XFOIL Version 6.96 Calculated polar for: GOE 436 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 ------ -------- --------- --------- -------- -------- -------- -14.500 -1.1138 0.03084 0.02779 -0.0832 1.0000 0.0121 -14.250 -1.1209 0.02815 0.02490 -0.0800 1.0000 0.0124 -14.000 -1.1059 0.02563 0.02218 -0.0806 0.9985 0.0131 -13.750 -1.0848 0.02387 0.02025 -0.0813 0.9966 0.0137 -13.500 -1.0614 0.02243 0.01867 -0.0819 0.9948 0.0145 -13.250 -1.0389 0.02105 0.01717 -0.0823 0.9928 0.0155 -13.000 -1.0152 0.01998 0.01600 -0.0824 0.9905 0.0167 -12.750 -0.9891 0.01911 0.01503 -0.0829 0.9884 0.0176 -12.500 -0.9614 0.01827 0.01413 -0.0835 0.9866 0.0188 -12.250 -0.9319 0.01758 0.01337 -0.0844 0.9850 0.0200 -12.000 -0.9028 0.01696 0.01266 -0.0851 0.9832 0.0211 -11.750 -0.8771 0.01641 0.01206 -0.0850 0.9797 0.0220 -11.500 -0.8481 0.01596 0.01158 -0.0855 0.9772 0.0231 -11.250 -0.8175 0.01551 0.01108 -0.0864 0.9751 0.0240 -11.000 -0.7859 0.01505 0.01054 -0.0874 0.9736 0.0248 -10.750 -0.7566 0.01462 0.01003 -0.0878 0.9708 0.0254 -10.500 -0.7293 0.01419 0.00956 -0.0879 0.9660 0.0261 -10.250 -0.6978 0.01384 0.00919 -0.0888 0.9625 0.0269 -10.000 -0.6653 0.01353 0.00885 -0.0899 0.9597 0.0277 -9.750 -0.6383 0.01325 0.00851 -0.0897 0.9537 0.0284 -9.500 -0.6081 0.01294 0.00814 -0.0902 0.9481 0.0291 -9.250 -0.5790 0.01262 0.00776 -0.0905 0.9416 0.0297 -9.000 -0.5506 0.01235 0.00742 -0.0906 0.9332 0.0301 -8.750 -0.5232 0.01200 0.00700 -0.0905 0.9243 0.0309 -8.500 -0.4954 0.01176 0.00673 -0.0905 0.9140 0.0318 -8.250 -0.4683 0.01160 0.00652 -0.0902 0.8999 0.0325 -8.000 -0.4418 0.01144 0.00628 -0.0898 0.8842 0.0332 -7.500 -0.3906 0.01103 0.00567 -0.0887 0.8548 0.0342 -7.250 -0.3651 0.01081 0.00537 -0.0881 0.8429 0.0346 -7.000 -0.3394 0.01061 0.00508 -0.0875 0.8325 0.0351 -6.750 -0.3136 0.01044 0.00482 -0.0870 0.8216 0.0355 -6.500 -0.2874 0.01027 0.00458 -0.0865 0.8128 0.0358 -6.000 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0.2547 0.00886 0.00163 -0.0750 0.4450 0.0555 -1.000 0.2807 0.00890 0.00162 -0.0746 0.4296 0.0571 -0.750 0.3071 0.00893 0.00160 -0.0741 0.4178 0.0588 -0.500 0.3335 0.00897 0.00159 -0.0738 0.4075 0.0602 -0.250 0.3601 0.00897 0.00157 -0.0734 0.3988 0.0628 0.000 0.3864 0.00899 0.00157 -0.0730 0.3902 0.0663 0.250 0.4132 0.00899 0.00157 -0.0727 0.3830 0.0697 0.500 0.4398 0.00903 0.00158 -0.0723 0.3759 0.0725 0.750 0.4664 0.00903 0.00159 -0.0720 0.3705 0.0795 1.250 0.5193 0.00903 0.00165 -0.0713 0.3594 0.1065 1.500 0.5455 0.00898 0.00169 -0.0709 0.3550 0.1439 1.750 0.5713 0.00887 0.00173 -0.0704 0.3498 0.2056 2.000 0.5943 0.00856 0.00181 -0.0696 0.3427 0.3759 2.250 0.6120 0.00786 0.00191 -0.0678 0.3358 0.6765 2.500 0.6613 0.00737 0.00215 -0.0723 0.3251 0.9688 2.750 0.7118 0.00751 0.00225 -0.0773 0.3189 0.9898 3.000 0.7574 0.00766 0.00234 -0.0812 0.3123 0.9992 3.250 0.7860 0.00778 0.00242 -0.0814 0.3047 1.0000 3.500 0.8087 0.00793 0.00251 -0.0803 0.2956 1.0000 3.750 0.8324 0.00804 0.00259 -0.0794 0.2907 1.0000 4.000 0.8559 0.00816 0.00268 -0.0785 0.2840 1.0000 4.250 0.8790 0.00832 0.00279 -0.0775 0.2759 1.0000 4.500 0.9023 0.00846 0.00290 -0.0765 0.2678 1.0000 4.750 0.9257 0.00861 0.00302 -0.0756 0.2610 1.0000 5.000 0.9491 0.00877 0.00314 -0.0746 0.2532 1.0000 5.250 0.9722 0.00894 0.00328 -0.0737 0.2448 1.0000 5.500 0.9948 0.00916 0.00344 -0.0726 0.2334 1.0000 5.750 1.0167 0.00941 0.00362 -0.0715 0.2184 1.0000 6.000 1.0364 0.00981 0.00388 -0.0700 0.1925 1.0000 6.250 1.0545 0.01032 0.00422 -0.0682 0.1626 1.0000 6.500 1.0738 0.01076 0.00455 -0.0667 0.1411 1.0000 6.750 1.0936 0.01117 0.00487 -0.0652 0.1250 1.0000 7.000 1.1143 0.01151 0.00516 -0.0640 0.1131 1.0000 7.250 1.1346 0.01188 0.00546 -0.0626 0.1001 1.0000 7.500 1.1484 0.01268 0.00603 -0.0603 0.0630 1.0000 7.750 1.1683 0.01306 0.00638 -0.0589 0.0576 1.0000 8.000 1.1886 0.01339 0.00671 -0.0576 0.0533 1.0000 8.250 1.2098 0.01366 0.00699 -0.0565 0.0518 1.0000 8.500 1.2306 0.01394 0.00729 -0.0553 0.0506 1.0000 8.750 1.2507 0.01425 0.00762 -0.0540 0.0491 1.0000 9.000 1.2698 0.01459 0.00798 -0.0525 0.0474 1.0000 9.250 1.2873 0.01494 0.00834 -0.0507 0.0459 1.0000 9.500 1.3033 0.01531 0.00873 -0.0487 0.0440 1.0000 9.750 1.3203 0.01564 0.00909 -0.0469 0.0433 1.0000 10.000 1.3382 0.01593 0.00941 -0.0453 0.0421 1.0000 10.250 1.3551 0.01628 0.00979 -0.0435 0.0405 1.0000 10.500 1.3711 0.01670 0.01022 -0.0417 0.0385 1.0000 10.750 1.3859 0.01718 0.01070 -0.0398 0.0363 1.0000 11.000 1.4021 0.01760 0.01116 -0.0381 0.0344 1.0000 11.250 1.4157 0.01817 0.01170 -0.0362 0.0296 1.0000 11.750 1.4346 0.01982 0.01327 -0.0315 0.0166 1.0000 12.000 1.4450 0.02063 0.01411 -0.0294 0.0146 1.0000 12.250 1.4550 0.02150 0.01502 -0.0274 0.0132 1.0000 12.500 1.4661 0.02233 0.01590 -0.0257 0.0125 1.0000 12.750 1.4760 0.02329 0.01691 -0.0240 0.0117 1.0000 13.000 1.4847 0.02437 0.01803 -0.0223 0.0111 1.0000 13.250 1.4919 0.02561 0.01933 -0.0206 0.0104 1.0000 13.500 1.5011 0.02676 0.02054 -0.0193 0.0100 1.0000 13.750 1.5089 0.02808 0.02192 -0.0180 0.0096 1.0000 14.000 1.5155 0.02954 0.02345 -0.0168 0.0092 1.0000 14.250 1.5209 0.03118 0.02515 -0.0157 0.0088 1.0000 14.500 1.5247 0.03304 0.02708 -0.0147 0.0085 1.0000 14.750 1.5266 0.03516 0.02927 -0.0138 0.0081 1.0000 15.000 1.5274 0.03749 0.03168 -0.0132 0.0080 1.0000 15.250 1.5295 0.03981 0.03409 -0.0128 0.0078 1.0000 15.500 1.5310 0.04229 0.03666 -0.0126 0.0077 1.0000 15.750 1.5308 0.04507 0.03952 -0.0125 0.0075 1.0000 16.000 1.5284 0.04821 0.04276 -0.0127 0.0074 1.0000 16.250 1.5258 0.05146 0.04610 -0.0131 0.0072 1.0000 16.500 1.5208 0.05508 0.04982 -0.0136 0.0071 1.0000 16.750 1.5148 0.05892 0.05375 -0.0143 0.0069 1.0000 17.000 1.5073 0.06310 0.05803 -0.0152 0.0068 1.0000 17.250 1.4973 0.06766 0.06270 -0.0163 0.0068 1.0000 17.500 1.4879 0.07223 0.06737 -0.0175 0.0066 1.0000 17.750 1.4773 0.07705 0.07227 -0.0188 0.0065 1.0000 18.000 1.4649 0.08215 0.07746 -0.0203 0.0063 1.0000 18.250 1.4537 0.08712 0.08254 -0.0218 0.0064 1.0000 18.500 1.4407 0.09242 0.08794 -0.0235 0.0062 1.0000 18.750 1.4285 0.09769 0.09331 -0.0253 0.0062 1.0000