// Airfoil suction side
airfoil_s_lc = 1.000000e-02;
Point(1) = {1.00000000, 0.00000000, 0.00000000, airfoil_s_lc/2};
Point(2) = {0.99939800, 0.00012800, 0.00000000, airfoil_s_lc};
Point(3) = {0.99759200, 0.00051000, 0.00000000, airfoil_s_lc};
Point(4) = {0.99458800, 0.00113700, 0.00000000, airfoil_s_lc};
Point(5) = {0.99039300, 0.00200100, 0.00000000, airfoil_s_lc};
Point(6) = {0.98501600, 0.00309200, 0.00000000, airfoil_s_lc};
Point(7) = {0.97847000, 0.00440100, 0.00000000, airfoil_s_lc};
Point(8) = {0.97077200, 0.00591500, 0.00000000, airfoil_s_lc};
Point(9) = {0.96194000, 0.00762200, 0.00000000, airfoil_s_lc};
Point(10) = {0.95199500, 0.00950800, 0.00000000, airfoil_s_lc};
Point(11) = {0.94096100, 0.01156200, 0.00000000, airfoil_s_lc};
Point(12) = {0.92886400, 0.01376900, 0.00000000, airfoil_s_lc};
Point(13) = {0.91573500, 0.01611300, 0.00000000, airfoil_s_lc};
Point(14) = {0.90160400, 0.01858000, 0.00000000, airfoil_s_lc};
Point(15) = {0.88650500, 0.02115300, 0.00000000, airfoil_s_lc};
Point(16) = {0.87047600, 0.02381700, 0.00000000, airfoil_s_lc};
Point(17) = {0.85355300, 0.02655400, 0.00000000, airfoil_s_lc};
Point(18) = {0.83577900, 0.02934700, 0.00000000, airfoil_s_lc};
Point(19) = {0.81719700, 0.03217600, 0.00000000, airfoil_s_lc};
Point(20) = {0.79785000, 0.03501700, 0.00000000, airfoil_s_lc};
Point(21) = {0.77778500, 0.03784700, 0.00000000, airfoil_s_lc};
Point(22) = {0.75705100, 0.04064100, 0.00000000, airfoil_s_lc};
Point(23) = {0.73569800, 0.04337700, 0.00000000, airfoil_s_lc};
Point(24) = {0.71377800, 0.04602900, 0.00000000, airfoil_s_lc};
Point(25) = {0.69134200, 0.04857500, 0.00000000, airfoil_s_lc};
Point(26) = {0.66844500, 0.05099300, 0.00000000, airfoil_s_lc};
Point(27) = {0.64514200, 0.05325800, 0.00000000, airfoil_s_lc};
Point(28) = {0.62149000, 0.05534400, 0.00000000, airfoil_s_lc};
Point(29) = {0.59754500, 0.05721800, 0.00000000, airfoil_s_lc};
Point(30) = {0.57336500, 0.05884500, 0.00000000, airfoil_s_lc};
Point(31) = {0.54900900, 0.06019400, 0.00000000, airfoil_s_lc};
Point(32) = {0.52453400, 0.06125400, 0.00000000, airfoil_s_lc};
Point(33) = {0.50000000, 0.06202900, 0.00000000, airfoil_s_lc};
Point(34) = {0.47546600, 0.06253000, 0.00000000, airfoil_s_lc};
Point(35) = {0.45099100, 0.06277400, 0.00000000, airfoil_s_lc};
Point(36) = {0.42663500, 0.06277900, 0.00000000, airfoil_s_lc};
Point(37) = {0.40245500, 0.06256200, 0.00000000, airfoil_s_lc};
Point(38) = {0.37851000, 0.06213300, 0.00000000, airfoil_s_lc};
Point(39) = {0.35485800, 0.06149700, 0.00000000, airfoil_s_lc};
Point(40) = {0.33155500, 0.06066000, 0.00000000, airfoil_s_lc};
Point(41) = {0.30865800, 0.05962900, 0.00000000, airfoil_s_lc};
Point(42) = {0.28622200, 0.05841400, 0.00000000, airfoil_s_lc};
Point(43) = {0.26430200, 0.05702600, 0.00000000, airfoil_s_lc};
Point(44) = {0.24294900, 0.05547000, 0.00000000, airfoil_s_lc};
Point(45) = {0.22221500, 0.05375300, 0.00000000, airfoil_s_lc};
Point(46) = {0.20215000, 0.05188500, 0.00000000, airfoil_s_lc};
Point(47) = {0.18280300, 0.04987400, 0.00000000, airfoil_s_lc};
Point(48) = {0.16422100, 0.04772900, 0.00000000, airfoil_s_lc};
Point(49) = {0.14644700, 0.04545700, 0.00000000, airfoil_s_lc};
Point(50) = {0.12952400, 0.04307100, 0.00000000, airfoil_s_lc};
Point(51) = {0.11349500, 0.04058500, 0.00000000, airfoil_s_lc};
Point(52) = {0.09839600, 0.03801100, 0.00000000, airfoil_s_lc};
Point(53) = {0.08426500, 0.03536000, 0.00000000, airfoil_s_lc};
Point(54) = {0.07113600, 0.03264400, 0.00000000, airfoil_s_lc};
Point(55) = {0.05903900, 0.02987400, 0.00000000, airfoil_s_lc};
Point(56) = {0.04800500, 0.02706200, 0.00000000, airfoil_s_lc};
Point(57) = {0.03806000, 0.02421900, 0.00000000, airfoil_s_lc};
Point(58) = {0.02922800, 0.02134800, 0.00000000, airfoil_s_lc};
Point(59) = {0.02153000, 0.01844100, 0.00000000, airfoil_s_lc/2};
Point(60) = {0.01498400, 0.01548900, 0.00000000, airfoil_s_lc/2};
Point(61) = {0.00960700, 0.01248000, 0.00000000, airfoil_s_lc/2};
Point(62) = {0.00541200, 0.00941600, 0.00000000, airfoil_s_lc/2};
Point(63) = {0.00240800, 0.00630600, 0.00000000, airfoil_s_lc/2};
Point(64) = {0.00060200, 0.00316500, 0.00000000, airfoil_s_lc/2};
Point(65) = {0.00000000, 0.00000000, 0.00000000, airfoil_s_lc/2};
// Airfoil pressure side
airfoil_p_lc = 1.000000e-02;
Point(66) = {0.00060200, -0.00316000, 0.00000000, airfoil_p_lc/2};
Point(67) = {0.00240800, -0.00630800, 0.00000000, airfoil_p_lc/2};
Point(68) = {0.00541200, -0.00944300, 0.00000000, airfoil_p_lc/2};
Point(69) = {0.00960700, -0.01255900, 0.00000000, airfoil_p_lc/2};
Point(70) = {0.01498400, -0.01564900, 0.00000000, airfoil_p_lc/2};
Point(71) = {0.02153000, -0.01870700, 0.00000000, airfoil_p_lc/2};
Point(72) = {0.02922800, -0.02172200, 0.00000000, airfoil_p_lc};
Point(73) = {0.03806000, -0.02468500, 0.00000000, airfoil_p_lc};
Point(74) = {0.04800500, -0.02758600, 0.00000000, airfoil_p_lc};
Point(75) = {0.05903900, -0.03041600, 0.00000000, airfoil_p_lc};
Point(76) = {0.07113600, -0.03317000, 0.00000000, airfoil_p_lc};
Point(77) = {0.08426500, -0.03584300, 0.00000000, airfoil_p_lc};
Point(78) = {0.09839600, -0.03843100, 0.00000000, airfoil_p_lc};
Point(79) = {0.11349500, -0.04092900, 0.00000000, airfoil_p_lc};
Point(80) = {0.12952400, -0.04332600, 0.00000000, airfoil_p_lc};
Point(81) = {0.14644700, -0.04561000, 0.00000000, airfoil_p_lc};
Point(82) = {0.16422100, -0.04777300, 0.00000000, airfoil_p_lc};
Point(83) = {0.18280300, -0.04980500, 0.00000000, airfoil_p_lc};
Point(84) = {0.20215000, -0.05169400, 0.00000000, airfoil_p_lc};
Point(85) = {0.22221500, -0.05342700, 0.00000000, airfoil_p_lc};
Point(86) = {0.24294900, -0.05499400, 0.00000000, airfoil_p_lc};
Point(87) = {0.26430200, -0.05637600, 0.00000000, airfoil_p_lc};
Point(88) = {0.28622200, -0.05754700, 0.00000000, airfoil_p_lc};
Point(89) = {0.30865800, -0.05845900, 0.00000000, airfoil_p_lc};
Point(90) = {0.33155500, -0.05904600, 0.00000000, airfoil_p_lc};
Point(91) = {0.35485800, -0.05923600, 0.00000000, airfoil_p_lc};
Point(92) = {0.37851000, -0.05897400, 0.00000000, airfoil_p_lc};
Point(93) = {0.40245500, -0.05822400, 0.00000000, airfoil_p_lc};
Point(94) = {0.42663500, -0.05697900, 0.00000000, airfoil_p_lc};
Point(95) = {0.45099100, -0.05525700, 0.00000000, airfoil_p_lc};
Point(96) = {0.47546600, -0.05309900, 0.00000000, airfoil_p_lc};
Point(97) = {0.50000000, -0.05056300, 0.00000000, airfoil_p_lc};
Point(98) = {0.52453400, -0.04771900, 0.00000000, airfoil_p_lc};
Point(99) = {0.54900900, -0.04464200, 0.00000000, airfoil_p_lc};
Point(100) = {0.57336500, -0.04139700, 0.00000000, airfoil_p_lc};
Point(101) = {0.59754500, -0.03804300, 0.00000000, airfoil_p_lc};
Point(102) = {0.62149000, -0.03463100, 0.00000000, airfoil_p_lc};
Point(103) = {0.64514200, -0.03120700, 0.00000000, airfoil_p_lc};
Point(104) = {0.66844500, -0.02781400, 0.00000000, airfoil_p_lc};
Point(105) = {0.69134200, -0.02449500, 0.00000000, airfoil_p_lc};
Point(106) = {0.71377800, -0.02128900, 0.00000000, airfoil_p_lc};
Point(107) = {0.73569800, -0.01823200, 0.00000000, airfoil_p_lc};
Point(108) = {0.75705100, -0.01535700, 0.00000000, airfoil_p_lc};
Point(109) = {0.77778500, -0.01269000, 0.00000000, airfoil_p_lc};
Point(110) = {0.79785000, -0.01024400, 0.00000000, airfoil_p_lc};
Point(111) = {0.81719700, -0.00802700, 0.00000000, airfoil_p_lc};
Point(112) = {0.83577900, -0.00604800, 0.00000000, airfoil_p_lc};
Point(113) = {0.85355300, -0.00431400, 0.00000000, airfoil_p_lc};
Point(114) = {0.87047600, -0.00282900, 0.00000000, airfoil_p_lc};
Point(115) = {0.88650500, -0.00159200, 0.00000000, airfoil_p_lc};
Point(116) = {0.90160400, -0.00060000, 0.00000000, airfoil_p_lc};
Point(117) = {0.91573500, 0.00015700, 0.00000000, airfoil_p_lc};
Point(118) = {0.92886400, 0.00069400, 0.00000000, airfoil_p_lc};
Point(119) = {0.94096100, 0.00103300, 0.00000000, airfoil_p_lc};
Point(120) = {0.95199500, 0.00119700, 0.00000000, airfoil_p_lc};
Point(121) = {0.96194000, 0.00121200, 0.00000000, airfoil_p_lc};
Point(122) = {0.97077200, 0.00111200, 0.00000000, airfoil_p_lc};
Point(123) = {0.97847000, 0.00093500, 0.00000000, airfoil_p_lc};
Point(124) = {0.98501600, 0.00071900, 0.00000000, airfoil_p_lc};
Point(125) = {0.99039300, 0.00049700, 0.00000000, airfoil_p_lc};
Point(126) = {0.99458800, 0.00029600, 0.00000000, airfoil_p_lc};
Point(127) = {0.99759200, 0.00013700, 0.00000000, airfoil_p_lc};
Point(128) = {0.99939800, 0.00003500, 0.00000000, airfoil_p_lc};
Point(129) = {1.00000000, 0.00000000, 0.00000000, airfoil_p_lc};
Spline(1) = {1:129,1};
Line Loop(1) = {1};
// Domain boundary
domain_disc = 8;
Point(130) = {0, 0, 0, domain_disc};
Point(131) = {55, 0, 0, domain_disc};
Point(132) = {0, 55, 0, domain_disc};
Point(133) = {-55, 0, 0, domain_disc};
Point(134) = {0, -55, 0, domain_disc};
Circle(3) = {131, 130, 132};
Circle(4) = {132, 130, 133};
Circle(5) = {133, 130, 134};
Circle(6) = {134, 130, 131};
Line Loop(2) = {3, 4, 5, 6};
Plane Surface(1) = {2, 1};
// Boundary layer
Field[1] = BoundaryLayer;
Field[1].EdgesList = {1};
Field[1].FanNodesList = {1};
Field[1].hwall_n = 0.001;
Field[1].thickness = 0.01;
Field[1].ratio = 1.2;
Field[1].Quads = 1;
BoundaryLayer Field = 1;
