XFOIL Version 6.96 Calculated polar for: GOE 692 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.750 -0.7741 0.08220 0.07956 -0.0884 1.0000 0.0276 -16.500 -0.8283 0.07153 0.06874 -0.0944 1.0000 0.0276 -16.250 -0.8778 0.06201 0.05908 -0.0995 1.0000 0.0276 -16.000 -0.9252 0.05300 0.04993 -0.1040 1.0000 0.0275 -15.750 -0.9676 0.04489 0.04166 -0.1080 1.0000 0.0275 -15.500 -0.9745 0.03791 0.03449 -0.1167 0.9981 0.0276 -15.250 -0.9641 0.03352 0.02993 -0.1238 0.9952 0.0279 -15.000 -0.9480 0.03069 0.02696 -0.1284 0.9930 0.0281 -14.750 -0.9336 0.02862 0.02477 -0.1306 0.9880 0.0284 -14.500 -0.9134 0.02691 0.02295 -0.1327 0.9844 0.0286 -14.250 -0.8958 0.02558 0.02150 -0.1332 0.9784 0.0288 -14.000 -0.8778 0.02447 0.02029 -0.1332 0.9711 0.0290 -13.750 -0.8607 0.02355 0.01927 -0.1326 0.9617 0.0292 -13.500 -0.8415 0.02273 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0.0854 -4.000 0.1199 0.00891 0.00272 -0.1223 0.7193 0.0883 -3.750 0.1478 0.00878 0.00260 -0.1223 0.7119 0.0930 -3.500 0.1759 0.00870 0.00250 -0.1223 0.7038 0.0970 -3.250 0.2036 0.00861 0.00241 -0.1223 0.6964 0.1039 -3.000 0.2318 0.00852 0.00233 -0.1223 0.6888 0.1122 -2.500 0.2878 0.00839 0.00224 -0.1224 0.6750 0.1373 -2.250 0.3157 0.00835 0.00222 -0.1224 0.6682 0.1491 -2.000 0.3437 0.00832 0.00219 -0.1224 0.6622 0.1585 -1.750 0.3723 0.00830 0.00217 -0.1225 0.6564 0.1660 -1.500 0.4002 0.00828 0.00215 -0.1225 0.6505 0.1748 -1.250 0.4283 0.00828 0.00214 -0.1225 0.6452 0.1825 -1.000 0.4569 0.00824 0.00212 -0.1227 0.6403 0.1910 -0.750 0.4850 0.00823 0.00212 -0.1227 0.6351 0.1998 -0.500 0.5125 0.00825 0.00213 -0.1227 0.6296 0.2109 -0.250 0.5412 0.00820 0.00213 -0.1228 0.6255 0.2238 0.000 0.5695 0.00817 0.00214 -0.1229 0.6208 0.2406 0.250 0.5970 0.00813 0.00216 -0.1229 0.6158 0.2646 0.500 0.6244 0.00809 0.00219 -0.1229 0.6109 0.2999 0.750 0.6522 0.00791 0.00222 -0.1230 0.6068 0.3670 1.000 0.6785 0.00763 0.00227 -0.1229 0.6014 0.4846 1.250 0.7029 0.00734 0.00236 -0.1224 0.5948 0.6360 1.500 0.7273 0.00700 0.00245 -0.1217 0.5888 0.7777 1.750 0.7486 0.00684 0.00257 -0.1200 0.5814 0.8842 2.000 0.7716 0.00687 0.00267 -0.1187 0.5746 0.9411 2.250 0.8021 0.00693 0.00274 -0.1191 0.5678 0.9682 2.500 0.8370 0.00706 0.00282 -0.1207 0.5610 0.9835 2.750 0.8752 0.00716 0.00290 -0.1230 0.5545 0.9933 3.000 0.9154 0.00729 0.00298 -0.1258 0.5459 0.9972 3.250 0.9495 0.00741 0.00306 -0.1273 0.5379 1.0000 3.500 0.9712 0.00750 0.00311 -0.1261 0.5297 1.0000 3.750 0.9930 0.00761 0.00318 -0.1249 0.5222 1.0000 4.000 1.0154 0.00771 0.00325 -0.1238 0.5136 1.0000 4.250 1.0375 0.00785 0.00334 -0.1227 0.5043 1.0000 4.500 1.0593 0.00801 0.00345 -0.1215 0.4929 1.0000 4.750 1.0823 0.00816 0.00357 -0.1206 0.4818 1.0000 5.000 1.1044 0.00836 0.00370 -0.1195 0.4706 1.0000 5.250 1.1263 0.00857 0.00386 -0.1184 0.4593 1.0000 5.500 1.1491 0.00875 0.00401 -0.1175 0.4491 1.0000 5.750 1.1704 0.00899 0.00419 -0.1163 0.4385 1.0000 6.000 1.1919 0.00921 0.00438 -0.1152 0.4276 1.0000 6.250 1.2122 0.00944 0.00456 -0.1138 0.4175 1.0000 6.500 1.2303 0.00973 0.00480 -0.1120 0.4067 1.0000 6.750 1.2506 0.00997 0.00502 -0.1107 0.3959 1.0000 7.000 1.2699 0.01027 0.00527 -0.1092 0.3845 1.0000 7.250 1.2880 0.01063 0.00557 -0.1076 0.3718 1.0000 7.500 1.3064 0.01099 0.00588 -0.1060 0.3584 1.0000 7.750 1.3249 0.01136 0.00621 -0.1045 0.3450 1.0000 8.000 1.3424 0.01178 0.00658 -0.1029 0.3311 1.0000 8.250 1.3590 0.01226 0.00699 -0.1012 0.3162 1.0000 8.500 1.3746 0.01280 0.00746 -0.0993 0.3011 1.0000 8.750 1.3896 0.01338 0.00797 -0.0975 0.2861 1.0000 9.000 1.4041 0.01400 0.00852 -0.0956 0.2719 1.0000 9.250 1.4178 0.01468 0.00914 -0.0936 0.2586 1.0000 9.500 1.4331 0.01530 0.00973 -0.0920 0.2469 1.0000 9.750 1.4473 0.01600 0.01039 -0.0903 0.2356 1.0000 10.000 1.4602 0.01679 0.01112 -0.0884 0.2241 1.0000 10.250 1.4724 0.01764 0.01193 -0.0866 0.2127 1.0000 10.500 1.4868 0.01840 0.01267 -0.0851 0.2033 1.0000 10.750 1.4992 0.01929 0.01353 -0.0834 0.1939 1.0000 11.000 1.5109 0.02025 0.01444 -0.0817 0.1838 1.0000 11.250 1.5230 0.02120 0.01538 -0.0801 0.1741 1.0000 11.500 1.5330 0.02232 0.01645 -0.0784 0.1643 1.0000 11.750 1.5428 0.02347 0.01757 -0.0767 0.1554 1.0000 12.000 1.5536 0.02457 0.01866 -0.0752 0.1487 1.0000 12.250 1.5629 0.02580 0.01987 -0.0736 0.1424 1.0000 12.500 1.5738 0.02696 0.02105 -0.0722 0.1379 1.0000 12.750 1.5854 0.02810 0.02220 -0.0710 0.1343 1.0000 13.000 1.5948 0.02940 0.02351 -0.0696 0.1306 1.0000 13.250 1.6024 0.03088 0.02499 -0.0681 0.1266 1.0000 13.500 1.6156 0.03195 0.02612 -0.0672 0.1247 1.0000 13.750 1.6261 0.03326 0.02746 -0.0661 0.1222 1.0000 14.000 1.6352 0.03469 0.02891 -0.0650 0.1193 1.0000 14.250 1.6417 0.03639 0.03063 -0.0637 0.1161 1.0000 14.500 1.6506 0.03790 0.03218 -0.0627 0.1137 1.0000 14.750 1.6618 0.03924 0.03357 -0.0619 0.1119 1.0000 15.000 1.6712 0.04076 0.03514 -0.0611 0.1096 1.0000 15.250 1.6783 0.04251 0.03691 -0.0601 0.1070 1.0000 15.500 1.6828 0.04454 0.03897 -0.0591 0.1040 1.0000 15.750 1.6916 0.04617 0.04065 -0.0584 0.1018 1.0000 16.000 1.7003 0.04785 0.04238 -0.0577 0.0991 1.0000 16.250 1.7055 0.04986 0.04441 -0.0569 0.0951 1.0000 16.500 1.7091 0.05206 0.04663 -0.0561 0.0911 1.0000 16.750 1.7126 0.05431 0.04890 -0.0554 0.0845 1.0000 17.000 1.7081 0.05739 0.05191 -0.0545 0.0736 1.0000 17.250 1.6959 0.06130 0.05576 -0.0534 0.0612 1.0000 17.500 1.6825 0.06547 0.05989 -0.0525 0.0523 1.0000 17.750 1.6704 0.06961 0.06403 -0.0517 0.0450 1.0000 18.000 1.6590 0.07373 0.06816 -0.0512 0.0382 1.0000 18.250 1.6466 0.07808 0.07252 -0.0509 0.0317 1.0000 18.500 1.6352 0.08241 0.07688 -0.0507 0.0269 1.0000 18.750 1.6263 0.08652 0.08103 -0.0507 0.0239 1.0000