XFOIL Version 6.96 Calculated polar for: GOE 383 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 -0.1690 0.14770 0.14579 -0.0512 0.9055 0.0314 -16.500 -0.7485 0.06968 0.06678 -0.0884 1.0000 0.0304 -16.250 -0.7869 0.05994 0.05681 -0.0962 1.0000 0.0304 -16.000 -0.8076 0.05297 0.04963 -0.1025 0.9844 0.0304 -15.750 -0.8223 0.04787 0.04434 -0.1062 0.9718 0.0304 -15.500 -0.8352 0.04397 0.04027 -0.1077 0.9600 0.0305 -15.250 -0.8447 0.04083 0.03697 -0.1082 0.9493 0.0305 -15.000 -0.8504 0.03810 0.03408 -0.1084 0.9386 0.0306 -14.750 -0.8525 0.03575 0.03158 -0.1084 0.9283 0.0306 -14.500 -0.8528 0.03376 0.02945 -0.1078 0.9174 0.0307 -14.250 -0.8500 0.03203 0.02757 -0.1071 0.9048 0.0308 -14.000 -0.8454 0.03054 0.02595 -0.1060 0.8909 0.0309 -13.750 -0.8392 0.02927 0.02452 -0.1047 0.8751 0.0309 -13.500 -0.8311 0.02816 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0.0434 -4.000 0.0567 0.01102 0.00398 -0.0829 0.5822 0.0444 -3.750 0.0849 0.01082 0.00381 -0.0829 0.5798 0.0457 -3.500 0.1134 0.01068 0.00368 -0.0830 0.5770 0.0471 -3.250 0.1421 0.01057 0.00356 -0.0830 0.5739 0.0485 -3.000 0.1699 0.01041 0.00339 -0.0829 0.5707 0.0509 -2.750 0.1980 0.01034 0.00329 -0.0829 0.5667 0.0534 -2.500 0.2261 0.01019 0.00317 -0.0829 0.5634 0.0580 -2.250 0.2541 0.00996 0.00302 -0.0829 0.5605 0.0700 -2.000 0.2806 0.00957 0.00290 -0.0828 0.5570 0.1317 -1.500 0.3354 0.00919 0.00273 -0.0826 0.5487 0.1948 -1.250 0.3619 0.00897 0.00270 -0.0825 0.5440 0.2545 -1.000 0.3903 0.00880 0.00267 -0.0826 0.5406 0.2923 -0.750 0.4186 0.00867 0.00264 -0.0827 0.5359 0.3255 -0.500 0.4459 0.00852 0.00261 -0.0826 0.5304 0.3681 -0.250 0.4722 0.00833 0.00259 -0.0824 0.5244 0.4337 0.000 0.4994 0.00810 0.00258 -0.0824 0.5187 0.5047 0.250 0.5255 0.00791 0.00260 -0.0821 0.5114 0.5789 0.500 0.5518 0.00781 0.00265 -0.0818 0.5043 0.6389 0.750 0.5792 0.00778 0.00270 -0.0817 0.4960 0.6793 1.000 0.6055 0.00780 0.00277 -0.0813 0.4867 0.7144 1.250 0.6326 0.00782 0.00283 -0.0812 0.4773 0.7421 1.500 0.6590 0.00791 0.00291 -0.0808 0.4678 0.7615 1.750 0.6859 0.00797 0.00300 -0.0807 0.4594 0.7811 2.000 0.7119 0.00809 0.00310 -0.0803 0.4504 0.7985 2.750 0.7891 0.00837 0.00346 -0.0790 0.4275 0.8674 3.000 0.8134 0.00848 0.00361 -0.0782 0.4216 0.8941 3.250 0.8368 0.00865 0.00377 -0.0773 0.4157 0.9179 3.500 0.8625 0.00873 0.00390 -0.0768 0.4125 0.9395 3.750 0.8898 0.00886 0.00403 -0.0766 0.4087 0.9568 4.000 0.9198 0.00904 0.00419 -0.0772 0.4043 0.9700 4.250 0.9517 0.00927 0.00438 -0.0782 0.3994 0.9809 4.500 0.9881 0.00946 0.00455 -0.0802 0.3960 0.9875 4.750 1.0255 0.00961 0.00470 -0.0824 0.3929 0.9924 5.000 1.0657 0.00980 0.00486 -0.0853 0.3890 0.9951 5.250 1.1061 0.01003 0.00506 -0.0882 0.3848 0.9985 5.500 1.1313 0.01026 0.00525 -0.0881 0.3806 1.0000 5.750 1.1458 0.01036 0.00535 -0.0856 0.3782 1.0000 6.000 1.1633 0.01045 0.00545 -0.0837 0.3760 1.0000 6.250 1.1798 0.01056 0.00557 -0.0817 0.3732 1.0000 6.500 1.1957 0.01072 0.00572 -0.0795 0.3700 1.0000 6.750 1.2128 0.01094 0.00592 -0.0777 0.3664 1.0000 7.000 1.2294 0.01126 0.00620 -0.0760 0.3618 1.0000 7.250 1.2534 0.01139 0.00636 -0.0755 0.3591 1.0000 7.500 1.2759 0.01158 0.00657 -0.0748 0.3555 1.0000 7.750 1.2969 0.01185 0.00682 -0.0740 0.3513 1.0000 8.000 1.3156 0.01221 0.00716 -0.0728 0.3464 1.0000 8.250 1.3373 0.01249 0.00744 -0.0721 0.3429 1.0000 8.500 1.3602 0.01273 0.00770 -0.0717 0.3393 1.0000 8.750 1.3808 0.01306 0.00803 -0.0709 0.3348 1.0000 9.000 1.3988 0.01352 0.00847 -0.0698 0.3295 1.0000 9.250 1.4199 0.01387 0.00883 -0.0692 0.3246 1.0000 9.500 1.4393 0.01429 0.00925 -0.0684 0.3180 1.0000 9.750 1.4550 0.01491 0.00982 -0.0671 0.3107 1.0000 10.000 1.4736 0.01541 0.01032 -0.0663 0.3026 1.0000 10.250 1.4875 0.01617 0.01104 -0.0650 0.2935 1.0000 10.500 1.5019 0.01693 0.01177 -0.0638 0.2839 1.0000 10.750 1.5147 0.01781 0.01263 -0.0625 0.2749 1.0000 11.250 1.5379 0.01983 0.01460 -0.0600 0.2577 1.0000 11.500 1.5459 0.02113 0.01587 -0.0585 0.2497 1.0000 11.750 1.5580 0.02220 0.01694 -0.0575 0.2430 1.0000 12.250 1.5754 0.02489 0.01962 -0.0552 0.2300 1.0000 12.500 1.5817 0.02648 0.02120 -0.0540 0.2238 1.0000 12.750 1.5906 0.02791 0.02265 -0.0530 0.2189 1.0000 13.000 1.5995 0.02939 0.02414 -0.0522 0.2143 1.0000 13.250 1.6042 0.03122 0.02598 -0.0511 0.2095 1.0000 13.500 1.6124 0.03281 0.02760 -0.0504 0.2056 1.0000 13.750 1.6201 0.03447 0.02929 -0.0497 0.2014 1.0000 14.000 1.6234 0.03653 0.03136 -0.0488 0.1969 1.0000 14.250 1.6287 0.03842 0.03326 -0.0480 0.1930 1.0000 14.500 1.6357 0.04021 0.03510 -0.0474 0.1893 1.0000 14.750 1.6393 0.04231 0.03721 -0.0467 0.1850 1.0000 15.000 1.6398 0.04473 0.03965 -0.0460 0.1807 1.0000 15.250 1.6465 0.04658 0.04154 -0.0455 0.1767 1.0000 15.500 1.6466 0.04908 0.04405 -0.0448 0.1718 1.0000 15.750 1.6471 0.05157 0.04657 -0.0442 0.1671 1.0000 16.000 1.6481 0.05405 0.04906 -0.0437 0.1614 1.0000 16.250 1.6440 0.05704 0.05206 -0.0431 0.1556 1.0000 16.500 1.6404 0.06001 0.05503 -0.0426 0.1481 1.0000 16.750 1.6321 0.06357 0.05859 -0.0420 0.1393 1.0000 17.000 1.6162 0.06797 0.06296 -0.0414 0.1268 1.0000 17.250 1.5833 0.07433 0.06923 -0.0408 0.1055 1.0000 17.500 1.5448 0.08158 0.07639 -0.0404 0.0852 1.0000 17.750 1.5220 0.08718 0.08200 -0.0404 0.0773 1.0000