XFOIL Version 6.96 Calculated polar for: GOE 414 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.3950 0.04398 0.04027 -0.1178 0.9488 0.0190 -9.750 -0.4080 0.03676 0.03245 -0.1226 0.9364 0.0193 -9.500 -0.4043 0.03283 0.02797 -0.1233 0.9280 0.0199 -9.250 -0.3909 0.03006 0.02483 -0.1236 0.9218 0.0206 -9.000 -0.3714 0.02850 0.02312 -0.1237 0.9168 0.0214 -8.750 -0.3531 0.02729 0.02175 -0.1231 0.9101 0.0224 -8.500 -0.3300 0.02597 0.02019 -0.1233 0.9056 0.0239 -8.250 -0.3099 0.02468 0.01858 -0.1227 0.8989 0.0255 -8.000 -0.2866 0.02352 0.01709 -0.1224 0.8927 0.0267 -7.750 -0.2655 0.02188 0.01530 -0.1219 0.8867 0.0283 -7.500 -0.2425 0.02104 0.01435 -0.1215 0.8792 0.0302 -7.250 -0.2166 0.02016 0.01328 -0.1214 0.8737 0.0324 -7.000 -0.1932 0.01938 0.01229 -0.1207 0.8660 0.0342 -6.750 -0.1672 0.01841 0.01114 -0.1206 0.8608 0.0363 -6.500 -0.1439 0.01774 0.01041 -0.1200 0.8527 0.0387 -6.250 -0.1167 0.01710 0.00963 -0.1200 0.8465 0.0411 -6.000 -0.0919 0.01660 0.00899 -0.1194 0.8382 0.0436 -5.750 -0.0648 0.01601 0.00831 -0.1194 0.8319 0.0466 -5.500 -0.0396 0.01559 0.00783 -0.1189 0.8234 0.0496 -5.250 -0.0118 0.01518 0.00729 -0.1189 0.8163 0.0542 -5.000 0.0140 0.01486 0.00698 -0.1185 0.8066 0.0611 -4.750 0.0410 0.01455 0.00661 -0.1183 0.7979 0.0702 -4.500 0.0682 0.01430 0.00625 -0.1181 0.7885 0.0807 -4.250 0.0948 0.01412 0.00598 -0.1178 0.7787 0.0899 -4.000 0.1222 0.01391 0.00570 -0.1177 0.7703 0.0979 -3.750 0.1490 0.01378 0.00547 -0.1175 0.7608 0.1060 -3.500 0.1757 0.01360 0.00525 -0.1174 0.7515 0.1140 -3.250 0.2030 0.01346 0.00499 -0.1172 0.7420 0.1204 -3.000 0.2294 0.01329 0.00479 -0.1169 0.7313 0.1265 -2.750 0.2562 0.01316 0.00459 -0.1167 0.7211 0.1346 -2.500 0.2829 0.01301 0.00439 -0.1165 0.7111 0.1432 -2.250 0.3094 0.01288 0.00422 -0.1163 0.7008 0.1555 -2.000 0.3358 0.01273 0.00408 -0.1161 0.6910 0.1736 -1.750 0.3623 0.01259 0.00396 -0.1159 0.6816 0.1998 -1.500 0.3883 0.01246 0.00390 -0.1157 0.6718 0.2367 -1.250 0.4146 0.01238 0.00386 -0.1154 0.6625 0.2760 -1.000 0.4408 0.01233 0.00382 -0.1152 0.6534 0.3100 -0.750 0.4669 0.01229 0.00380 -0.1149 0.6439 0.3403 -0.500 0.4929 0.01227 0.00377 -0.1146 0.6347 0.3700 -0.250 0.5185 0.01222 0.00377 -0.1143 0.6251 0.4029 0.250 0.5675 0.01194 0.00381 -0.1132 0.6069 0.5321 0.500 0.6076 0.01116 0.00403 -0.1151 0.5972 0.9258 0.750 0.6540 0.01129 0.00405 -0.1193 0.5871 1.0000 1.000 0.6778 0.01143 0.00409 -0.1185 0.5775 1.0000 1.250 0.7017 0.01157 0.00414 -0.1178 0.5677 1.0000 1.500 0.7255 0.01173 0.00420 -0.1171 0.5582 1.0000 1.750 0.7492 0.01189 0.00428 -0.1164 0.5480 1.0000 2.000 0.7730 0.01205 0.00437 -0.1157 0.5379 1.0000 2.250 0.7965 0.01223 0.00447 -0.1149 0.5282 1.0000 2.500 0.8199 0.01241 0.00458 -0.1142 0.5180 1.0000 2.750 0.8434 0.01261 0.00471 -0.1135 0.5081 1.0000 3.000 0.8666 0.01282 0.00484 -0.1127 0.4992 1.0000 3.250 0.8901 0.01303 0.00500 -0.1120 0.4906 1.0000 3.500 0.9135 0.01326 0.00516 -0.1113 0.4836 1.0000 3.750 0.9373 0.01348 0.00535 -0.1107 0.4769 1.0000 4.000 0.9608 0.01373 0.00555 -0.1100 0.4713 1.0000 4.250 0.9849 0.01396 0.00577 -0.1095 0.4656 1.0000 4.500 1.0087 0.01421 0.00600 -0.1089 0.4604 1.0000 4.750 1.0326 0.01448 0.00624 -0.1083 0.4561 1.0000 5.000 1.0570 0.01471 0.00651 -0.1079 0.4516 1.0000 5.250 1.0808 0.01498 0.00678 -0.1074 0.4469 1.0000 5.500 1.1044 0.01527 0.00706 -0.1068 0.4424 1.0000 5.750 1.1281 0.01554 0.00737 -0.1062 0.4377 1.0000 6.000 1.1517 0.01581 0.00769 -0.1057 0.4332 1.0000 6.250 1.1753 0.01611 0.00801 -0.1051 0.4293 1.0000 6.500 1.1977 0.01643 0.00835 -0.1044 0.4236 1.0000 6.750 1.2169 0.01673 0.00869 -0.1030 0.4140 1.0000 7.000 1.2344 0.01706 0.00904 -0.1014 0.4025 1.0000 7.250 1.2516 0.01742 0.00940 -0.0997 0.3923 1.0000 7.500 1.2673 0.01774 0.00979 -0.0977 0.3819 1.0000 7.750 1.2834 0.01808 0.01020 -0.0958 0.3717 1.0000 8.000 1.2962 0.01849 0.01065 -0.0935 0.3556 1.0000 8.250 1.3065 0.01903 0.01116 -0.0908 0.3316 1.0000 8.500 1.3131 0.01981 0.01183 -0.0877 0.2946 1.0000 8.750 1.3078 0.02133 0.01304 -0.0833 0.2477 1.0000 9.000 1.3014 0.02322 0.01466 -0.0792 0.2076 1.0000 9.250 1.2870 0.02581 0.01686 -0.0745 0.1349 1.0000 9.500 1.2705 0.02878 0.01950 -0.0702 0.0867 1.0000 9.750 1.2523 0.03213 0.02254 -0.0662 0.0309 1.0000 10.000 1.2536 0.03415 0.02460 -0.0642 0.0241 1.0000 10.250 1.2573 0.03605 0.02659 -0.0625 0.0216 1.0000 10.500 1.2607 0.03803 0.02868 -0.0610 0.0201 1.0000 10.750 1.2654 0.03997 0.03075 -0.0597 0.0190 1.0000 11.000 1.2684 0.04213 0.03305 -0.0585 0.0179 1.0000 11.250 1.2700 0.04450 0.03555 -0.0574 0.0170 1.0000 11.500 1.2696 0.04717 0.03835 -0.0563 0.0162 1.0000 11.750 1.2674 0.05016 0.04147 -0.0554 0.0156 1.0000 12.000 1.2630 0.05350 0.04498 -0.0547 0.0152 1.0000 12.250 1.2563 0.05722 0.04885 -0.0541 0.0148 1.0000 12.500 1.2520 0.06076 0.05251 -0.0537 0.0145 1.0000 12.750 1.2491 0.06420 0.05609 -0.0534 0.0143 1.0000 13.000 1.2458 0.06775 0.05976 -0.0532 0.0140 1.0000 13.250 1.2424 0.07136 0.06348 -0.0531 0.0137 1.0000 13.500 1.2393 0.07500 0.06723 -0.0531 0.0134 1.0000 13.750 1.2363 0.07864 0.07098 -0.0532 0.0130 1.0000 14.000 1.2339 0.08223 0.07466 -0.0533 0.0125 1.0000 14.250 1.2317 0.08579 0.07830 -0.0535 0.0121 1.0000 14.500 1.2301 0.08927 0.08186 -0.0536 0.0118 1.0000