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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.9384 0.08211 0.07822 -0.0509 1.0000 0.0357 -18.250 -0.9824 0.07230 0.06824 -0.0569 1.0000 0.0359 -18.000 -1.0217 0.06319 0.05895 -0.0626 1.0000 0.0359 -17.750 -1.0520 0.05538 0.05096 -0.0677 1.0000 0.0362 -17.500 -1.0764 0.04943 0.04487 -0.0703 0.9868 0.0363 -17.250 -1.0473 0.04361 0.03874 -0.0823 0.8921 0.0371 -17.000 -1.0536 0.04030 0.03512 -0.0836 0.8444 0.0375 -16.750 -1.0605 0.03757 0.03219 -0.0837 0.8233 0.0379 -16.500 -1.0648 0.03523 0.02969 -0.0833 0.8084 0.0383 -16.250 -1.0704 0.03300 0.02734 -0.0824 0.7963 0.0387 -16.000 -1.0725 0.03121 0.02543 -0.0812 0.7858 0.0392 -15.750 -1.0717 0.02969 0.02381 -0.0797 0.7773 0.0397 -15.500 -1.0689 0.02840 0.02242 -0.0780 0.7683 0.0404 -15.250 -1.0640 0.02728 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0.00374 -0.0147 0.4049 0.1693 -1.000 0.1564 0.01202 0.00371 -0.0142 0.4012 0.1793 -0.750 0.1821 0.01197 0.00369 -0.0137 0.3972 0.1922 -0.500 0.2071 0.01191 0.00368 -0.0131 0.3934 0.2115 -0.250 0.2316 0.01184 0.00368 -0.0125 0.3901 0.2375 0.000 0.2568 0.01173 0.00368 -0.0119 0.3875 0.2671 0.250 0.2815 0.01162 0.00369 -0.0112 0.3845 0.3009 0.500 0.3057 0.01152 0.00371 -0.0105 0.3813 0.3375 0.750 0.3293 0.01142 0.00373 -0.0097 0.3781 0.3771 1.000 0.3518 0.01131 0.00375 -0.0087 0.3748 0.4218 1.250 0.3713 0.01110 0.00378 -0.0071 0.3718 0.4962 1.500 0.3889 0.01080 0.00381 -0.0051 0.3692 0.5898 1.750 0.4064 0.01056 0.00385 -0.0029 0.3664 0.6646 2.000 0.4230 0.01032 0.00394 -0.0005 0.3638 0.7546 2.250 0.4481 0.01026 0.00409 0.0003 0.3608 0.8197 2.500 0.4851 0.01036 0.00430 -0.0015 0.3577 0.8655 2.750 0.5274 0.01057 0.00452 -0.0044 0.3545 0.8952 3.000 0.5767 0.01079 0.00477 -0.0087 0.3517 0.9158 3.250 0.6147 0.01101 0.00499 -0.0106 0.3487 0.9309 3.500 0.6590 0.01129 0.00524 -0.0139 0.3452 0.9382 3.750 0.6814 0.01151 0.00543 -0.0128 0.3424 0.9485 4.000 0.7195 0.01178 0.00565 -0.0150 0.3395 0.9509 4.250 0.7565 0.01204 0.00588 -0.0169 0.3369 0.9542 4.500 0.7911 0.01225 0.00610 -0.0183 0.3347 0.9594 4.750 0.8194 0.01246 0.00630 -0.0185 0.3324 0.9651 5.000 0.8553 0.01266 0.00648 -0.0203 0.3295 0.9668 5.250 0.8894 0.01287 0.00667 -0.0218 0.3267 0.9691 5.500 0.9207 0.01310 0.00688 -0.0229 0.3239 0.9719 5.750 0.9474 0.01336 0.00710 -0.0230 0.3214 0.9756 6.000 0.9730 0.01357 0.00732 -0.0229 0.3194 0.9790 6.250 1.0058 0.01374 0.00751 -0.0242 0.3172 0.9803 6.500 1.0371 0.01393 0.00771 -0.0253 0.3148 0.9819 6.750 1.0675 0.01415 0.00793 -0.0263 0.3121 0.9838 7.000 1.0967 0.01440 0.00816 -0.0270 0.3095 0.9863 7.250 1.1236 0.01469 0.00843 -0.0274 0.3069 0.9890 7.500 1.1472 0.01504 0.00876 -0.0273 0.3041 0.9917 7.750 1.1780 0.01523 0.00899 -0.0284 0.3018 0.9932 8.000 1.2080 0.01545 0.00924 -0.0295 0.2993 0.9951 8.250 1.2369 0.01572 0.00952 -0.0304 0.2967 0.9972 8.500 1.2639 0.01602 0.00983 -0.0310 0.2939 0.9992 8.750 1.2733 0.01634 0.01016 -0.0284 0.2920 1.0000 9.000 1.2682 0.01676 0.01060 -0.0234 0.2903 1.0000 9.250 1.2672 0.01732 0.01116 -0.0194 0.2883 1.0000 9.500 1.2739 0.01780 0.01168 -0.0167 0.2868 1.0000 9.750 1.2825 0.01830 0.01222 -0.0143 0.2849 1.0000 10.000 1.2913 0.01886 0.01282 -0.0122 0.2829 1.0000 10.250 1.3000 0.01949 0.01348 -0.0102 0.2805 1.0000 10.500 1.3089 0.02018 0.01418 -0.0083 0.2784 1.0000 10.750 1.3175 0.02094 0.01495 -0.0065 0.2763 1.0000 11.000 1.3255 0.02178 0.01581 -0.0048 0.2743 1.0000 11.250 1.3336 0.02268 0.01671 -0.0032 0.2721 1.0000 11.500 1.3459 0.02340 0.01749 -0.0020 0.2705 1.0000 11.750 1.3570 0.02421 0.01835 -0.0008 0.2684 1.0000 12.000 1.3673 0.02511 0.01929 0.0003 0.2661 1.0000 12.250 1.3761 0.02613 0.02035 0.0014 0.2635 1.0000 12.500 1.3842 0.02723 0.02147 0.0025 0.2611 1.0000 12.750 1.3903 0.02850 0.02275 0.0037 0.2586 1.0000 13.000 1.3983 0.02968 0.02396 0.0046 0.2565 1.0000 13.250 1.4081 0.03080 0.02514 0.0054 0.2545 1.0000 13.500 1.4171 0.03200 0.02640 0.0061 0.2522 1.0000 13.750 1.4242 0.03338 0.02783 0.0068 0.2497 1.0000 14.000 1.4302 0.03490 0.02939 0.0074 0.2471 1.0000 14.250 1.4345 0.03660 0.03111 0.0080 0.2444 1.0000 14.500 1.4381 0.03842 0.03295 0.0085 0.2417 1.0000 14.750 1.4457 0.03997 0.03457 0.0089 0.2393 1.0000 15.000 1.4484 0.04202 0.03669 0.0091 0.2355 1.0000 15.250 1.4493 0.04426 0.03896 0.0094 0.2319 1.0000 15.500 1.4481 0.04671 0.04141 0.0096 0.2283 1.0000 15.750 1.4494 0.04904 0.04382 0.0097 0.2246 1.0000 16.000 1.4483 0.05163 0.04647 0.0097 0.2205 1.0000 16.250 1.4425 0.05471 0.04957 0.0097 0.2157 1.0000 16.500 1.4397 0.05754 0.05243 0.0096 0.2123 1.0000 16.750 1.4374 0.06038 0.05534 0.0094 0.2082 1.0000 17.000 1.4291 0.06389 0.05888 0.0092 0.2030 1.0000 17.250 1.4217 0.06736 0.06237 0.0088 0.1991 1.0000 17.500 1.4195 0.07030 0.06538 0.0085 0.1955 1.0000 17.750 1.4134 0.07371 0.06884 0.0080 0.1915 1.0000 18.000 1.4027 0.07768 0.07281 0.0075 0.1872 1.0000 18.250 1.3998 0.08079 0.07598 0.0069 0.1836 1.0000 18.500 1.3923 0.08450 0.07975 0.0063 0.1796 1.0000 18.750 1.3865 0.08801 0.08328 0.0056 0.1759 1.0000