XFOIL Version 6.96 Calculated polar for: GOE 612 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.5071 0.04666 0.04355 -0.1194 0.9798 0.0376 -11.750 -0.5244 0.03704 0.03344 -0.1360 0.9708 0.0376 -11.500 -0.5249 0.03360 0.02966 -0.1382 0.9625 0.0378 -11.250 -0.5145 0.03100 0.02676 -0.1394 0.9560 0.0380 -11.000 -0.5084 0.02934 0.02484 -0.1379 0.9470 0.0382 -10.750 -0.4958 0.02784 0.02308 -0.1370 0.9402 0.0384 -10.500 -0.4905 0.02560 0.02065 -0.1348 0.9311 0.0387 -10.250 -0.4739 0.02415 0.01909 -0.1337 0.9250 0.0390 -10.000 -0.4578 0.02317 0.01804 -0.1321 0.9175 0.0394 -9.750 -0.4393 0.02226 0.01704 -0.1309 0.9104 0.0398 -9.500 -0.4195 0.02151 0.01619 -0.1297 0.9038 0.0403 -9.250 -0.4000 0.02078 0.01538 -0.1285 0.8955 0.0408 -9.000 -0.3781 0.02001 0.01449 -0.1275 0.8891 0.0414 -8.750 -0.3583 0.01925 0.01363 -0.1262 0.8799 0.0418 -8.500 -0.3356 0.01848 0.01270 -0.1254 0.8730 0.0423 -8.250 -0.3141 0.01781 0.01193 -0.1242 0.8634 0.0427 -8.000 -0.2901 0.01721 0.01118 -0.1235 0.8557 0.0432 -7.750 -0.2671 0.01672 0.01059 -0.1225 0.8455 0.0436 -7.500 -0.2448 0.01572 0.00949 -0.1216 0.8370 0.0443 -7.250 -0.2220 0.01510 0.00885 -0.1208 0.8268 0.0450 -7.000 -0.1975 0.01465 0.00835 -0.1201 0.8184 0.0457 -6.750 -0.1731 0.01427 0.00791 -0.1194 0.8090 0.0466 -6.500 -0.1480 0.01392 0.00748 -0.1187 0.8009 0.0477 -6.250 -0.1231 0.01358 0.00706 -0.1180 0.7920 0.0486 -6.000 -0.0976 0.01329 0.00666 -0.1174 0.7845 0.0494 -5.750 -0.0744 0.01274 0.00608 -0.1166 0.7764 0.0506 -5.500 -0.0493 0.01240 0.00569 -0.1160 0.7698 0.0520 -5.250 -0.0240 0.01213 0.00540 -0.1154 0.7632 0.0536 -5.000 0.0019 0.01190 0.00510 -0.1148 0.7564 0.0552 -4.750 0.0275 0.01161 0.00474 -0.1143 0.7506 0.0574 -4.500 0.0528 0.01134 0.00448 -0.1137 0.7443 0.0604 -4.250 0.0790 0.01116 0.00424 -0.1132 0.7379 0.0637 -4.000 0.1048 0.01091 0.00398 -0.1127 0.7316 0.0693 -3.750 0.1304 0.01067 0.00379 -0.1121 0.7250 0.0781 -3.500 0.1566 0.01048 0.00363 -0.1116 0.7192 0.0946 -3.250 0.1834 0.01034 0.00352 -0.1113 0.7138 0.1130 -3.000 0.2095 0.01019 0.00341 -0.1108 0.7080 0.1277 -2.750 0.2361 0.01007 0.00330 -0.1105 0.7025 0.1416 -2.500 0.2633 0.00999 0.00322 -0.1102 0.6974 0.1566 -2.250 0.2892 0.00984 0.00315 -0.1097 0.6919 0.1756 -2.000 0.3153 0.00969 0.00309 -0.1092 0.6862 0.2028 -1.750 0.3420 0.00961 0.00304 -0.1089 0.6805 0.2345 -1.500 0.3681 0.00951 0.00303 -0.1084 0.6750 0.2647 -1.250 0.3943 0.00942 0.00303 -0.1080 0.6696 0.2923 -1.000 0.4213 0.00939 0.00302 -0.1076 0.6647 0.3184 -0.750 0.4481 0.00937 0.00304 -0.1073 0.6598 0.3416 -0.500 0.4743 0.00932 0.00306 -0.1068 0.6545 0.3636 -0.250 0.5009 0.00930 0.00307 -0.1064 0.6495 0.3826 0.000 0.5281 0.00932 0.00307 -0.1061 0.6447 0.3996 0.250 0.5542 0.00928 0.00309 -0.1056 0.6394 0.4162 0.500 0.5801 0.00925 0.00310 -0.1050 0.6334 0.4335 0.750 0.6065 0.00926 0.00310 -0.1046 0.6278 0.4521 1.000 0.6320 0.00922 0.00313 -0.1040 0.6222 0.4726 1.250 0.6571 0.00916 0.00316 -0.1033 0.6159 0.4978 1.500 0.6819 0.00911 0.00317 -0.1026 0.6096 0.5342 1.750 0.7043 0.00892 0.00322 -0.1014 0.6025 0.5951 2.000 0.7963 0.00824 0.00342 -0.1148 0.5923 0.9804 2.250 0.8404 0.00834 0.00350 -0.1183 0.5824 1.0000 2.500 0.8624 0.00845 0.00352 -0.1170 0.5733 1.0000 2.750 0.8845 0.00853 0.00358 -0.1157 0.5623 1.0000 3.000 0.9060 0.00865 0.00364 -0.1143 0.5506 1.0000 3.250 0.9262 0.00879 0.00370 -0.1126 0.5363 1.0000 3.500 0.9454 0.00896 0.00379 -0.1108 0.5186 1.0000 3.750 0.9631 0.00918 0.00390 -0.1087 0.4964 1.0000 4.000 0.9769 0.00950 0.00406 -0.1059 0.4674 1.0000 4.250 0.9876 0.00994 0.00429 -0.1025 0.4337 1.0000 4.750 1.0095 0.01083 0.00486 -0.0960 0.3822 1.0000 5.000 1.0202 0.01120 0.00512 -0.0927 0.3669 1.0000 5.250 1.0322 0.01155 0.00539 -0.0897 0.3551 1.0000 5.500 1.0471 0.01186 0.00565 -0.0872 0.3454 1.0000 5.750 1.0608 0.01223 0.00595 -0.0847 0.3369 1.0000 6.000 1.0782 0.01252 0.00622 -0.0828 0.3295 1.0000 6.250 1.0939 0.01288 0.00654 -0.0807 0.3223 1.0000 6.500 1.1106 0.01324 0.00687 -0.0788 0.3163 1.0000 6.750 1.1292 0.01354 0.00717 -0.0772 0.3106 1.0000 7.000 1.1455 0.01394 0.00753 -0.0754 0.3049 1.0000 7.250 1.1624 0.01433 0.00791 -0.0737 0.2997 1.0000 7.500 1.1818 0.01464 0.00824 -0.0724 0.2947 1.0000 7.750 1.1990 0.01504 0.00862 -0.0708 0.2895 1.0000 8.000 1.2139 0.01557 0.00910 -0.0689 0.2843 1.0000 8.250 1.2340 0.01587 0.00946 -0.0678 0.2798 1.0000 8.500 1.2520 0.01627 0.00987 -0.0665 0.2745 1.0000 8.750 1.2671 0.01682 0.01038 -0.0648 0.2692 1.0000 9.000 1.2852 0.01725 0.01084 -0.0635 0.2643 1.0000 9.250 1.3030 0.01769 0.01131 -0.0623 0.2588 1.0000 9.500 1.3180 0.01830 0.01189 -0.0607 0.2535 1.0000 9.750 1.3346 0.01884 0.01245 -0.0594 0.2485 1.0000 10.000 1.3517 0.01936 0.01300 -0.0583 0.2429 1.0000 10.250 1.3657 0.02007 0.01369 -0.0567 0.2372 1.0000 10.500 1.3815 0.02070 0.01435 -0.0555 0.2317 1.0000 10.750 1.3970 0.02136 0.01503 -0.0543 0.2255 1.0000 11.000 1.4078 0.02231 0.01595 -0.0526 0.2193 1.0000 11.250 1.4245 0.02295 0.01664 -0.0516 0.2130 1.0000 11.500 1.4351 0.02398 0.01763 -0.0501 0.2056 1.0000 11.750 1.4490 0.02483 0.01850 -0.0490 0.1985 1.0000 12.000 1.4588 0.02596 0.01961 -0.0476 0.1915 1.0000 12.250 1.4709 0.02698 0.02065 -0.0464 0.1850 1.0000 12.500 1.4808 0.02817 0.02184 -0.0452 0.1786 1.0000 12.750 1.4902 0.02944 0.02310 -0.0439 0.1731 1.0000 13.000 1.5017 0.03057 0.02428 -0.0429 0.1684 1.0000 13.250 1.5095 0.03201 0.02571 -0.0417 0.1636 1.0000 13.500 1.5179 0.03343 0.02715 -0.0406 0.1597 1.0000 13.750 1.5293 0.03464 0.02842 -0.0397 0.1557 1.0000 14.000 1.5374 0.03613 0.02993 -0.0387 0.1518 1.0000 14.250 1.5421 0.03795 0.03174 -0.0376 0.1481 1.0000 14.500 1.5528 0.03927 0.03313 -0.0369 0.1450 1.0000 14.750 1.5622 0.04074 0.03466 -0.0361 0.1424 1.0000 15.000 1.5695 0.04239 0.03635 -0.0353 0.1393 1.0000 15.250 1.5735 0.04437 0.03835 -0.0345 0.1362 1.0000 15.500 1.5787 0.04626 0.04027 -0.0337 0.1336 1.0000 15.750 1.5888 0.04775 0.04185 -0.0332 0.1314 1.0000 16.000 1.5958 0.04954 0.04371 -0.0327 0.1285 1.0000 16.250 1.6007 0.05155 0.04576 -0.0322 0.1258 1.0000 16.500 1.6018 0.05398 0.04821 -0.0316 0.1231 1.0000 16.750 1.6065 0.05606 0.05036 -0.0312 0.1209 1.0000 17.000 1.6140 0.05793 0.05233 -0.0310 0.1180 1.0000 17.250 1.6179 0.06017 0.05463 -0.0307 0.1152 1.0000 17.500 1.6181 0.06285 0.05735 -0.0305 0.1125 1.0000 17.750 1.6159 0.06583 0.06037 -0.0303 0.1094 1.0000 18.000 1.6223 0.06790 0.06255 -0.0302 0.1062 1.0000 18.250 1.6206 0.07097 0.06566 -0.0303 0.1021 1.0000 18.500 1.6138 0.07467 0.06939 -0.0305 0.0985 1.0000 18.750 1.6162 0.07730 0.07212 -0.0307 0.0936 1.0000 19.000 1.6067 0.08146 0.07631 -0.0311 0.0887 1.0000 19.250 1.6013 0.08516 0.08008 -0.0316 0.0817 1.0000