n" % (count_point4, (chord * (1 + config.wake_long)), config.domain_height * chord))
count_point4 = count_point4 + 1
# Armado de Lineas de la Estela
file.write("\n// Wake Lines\n")
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3006, 3005))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3006, 3007))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3007, 3008))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3009, 3008))
count_line7 = count_line7 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line7, 3009, 3001))
count_line7 = count_line7 + 1
# Armado de Lineas de division de la Estela (se reutiliza el contador count_line6)
file.write("\n// Wake Division Lines\n")
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3007, break_points_airfoil[len(break_points_airfoil)-1] + 2001))
count_line6 = count_line6 + 1
file.write("Line(%i) = {%i, %i};\n" % (count_line6, 3008, break_points_airfoil[0] + 2001))
count_line6 = count_line6 + 1
# Armado de Linea de union de borde de fuga abierto
if separation == True:
file.write("\n// Open Trailing Edge Line\n")
file.write("Line(%i) = {%i, %i};\n" % (count_line1, break_points_airfoil[len(break_points_airfoil)-1] + 1, break_points_airfoil[0] + 1))
# Armado de Superficies, transfinite y recombine de la estela (se reutiliza el contador count_sup1)
file.write("\n// Surfaces and Transfinite and Recombine - Wake\n")
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, 1305, 1205, -1206, -1306))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i};\n" % (count_sup1))
count_sup1 = count_sup1 + 1
# Proceso diferente de armado para borde de fuga abierto y existencia de capa limite
if separation == True:
if config.bl == True:
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i, %i, %i, %i};\n" % (count_sup1, -1207, -1307, 1206, 1111, 1011, 11, -1001, -1101))
else:
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i, %i};\n" % (count_sup1, -1207, -1307, 1206, 1111, 11, -1101))
else:
if config.bl == True:
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i, %i, %i};\n" % (count_sup1, -1207, -1307, 1206, 1111, 1011, -1001, -1101))
else:
file.write("Line Loop(%i) = {%i, %i, %i, %i, %i};\n" % (count_sup1, -1207, -1307, 1206, 1111, -1101))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i} = {%i, %i, %i,%i};\n" % (count_sup1, 3008, 3007, break_points_airfoil[0] + 2001, break_points_airfoil[len(break_points_airfoil)-1] + 2001))
count_sup1 = count_sup1 + 1
file.write("Line Loop(%i) = {%i, %i, %i, %i};\n" % (count_sup1, 1207, -1201, -1309, 1308))
file.write("Plane Surface(%i) = {%i};\n" % (count_sup1, count_sup1))
file.write("Recombine Surface {%i};\n" % (count_sup1))
file.write("Transfinite Surface {%i};\n" % (count_sup1))
count_sup1 = count_sup1 + 1
# Transfinite curvas airfoil - numero de celdas para el perfil
long_airfoil = dist_calc(coords_airfoil, 0, len(coords_airfoil)-1) # Longitud del contorno del perfil
transfin_airfoil = []
w = 0.2 # Cambio de peso en la cantidad de elementos entre el borde de ataque y el resto del perfil
weight = [(1-w),(1-w),(1-w),(1-w),(1+w*4),(1+w*4),(1-w),(1-w),(1-w),(1-w)]
for i in range(len(break_points_airfoil)-1):
long = dist_calc(coords_airfoil, break_points_airfoil[i], break_points_airfoil[i+1])
transfin = round((long/long_airfoil) * config.airfoil_cell * config.global_cell * weight[i]) + 1
if transfin < 2: # Minimo valor de celdas por seccion
transfin = 2
transfin_airfoil.append(transfin)
file.write('\n// Transfinite Airfoil\n')
if config.bl == True:
for i in range(len(transfin_airfoil)):
file.write("Transfinite Curve {%i, %i, %i} = %i Using Progression 1;\n" % (i + 1, i + 101, i + 201, transfin_airfoil[i]))
else:
for i in range(len(transfin_airfoil)):
file.write("Transfinite Curve {%i,%i} = %i Using Progression 1;\n" % (i + 1, i + 201,transfin_airfoil[i]))
# Transfinite curvas dominio - No estela
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1301, transfin_airfoil[0] + transfin_airfoil[1] - 1))
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1302, transfin_airfoil[2] + transfin_airfoil[3] + transfin_airfoil[4] - 2))
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1303, transfin_airfoil[5] + transfin_airfoil[6] + transfin_airfoil[7] - 2))
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1304, transfin_airfoil[8] + transfin_airfoil[9] - 1))
# Transfinite curvas Estela
file.write('\n// Transfinite Wake\n')
file.write("Transfinite Curve {%i, %i, %i, %i} = %i Using Progression %2.3f;\n" % (1309, 1207, 1206, 1305, (config.wake_div_cell + 1) * config.global_cell , config.wake_prog_cell))
# Transfinite capa limite
if config.bl == True:
file.write('\n// Transfinite Boundary Layer\n')
file.write("Transfinite Curve {%i, %i, %i, %i, %i, %i, %i, %i, %i, %i, %i} = %i Using Progression %2.3f;\n" % (tuple(range(1001,1012)) + (config.bl_cell + 1, 1/config.bl_prog_cell)))
# Transfinite contorno exterior
file.write('\n// Transfinite Outer Layer\n')
file.write("Transfinite Curve {%i, %i, %i, %i, %i, %i, %i, %i, %i, %i, %i} = %i Using Progression %2.3f;\n" % (tuple(range(1101,1112))+ ((config.ol_cell + 1) * config.global_cell, config.ol_prog_cell)))
# Transfinite contorno exterior
file.write('\n// Transfinite Outer Domain\n')
file.write("Transfinite Curve {%i, %i, %i, %i, %i, %i, %i} = %i Using Progression %2.3f;\n" % (1308, 1201, 1202, 1203, 1204, 1205, 1306, (config.domain_cell + 1) * config.global_cell, config.domain_prog_cell))
# Transfinite Estela Perfil
file.write('\n// Transfinite Airfoil Wake\n')
if separation == True:
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (11, 2))
if config.bl == True:
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1307, (config.bl_cell + 1) * 2 + (config.ol_cell * config.global_cell + 1) * 2 - 2 ))
else:
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1307, (config.ol_cell * config.global_cell +1 ) * 2))
else:
if config.bl == True:
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1307, (config.bl_cell +1) * 2 + (config.ol_cell * config.global_cell+ 1 ) * 2 - 3))
else:
file.write("Transfinite Curve {%i} = %i Using Progression 1;\n" % (1307, (config.ol_cell * config.global_cell + 1) * 2 - 1))
# Definicion de las Physical Groups. No se pudo automatizar por tal caso se recomienda la version 4.5.6 del GMSH
file.write('\n// Physical Groups\n')
if config.bl == True:
file.write("ids [] = Extrude {0, 0, -0.1} {Surface{1:28}; Layers {1} ; Recombine;};\n")
file.write("""Physical Volume("Air") = {1:27};\n""")
if separation == True:
file.write("""Physical Surface("FrontandBack") = {1953, 1808, 1776, 1931, 1889, 1867, 1840, 1749, 1727, 1705, 1683, 1661, 1639, 1617, 1595, 1573, 1551, 1331, 1353, 1375, 1397, 1419, 1441, 1463, 1485, 1529, 1507, 24, 26, 25, 28, 27, 22, 23, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 10, 1, 2, 3, 4, 5, 6, 7, 8, 9};\n""")
file.write("""Physical Surface("Inlet") = {1835, 1803};\n""")
file.write("""Physical Surface("UpandDown") = {1771, 1948, 1876, 1862};\n""")
file.write("""Physical Surface("Outlet") = {1952, 1906, 1888};\n""")
file.write("""Physical Surface("Airfoil") = {1516, 1494, 1472, 1450, 1340, 1318, 1362, 1384, 1406, 1428, 1922};\n""")
else:
file.write("""Physical Surface("FrontandBack") = {23, 22, 28, 27, 26, 25, 24, 20, 19, 18, 17, 16, 15, 14, 13, 12, 11, 1, 2, 3, 4, 5, 6, 7, 9, 8, 10, 1889, 1948, 1926, 1776, 1808, 1840, 1867, 1661, 1617, 1639, 1683, 1705, 1595, 1727, 1573, 1551, 1749, 1529, 1507, 1463, 1485, 1441, 1419, 1375, 1331, 1397, 1353};\n""")
file.write("""Physical Surface("Inlet") = {1803, 1835};\n""")
file.write("""Physical Surface("UpandDown") = {1943, 1771, 1876, 1862};\n""")
file.write("""Physical Surface("Outlet") = {1947, 1905, 1888};\n""")
file.write("""Physical Surface("Airfoil") = {1494, 1318, 1340, 1516, 1362, 1406, 1384, 1428, 1472, 1450};\n""")
#file.write("""Physical Surface("FrontandBack") = {ids[{1:115:6, 128, 136, 144, 151, 157, 167, 60:114:6,120,127,128,135,143,150,156,166}],28};\n""") Metodo alternativo y automatico pero largo de realizar
else:
file.write("ids [] = Extrude {0, 0, -0.1} {Surface{1:18}; Layers {1} ; Recombine;};\n")
file.write("""Physical Volume("Air") = {1:18};\n""")
if separation == True:
file.write("""Physical Surface("FrontandBack") = {13, 12, 18, 14, 15, 17, 16, 5, 1, 7, 9, 8, 2, 10, 6, 4, 3, 1620, 1669, 1588, 1701, 1647, 1723, 1556, 1529, 1485, 1441, 1463, 1507, 1331, 1353, 1375, 1397, 1419};\n""")
file.write("""Physical Surface("Inlet") = {1583, 1615};\n""")
file.write("""Physical Surface("UpandDown") = {1656, 1642, 1718, 1551};\n""")
file.write("""Physical Surface("Outlet") = {1684, 1722, 1668};\n""")
file.write("""Physical Surface("Airfoil") = {1450, 1472, 1494, 1428, 1516, 1318, 1340, 1362, 1384, 1406, 1696};\n""")
else:
file.write("""Physical Surface("FrontandBack") = {18, 12, 13, 14, 15, 16, 17, 5, 6, 7, 8, 9, 10, 1, 2, 3, 4, 1620, 1588, 1718, 1556, 1696, 1669, 1647, 1529, 1485, 1507, 1441, 1463, 1419, 1397, 1375, 1353, 1331};\n""")
file.write("""Physical Surface("Inlet") = {1615, 1583};\n""")
file.write("""Physical Surface("UpandDown") = {1713, 1551, 1656, 1642};\n""")
file.write("""Physical Surface("Outlet") = {1717, 1668, 1683};\n""")
file.write("""Physical Surface("Airfoil") = {1494, 1472, 1450, 1428, 1406, 1340, 1362, 1384, 1318, 1516};\n""")
# Angulo de ataque en grados.
ang = 0
coords = NACA_4D('4415', 1, config.n_points, separation=True)
#coords=read_airfoil('goe05k.dat')
#coords=read_airfoil('NREL-S812.dat')
'''
INICIO DE LA FUNCION
'''
#def geo_airfoil_low_angle(coords, angle, config)
# Calculo capa altura capa limite
height_bl = config.bl_first_cell * (
(1 - math.pow(config.bl_prog_cell, config.bl_cell)) /
(1 - config.bl_prog_cell))
# Regeneracion de puntos del Perfil
coords_airfoil = regenerate_points(coords, config.n_points, precision=6)
# Armado de puntos
start_point = 1 # Inicio de numeracion de puntos
# Analisis de separacion de puntos de borde de fuga, se debe tener un tratamiento de la malla diferente segun sea el caso.
if coords_airfoil[0] == coords_airfoil[len(coords_airfoil) - 1]:
separation = False
else:
separation = True
# Valores de X donde se realizara la division
separation_point = coords_airfoil.index(
min(coords_airfoil)) # Separacion extrados-intrados
chord = coords_airfoil[0][0] - coords_airfoil[separation_point][
0] # Determinar el valor de la cuerda
minimum = coordsoffset.index( min(coordsoffset) )
for i in range( len(coordsoffset)-1 ):
if i<minimum:
if coordsoffset[i][0] - coordsoffset[i+1][0]<0:
index.append(i)
loop = 1
else:
if coordsoffset[i][0] - coordsoffset[i+1][0]>0:
index.append(i)
loop = 1
# Eliminación de puntos
if loop == 1:
for i in range( len(index)-1 ,-1 ,-1 ):
coordsoffset.pop( index[i] )
XX = [coords[x][0] for x in range(len(coords))]
YY = [coords[x][1] for x in range(len(coords))]
plt.axis('equal')
plt.plot(XX,YY,'*')
coordsoffset = regenerate_points(coordsoffset, n_points=200, precision=6)
XXX = [coordsoffset[x][0] for x in range(len(coordsoffset))]
YYY = [coordsoffset[x][1] for x in range(len(coordsoffset))]
plt.plot(XXX,YYY,'*')
#.plot(tita,ZZ,'*')
plt.show()