XFOIL Version 6.96 Calculated polar for: GOE 735 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 ------ -------- --------- --------- -------- -------- -------- -19.500 -1.0682 0.08044 0.07711 -0.0500 1.0000 0.0330 -19.250 -1.1202 0.06978 0.06627 -0.0564 1.0000 0.0329 -19.000 -1.1627 0.06025 0.05656 -0.0624 1.0000 0.0330 -18.750 -1.1910 0.05261 0.04875 -0.0675 1.0000 0.0332 -18.500 -1.2100 0.04655 0.04254 -0.0715 1.0000 0.0333 -18.250 -1.2185 0.04224 0.03812 -0.0740 1.0000 0.0336 -18.000 -1.2241 0.03863 0.03440 -0.0758 1.0000 0.0339 -17.750 -1.2260 0.03574 0.03142 -0.0767 1.0000 0.0343 -17.500 -1.2244 0.03342 0.02902 -0.0770 1.0000 0.0346 -17.250 -1.2214 0.03144 0.02696 -0.0769 1.0000 0.0349 -17.000 -1.1959 0.02971 0.02513 -0.0800 0.9468 0.0354 -16.750 -1.1784 0.02758 0.02266 -0.0829 0.8602 0.0362 -16.500 -1.1799 0.02629 0.02121 -0.0806 0.8323 0.0365 -16.250 -1.1780 0.02515 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0.00305 -0.0135 0.4271 0.1447 -2.000 0.0376 0.01006 0.00298 -0.0131 0.4237 0.1522 -1.750 0.0646 0.01001 0.00293 -0.0128 0.4196 0.1589 -1.500 0.0908 0.00994 0.00289 -0.0123 0.4156 0.1694 -1.250 0.1168 0.00991 0.00287 -0.0118 0.4108 0.1813 -1.000 0.1432 0.00980 0.00284 -0.0114 0.4081 0.1982 -0.750 0.1691 0.00967 0.00281 -0.0109 0.4051 0.2237 -0.500 0.1942 0.00952 0.00278 -0.0103 0.4015 0.2589 -0.250 0.2188 0.00940 0.00278 -0.0096 0.3976 0.2994 0.000 0.2430 0.00931 0.00279 -0.0089 0.3930 0.3390 0.250 0.2678 0.00918 0.00280 -0.0082 0.3903 0.3806 0.500 0.2917 0.00898 0.00278 -0.0073 0.3878 0.4339 0.750 0.3110 0.00864 0.00278 -0.0057 0.3849 0.5312 1.000 0.3294 0.00836 0.00278 -0.0037 0.3819 0.6216 1.250 0.3450 0.00810 0.00281 -0.0011 0.3787 0.7117 1.500 0.3615 0.00795 0.00290 0.0014 0.3749 0.7906 1.750 0.3855 0.00787 0.00299 0.0025 0.3725 0.8417 2.000 0.4152 0.00786 0.00309 0.0023 0.3700 0.8776 2.250 0.4490 0.00794 0.00321 0.0013 0.3668 0.8996 2.500 0.4830 0.00806 0.00333 0.0001 0.3634 0.9160 2.750 0.5162 0.00824 0.00348 -0.0010 0.3598 0.9283 3.000 0.5549 0.00846 0.00367 -0.0032 0.3560 0.9363 3.250 0.5839 0.00858 0.00380 -0.0033 0.3542 0.9457 3.500 0.6243 0.00876 0.00397 -0.0058 0.3517 0.9507 3.750 0.6695 0.00902 0.00421 -0.0092 0.3485 0.9545 4.000 0.7066 0.00930 0.00444 -0.0111 0.3452 0.9591 4.250 0.7349 0.00956 0.00466 -0.0112 0.3416 0.9645 4.500 0.7745 0.00979 0.00486 -0.0137 0.3385 0.9656 4.750 0.8140 0.00994 0.00501 -0.0161 0.3367 0.9668 5.000 0.8542 0.01011 0.00518 -0.0186 0.3343 0.9685 5.250 0.8930 0.01031 0.00536 -0.0210 0.3315 0.9707 5.500 0.9266 0.01051 0.00553 -0.0223 0.3285 0.9736 5.750 0.9490 0.01077 0.00576 -0.0214 0.3256 0.9785 6.000 0.9853 0.01099 0.00595 -0.0234 0.3222 0.9795 6.250 1.0227 0.01109 0.00606 -0.0256 0.3204 0.9804 6.500 1.0586 0.01120 0.00618 -0.0274 0.3181 0.9816 6.750 1.0929 0.01134 0.00632 -0.0290 0.3153 0.9829 7.000 1.1255 0.01151 0.00647 -0.0303 0.3126 0.9845 7.250 1.1564 0.01174 0.00667 -0.0313 0.3095 0.9866 7.500 1.1841 0.01205 0.00695 -0.0318 0.3061 0.9891 7.750 1.2102 0.01222 0.00715 -0.0318 0.3048 0.9917 8.000 1.2443 0.01231 0.00726 -0.0334 0.3029 0.9925 8.250 1.2780 0.01243 0.00740 -0.0350 0.3007 0.9936 8.500 1.3106 0.01259 0.00757 -0.0365 0.2983 0.9950 8.750 1.3419 0.01280 0.00777 -0.0377 0.2959 0.9966 9.000 1.3717 0.01306 0.00802 -0.0388 0.2931 0.9983 9.250 1.4005 0.01341 0.00834 -0.0398 0.2899 0.9997 9.500 1.4202 0.01356 0.00855 -0.0387 0.2886 1.0000 9.750 1.4322 0.01376 0.00878 -0.0362 0.2870 1.0000 10.000 1.4354 0.01398 0.00903 -0.0321 0.2855 1.0000 10.250 1.4294 0.01426 0.00935 -0.0266 0.2839 1.0000 10.500 1.4283 0.01469 0.00981 -0.0224 0.2821 1.0000 10.750 1.4306 0.01523 0.01037 -0.0189 0.2802 1.0000 11.000 1.4340 0.01588 0.01102 -0.0159 0.2780 1.0000 11.250 1.4370 0.01666 0.01181 -0.0131 0.2753 1.0000 11.500 1.4465 0.01728 0.01245 -0.0112 0.2736 1.0000 11.750 1.4592 0.01781 0.01304 -0.0097 0.2722 1.0000 12.000 1.4713 0.01841 0.01368 -0.0083 0.2705 1.0000 12.250 1.4830 0.01907 0.01437 -0.0069 0.2684 1.0000 12.500 1.4931 0.01986 0.01518 -0.0055 0.2658 1.0000 12.750 1.5012 0.02080 0.01614 -0.0040 0.2635 1.0000 13.000 1.5047 0.02205 0.01737 -0.0023 0.2597 1.0000 13.250 1.5172 0.02284 0.01821 -0.0013 0.2575 1.0000 13.500 1.5297 0.02365 0.01907 -0.0005 0.2552 1.0000 13.750 1.5398 0.02463 0.02008 0.0005 0.2523 1.0000 14.000 1.5453 0.02596 0.02142 0.0016 0.2488 1.0000 14.250 1.5482 0.02748 0.02295 0.0028 0.2457 1.0000 14.500 1.5562 0.02872 0.02423 0.0036 0.2423 1.0000 14.750 1.5662 0.02984 0.02540 0.0042 0.2400 1.0000 15.000 1.5715 0.03138 0.02697 0.0049 0.2359 1.0000 15.250 1.5704 0.03351 0.02910 0.0057 0.2318 1.0000 15.500 1.5735 0.03534 0.03096 0.0063 0.2286 1.0000 15.750 1.5819 0.03679 0.03247 0.0066 0.2255 1.0000 16.000 1.5855 0.03869 0.03441 0.0070 0.2224 1.0000 16.250 1.5800 0.04143 0.03716 0.0074 0.2177 1.0000 16.500 1.5802 0.04373 0.03949 0.0077 0.2138 1.0000 16.750 1.5826 0.04587 0.04169 0.0079 0.2105 1.0000 17.000 1.5790 0.04860 0.04445 0.0080 0.2064 1.0000 17.250 1.5685 0.05203 0.04789 0.0082 0.2021 1.0000 17.500 1.5693 0.05443 0.05035 0.0081 0.1995 1.0000 17.750 1.5664 0.05723 0.05319 0.0080 0.1954 1.0000 18.000 1.5572 0.06069 0.05667 0.0079 0.1914 1.0000 18.250 1.5453 0.06452 0.06054 0.0077 0.1876 1.0000 18.500 1.5433 0.06734 0.06341 0.0074 0.1838 1.0000 18.750 1.5374 0.07060 0.06671 0.0070 0.1807 1.0000 19.000 1.5192 0.07530 0.07142 0.0064 0.1761 1.0000 19.250 1.5187 0.07804 0.07422 0.0060 0.1736 1.0000