XFOIL Version 6.96 Calculated polar for: CLARK YM-18 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.7303 0.07117 0.06589 -0.0474 1.0000 0.1070 -9.500 -0.7636 0.06691 0.06142 -0.0439 0.9998 0.1058 -9.250 -0.7651 0.06057 0.05470 -0.0465 0.9933 0.1052 -9.000 -0.7659 0.05498 0.04862 -0.0475 0.9859 0.1052 -8.750 -0.7589 0.04998 0.04288 -0.0489 0.9794 0.1062 -8.500 -0.7416 0.04720 0.03994 -0.0493 0.9724 0.1079 -8.250 -0.7072 0.04583 0.03861 -0.0516 0.9673 0.1105 -8.000 -0.6892 0.04363 0.03610 -0.0516 0.9600 0.1126 -7.750 -0.6655 0.04114 0.03312 -0.0525 0.9537 0.1153 -7.500 -0.6422 0.03909 0.03061 -0.0529 0.9476 0.1186 -7.250 -0.6150 0.03812 0.02974 -0.0536 0.9406 0.1224 -7.000 -0.5789 0.03680 0.02810 -0.0557 0.9357 0.1278 -6.750 -0.5587 0.03556 0.02670 -0.0550 0.9281 0.1319 -6.500 -0.5271 0.03485 0.02600 -0.0562 0.9220 0.1379 -6.250 -0.4867 0.03375 0.02472 -0.0589 0.9179 0.1456 -6.000 -0.4702 0.03333 0.02434 -0.0573 0.9087 0.1514 -5.750 -0.4353 0.03252 0.02341 -0.0589 0.9032 0.1600 -5.500 -0.3925 0.03202 0.02282 -0.0618 0.8996 0.1711 -5.250 -0.3814 0.03167 0.02258 -0.0593 0.8894 0.1773 -5.000 -0.3434 0.03114 0.02197 -0.0612 0.8842 0.1897 -4.750 -0.3156 0.03089 0.02181 -0.0615 0.8777 0.2010 -4.500 -0.2930 0.03062 0.02160 -0.0609 0.8697 0.2123 -4.250 -0.2534 0.03014 0.02118 -0.0630 0.8651 0.2301 -4.000 -0.2328 0.03002 0.02110 -0.0620 0.8569 0.2463 -3.750 -0.2054 0.02977 0.02094 -0.0621 0.8499 0.2683 -3.500 -0.1652 0.02926 0.02050 -0.0641 0.8458 0.3004 -3.250 -0.1502 0.02925 0.02061 -0.0622 0.8359 0.3230 -3.000 -0.1133 0.02872 0.02017 -0.0635 0.8292 0.3555 -2.750 -0.0613 0.02778 0.01941 -0.0670 0.8256 0.3916 -2.500 -0.0492 0.02774 0.01945 -0.0642 0.8121 0.4133 -2.250 0.0044 0.02660 0.01849 -0.0676 0.8080 0.4523 -2.000 0.0195 0.02657 0.01856 -0.0652 0.7960 0.4805 -1.750 0.0607 0.02574 0.01800 -0.0666 0.7913 0.5261 -1.500 0.1030 0.02479 0.01739 -0.0679 0.7882 0.5905 -1.250 0.1103 0.02504 0.01798 -0.0641 0.7761 0.6503 -1.000 0.1457 0.02437 0.01770 -0.0631 0.7718 0.7500 -0.750 0.1903 0.02388 0.01736 -0.0632 0.7688 0.8337 -0.500 0.2163 0.02446 0.01798 -0.0617 0.7575 0.8848 -0.250 0.2901 0.02411 0.01748 -0.0678 0.7537 0.9219 0.000 0.3792 0.02352 0.01669 -0.0773 0.7506 0.9440 0.250 0.4500 0.02339 0.01644 -0.0848 0.7416 0.9634 0.500 0.5297 0.02265 0.01555 -0.0937 0.7338 0.9788 0.750 0.6044 0.02197 0.01474 -0.1024 0.7241 0.9932 1.000 0.6516 0.02138 0.01402 -0.1061 0.7136 1.0000 1.250 0.6653 0.02132 0.01390 -0.1039 0.7015 1.0000 1.500 0.6923 0.02083 0.01326 -0.1035 0.6922 1.0000 1.750 0.7038 0.02087 0.01327 -0.1008 0.6783 1.0000 2.000 0.7232 0.02069 0.01299 -0.0992 0.6659 1.0000 2.250 0.7494 0.02033 0.01248 -0.0985 0.6542 1.0000 2.500 0.7627 0.02036 0.01245 -0.0958 0.6389 1.0000 2.750 0.7795 0.02034 0.01235 -0.0937 0.6241 1.0000 3.000 0.8003 0.02028 0.01216 -0.0922 0.6100 1.0000 3.250 0.8261 0.02017 0.01186 -0.0915 0.5965 1.0000 3.500 0.8405 0.02035 0.01197 -0.0890 0.5807 1.0000 3.750 0.8557 0.02058 0.01211 -0.0866 0.5657 1.0000 4.000 0.8739 0.02080 0.01222 -0.0848 0.5520 1.0000 4.250 0.9001 0.02093 0.01214 -0.0843 0.5403 1.0000 4.500 0.9120 0.02135 0.01256 -0.0815 0.5275 1.0000 4.750 0.9319 0.02172 0.01284 -0.0800 0.5173 1.0000 5.000 0.9517 0.02208 0.01311 -0.0786 0.5073 1.0000 5.250 0.9698 0.02254 0.01351 -0.0769 0.4982 1.0000 5.500 0.9893 0.02294 0.01386 -0.0755 0.4894 1.0000 5.750 1.0118 0.02341 0.01424 -0.0746 0.4821 1.0000 6.000 1.0256 0.02397 0.01484 -0.0722 0.4742 1.0000 6.250 1.0550 0.02432 0.01505 -0.0725 0.4676 1.0000 6.500 1.0660 0.02501 0.01582 -0.0698 0.4604 1.0000 6.750 1.0858 0.02552 0.01632 -0.0685 0.4536 1.0000 7.000 1.1173 0.02593 0.01659 -0.0692 0.4477 1.0000 7.250 1.1239 0.02672 0.01754 -0.0658 0.4409 1.0000 7.500 1.1456 0.02722 0.01803 -0.0649 0.4346 1.0000 7.750 1.1764 0.02771 0.01840 -0.0655 0.4290 1.0000 8.000 1.1821 0.02859 0.01946 -0.0621 0.4227 1.0000 8.250 1.2030 0.02915 0.02002 -0.0611 0.4167 1.0000 8.500 1.2372 0.02962 0.02035 -0.0623 0.4111 1.0000 8.750 1.2383 0.03061 0.02157 -0.0584 0.4048 1.0000 9.000 1.2604 0.03103 0.02196 -0.0575 0.3978 1.0000 9.250 1.2836 0.03155 0.02243 -0.0569 0.3906 1.0000 9.500 1.2897 0.03229 0.02330 -0.0538 0.3832 1.0000 9.750 1.3329 0.03237 0.02311 -0.0561 0.3754 1.0000 10.000 1.3253 0.03350 0.02452 -0.0510 0.3692 1.0000 10.250 1.3420 0.03410 0.02515 -0.0496 0.3625 1.0000 10.500 1.3746 0.03459 0.02553 -0.0505 0.3558 1.0000 10.750 1.3672 0.03579 0.02697 -0.0457 0.3496 1.0000 11.000 1.3921 0.03620 0.02732 -0.0454 0.3426 1.0000 11.250 1.4074 0.03708 0.02824 -0.0439 0.3361 1.0000 11.500 1.3980 0.03826 0.02960 -0.0389 0.3299 1.0000 11.750 1.4541 0.03818 0.02925 -0.0430 0.3213 1.0000 12.000 1.4239 0.03986 0.03124 -0.0354 0.3162 1.0000 12.250 1.4225 0.04095 0.03244 -0.0320 0.3094 1.0000 12.500 1.4575 0.04112 0.03248 -0.0329 0.3015 1.0000 12.750 1.4287 0.04325 0.03489 -0.0268 0.2955 1.0000 13.000 1.4668 0.04290 0.03435 -0.0278 0.2871 1.0000 13.250 1.4425 0.04523 0.03692 -0.0228 0.2811 1.0000 13.500 1.4315 0.04702 0.03885 -0.0194 0.2743 1.0000 13.750 1.4582 0.04708 0.03879 -0.0192 0.2664 1.0000 14.000 1.4211 0.05064 0.04265 -0.0147 0.2604 1.0000 14.250 1.4725 0.04897 0.04067 -0.0159 0.2517 1.0000 14.500 1.4177 0.05410 0.04621 -0.0111 0.2466 1.0000 14.750 1.4191 0.05561 0.04774 -0.0097 0.2396 1.0000 15.000 1.4226 0.05722 0.04936 -0.0085 0.2331 1.0000 15.250 1.3807 0.06285 0.05526 -0.0065 0.2275 1.0000 15.500 1.4435 0.05936 0.05144 -0.0068 0.2201 1.0000 15.750 1.3719 0.06820 0.06073 -0.0050 0.2161 1.0000 16.000 1.3053 0.07824 0.07107 -0.0055 0.2114 1.0000 16.250 1.4136 0.06869 0.06107 -0.0040 0.2048 1.0000 16.500 0.8403 0.17206 0.16524 -0.0442 0.1875 1.0000 16.750 0.8407 0.17740 0.17061 -0.0465 0.1888 1.0000