XFOIL Version 6.96 Calculated polar for: GOE 614 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.250 -0.4924 0.10060 0.09800 -0.0943 0.9908 0.0202 -17.000 -0.5191 0.09150 0.08875 -0.1005 0.9894 0.0203 -16.750 -0.5327 0.08468 0.08181 -0.1056 0.9879 0.0203 -16.500 -0.5426 0.07851 0.07552 -0.1106 0.9862 0.0204 -16.250 -0.5468 0.07320 0.07013 -0.1153 0.9846 0.0204 -16.000 -0.5492 0.06813 0.06496 -0.1200 0.9830 0.0204 -15.750 -0.5483 0.06345 0.06019 -0.1249 0.9816 0.0205 -15.500 -0.5576 0.05915 0.05581 -0.1274 0.9759 0.0205 -15.250 -0.5577 0.05510 0.05168 -0.1313 0.9720 0.0205 -15.000 -0.5559 0.05092 0.04740 -0.1358 0.9682 0.0206 -14.750 -0.5554 0.04733 0.04373 -0.1390 0.9606 0.0206 -14.500 -0.5446 0.04346 0.03975 -0.1445 0.9555 0.0206 -14.250 -0.5366 0.03982 0.03601 -0.1493 0.9463 0.0207 -14.000 -0.5177 0.03643 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-4.000 0.2113 0.01083 0.00369 -0.1313 0.5103 0.0262 -3.500 0.2587 0.01067 0.00345 -0.1294 0.4985 0.0268 -3.250 0.2826 0.01060 0.00335 -0.1286 0.4929 0.0270 -3.000 0.3048 0.01055 0.00325 -0.1273 0.4865 0.0274 -2.750 0.3278 0.01049 0.00316 -0.1262 0.4815 0.0277 -2.500 0.3501 0.01044 0.00308 -0.1250 0.4746 0.0279 -2.250 0.3715 0.01041 0.00301 -0.1236 0.4683 0.0284 -2.000 0.3945 0.01035 0.00293 -0.1225 0.4635 0.0291 -1.750 0.4177 0.01031 0.00287 -0.1215 0.4583 0.0298 -1.500 0.4401 0.01031 0.00283 -0.1203 0.4524 0.0308 -1.250 0.4622 0.01032 0.00281 -0.1191 0.4454 0.0320 -1.000 0.4851 0.01030 0.00277 -0.1180 0.4397 0.0348 -0.750 0.5045 0.01013 0.00272 -0.1164 0.4324 0.0832 -0.500 0.5273 0.01010 0.00273 -0.1153 0.4278 0.1003 -0.250 0.5505 0.01011 0.00274 -0.1144 0.4225 0.1085 0.000 0.5731 0.01014 0.00278 -0.1133 0.4178 0.1185 0.250 0.5940 0.01007 0.00282 -0.1120 0.4132 0.1593 0.500 0.6168 0.01005 0.00289 -0.1110 0.4095 0.1896 0.750 0.6395 0.01010 0.00296 -0.1100 0.4041 0.2035 1.000 0.6613 0.01019 0.00305 -0.1088 0.3986 0.2127 1.250 0.6835 0.01028 0.00313 -0.1077 0.3939 0.2209 1.500 0.7065 0.01034 0.00321 -0.1067 0.3892 0.2312 1.750 0.7278 0.01045 0.00332 -0.1055 0.3823 0.2422 2.000 0.7486 0.01056 0.00343 -0.1041 0.3770 0.2554 2.250 0.7710 0.01064 0.00353 -0.1031 0.3724 0.2660 2.500 0.7929 0.01072 0.00364 -0.1020 0.3680 0.2817 2.750 0.8128 0.01083 0.00379 -0.1006 0.3620 0.3071 3.000 0.8342 0.01093 0.00392 -0.0994 0.3571 0.3258 3.250 0.8550 0.01102 0.00407 -0.0982 0.3521 0.3496 3.500 0.8734 0.01120 0.00426 -0.0965 0.3443 0.3728 3.750 0.8939 0.01134 0.00442 -0.0953 0.3375 0.3909 4.000 0.9128 0.01152 0.00462 -0.0937 0.3306 0.4120 4.250 0.9314 0.01170 0.00484 -0.0922 0.3233 0.4363 4.500 0.9500 0.01190 0.00505 -0.0906 0.3162 0.4584 4.750 0.9670 0.01216 0.00532 -0.0888 0.3059 0.4794 5.000 0.9839 0.01243 0.00559 -0.0870 0.2980 0.4987 5.250 0.9981 0.01278 0.00593 -0.0848 0.2848 0.5250 5.500 1.0117 0.01316 0.00631 -0.0826 0.2716 0.5510 5.750 1.0247 0.01346 0.00671 -0.0803 0.2625 0.6032 6.000 1.0349 0.01382 0.00718 -0.0775 0.2503 0.6660 6.500 1.1575 0.01464 0.00850 -0.0936 0.2225 1.0000 6.750 1.1737 0.01516 0.00898 -0.0921 0.2153 1.0000 7.000 1.1905 0.01566 0.00946 -0.0908 0.2091 1.0000 7.250 1.2070 0.01620 0.00996 -0.0894 0.2038 1.0000 7.500 1.2238 0.01673 0.01047 -0.0881 0.1987 1.0000 7.750 1.2396 0.01733 0.01104 -0.0868 0.1924 1.0000 8.000 1.2541 0.01802 0.01169 -0.0853 0.1865 1.0000 8.250 1.2680 0.01875 0.01239 -0.0839 0.1774 1.0000 8.500 1.2626 0.02060 0.01404 -0.0803 0.1410 1.0000 8.750 1.2580 0.02255 0.01587 -0.0770 0.1158 1.0000 9.000 1.2719 0.02341 0.01674 -0.0759 0.1139 1.0000 9.250 1.2841 0.02441 0.01774 -0.0747 0.1111 1.0000 9.500 1.2980 0.02532 0.01867 -0.0736 0.1099 1.0000 9.750 1.3108 0.02634 0.01970 -0.0726 0.1084 1.0000 10.000 1.3238 0.02737 0.02074 -0.0716 0.1070 1.0000 10.250 1.3364 0.02845 0.02184 -0.0706 0.1058 1.0000 10.500 1.3490 0.02953 0.02295 -0.0697 0.1046 1.0000 10.750 1.3616 0.03065 0.02411 -0.0688 0.1043 1.0000 11.000 1.3735 0.03184 0.02533 -0.0680 0.1034 1.0000 11.250 1.3839 0.03319 0.02671 -0.0671 0.1024 1.0000 11.500 1.3952 0.03449 0.02804 -0.0663 0.1020 1.0000 11.750 1.4048 0.03594 0.02953 -0.0655 0.1014 1.0000 12.000 1.4131 0.03753 0.03115 -0.0646 0.1004 1.0000 12.250 1.4233 0.03899 0.03266 -0.0639 0.1003 1.0000 12.500 1.4285 0.04093 0.03463 -0.0631 0.0988 1.0000 12.750 1.4368 0.04261 0.03636 -0.0624 0.0984 1.0000 13.000 1.4432 0.04449 0.03827 -0.0617 0.0977 1.0000 13.250 1.4477 0.04659 0.04042 -0.0610 0.0965 1.0000 13.500 1.4523 0.04871 0.04258 -0.0604 0.0954 1.0000 13.750 1.4567 0.05088 0.04481 -0.0598 0.0948 1.0000 14.000 1.4614 0.05307 0.04706 -0.0593 0.0946 1.0000 14.250 1.4666 0.05518 0.04923 -0.0589 0.0941 1.0000 14.500 1.4722 0.05730 0.05140 -0.0585 0.0938 1.0000 14.750 1.4782 0.05937 0.05353 -0.0582 0.0935 1.0000 15.000 1.4831 0.06159 0.05581 -0.0579 0.0931 1.0000 15.250 1.4872 0.06391 0.05819 -0.0576 0.0926 1.0000 15.500 1.4914 0.06623 0.06056 -0.0574 0.0922 1.0000 15.750 1.4944 0.06868 0.06307 -0.0571 0.0914 1.0000 16.000 1.4970 0.07119 0.06563 -0.0570 0.0899 1.0000 16.250 1.4969 0.07404 0.06854 -0.0568 0.0887 1.0000 16.500 1.4989 0.07664 0.07119 -0.0567 0.0879 1.0000 16.750 1.4959 0.07989 0.07448 -0.0566 0.0862 1.0000 17.000 1.4950 0.08284 0.07748 -0.0565 0.0847 1.0000 17.250 1.4947 0.08579 0.08049 -0.0566 0.0839 1.0000 17.500 1.4984 0.08822 0.08298 -0.0566 0.0828 1.0000 17.750 1.4983 0.09117 0.08597 -0.0568 0.0794 1.0000 18.000 1.4861 0.09560 0.09033 -0.0570 0.0653 1.0000 18.250 1.4516 0.10296 0.09762 -0.0575 0.0485 1.0000 18.500 1.4226 0.10981 0.10449 -0.0583 0.0368 1.0000