XFOIL Version 6.96 Calculated polar for: GOE 12K AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.4443 0.09604 0.09255 -0.0484 0.9717 0.0692 -7.750 -0.4655 0.09210 0.08863 -0.0523 0.9665 0.0713 -7.500 -0.5009 0.08460 0.08089 -0.0613 0.9567 0.0730 -7.250 -0.4969 0.07829 0.07458 -0.0622 0.9547 0.0741 -7.000 -0.4768 0.07656 0.07292 -0.0612 0.9536 0.0753 -6.750 -0.4824 0.07486 0.07123 -0.0572 0.9484 0.0763 -6.500 -0.4721 0.07230 0.06861 -0.0572 0.9451 0.0785 -6.000 -0.4725 0.06258 0.05840 -0.0587 0.9361 0.0883 -5.750 -0.4594 0.06106 0.05693 -0.0573 0.9337 0.0900 -5.500 -0.4452 0.05999 0.05506 -0.0575 0.9300 0.1003 -5.250 -0.4301 0.05428 0.04958 -0.0583 0.9291 0.1025 -5.000 -0.4261 0.05311 0.04847 -0.0549 0.9245 0.1043 -4.750 -0.4143 0.05188 0.04719 -0.0530 0.9216 0.1089 -4.500 -0.4046 0.04899 0.04390 -0.0514 0.9190 0.1178 -4.250 -0.3851 0.04746 0.04238 -0.0509 0.9174 0.1209 -4.000 -0.3758 0.03832 0.03146 -0.0457 0.9156 0.0868 -3.750 -0.3572 0.03751 0.03040 -0.0439 0.9135 0.0863 -3.500 -0.3554 0.03562 0.02827 -0.0393 0.9094 0.0867 -3.250 -0.3397 0.03462 0.02705 -0.0371 0.9073 0.0865 -3.000 -0.3218 0.03363 0.02583 -0.0353 0.9057 0.0864 -2.750 -0.3033 0.03213 0.02410 -0.0337 0.9044 0.0870 -2.500 -0.2812 0.03106 0.02290 -0.0328 0.9031 0.0885 -2.250 -0.2542 0.03047 0.02217 -0.0327 0.9017 0.0891 -2.000 -0.2208 0.03008 0.02168 -0.0338 0.9003 0.0905 -1.750 -0.2132 0.02973 0.02125 -0.0301 0.8969 0.0910 -1.500 -0.1996 0.02958 0.02107 -0.0277 0.8954 0.0930 -1.250 -0.1825 0.02942 0.02085 -0.0259 0.8934 0.0947 -1.000 -0.1541 0.02911 0.02048 -0.0260 0.8895 0.0960 -0.750 -0.1092 0.02888 0.02018 -0.0290 0.8859 0.0981 -0.500 -0.0923 0.02866 0.01993 -0.0270 0.8799 0.0996 -0.250 -0.0724 0.02841 0.01969 -0.0256 0.8761 0.1015 0.000 -0.0412 0.02820 0.01956 -0.0263 0.8727 0.1058 0.250 -0.0002 0.02812 0.01952 -0.0286 0.8701 0.1104 0.500 0.0112 0.02807 0.01946 -0.0257 0.8639 0.1133 0.750 0.2442 0.02620 0.02074 -0.0711 0.8724 1.0000 1.000 0.2815 0.02633 0.02073 -0.0729 0.8703 1.0000 1.250 0.3219 0.02647 0.02079 -0.0753 0.8688 1.0000 1.500 0.3166 0.02682 0.02111 -0.0694 0.8593 1.0000 1.750 0.3514 0.02687 0.02110 -0.0707 0.8563 1.0000 2.000 0.3918 0.02686 0.02104 -0.0730 0.8543 1.0000 2.250 0.3992 0.02714 0.02130 -0.0694 0.8454 1.0000 2.500 0.4347 0.02704 0.02119 -0.0706 0.8417 1.0000 2.750 0.4746 0.02691 0.02105 -0.0728 0.8394 1.0000 3.000 0.4844 0.02729 0.02143 -0.0696 0.8316 1.0000 3.250 0.5155 0.02725 0.02141 -0.0702 0.8274 1.0000 3.500 0.5573 0.02690 0.02108 -0.0725 0.8248 1.0000 3.750 0.5748 0.02696 0.02117 -0.0705 0.8161 1.0000 4.000 0.6374 0.02521 0.01947 -0.0753 0.8105 1.0000 4.250 0.7098 0.02178 0.01609 -0.0805 0.7968 1.0000 4.500 0.7809 0.01899 0.01338 -0.0864 0.7933 1.0000 4.750 0.7948 0.01875 0.01320 -0.0831 0.7813 1.0000 5.000 0.8156 0.01819 0.01270 -0.0809 0.7696 1.0000 5.250 0.8413 0.01739 0.01196 -0.0794 0.7561 1.0000 5.500 0.8689 0.01660 0.01122 -0.0783 0.7380 1.0000 5.750 0.9023 0.01567 0.01032 -0.0782 0.7084 1.0000 6.000 0.9578 0.01447 0.00815 -0.0816 0.5244 1.0000 6.250 0.9468 0.01571 0.00885 -0.0741 0.4542 1.0000 6.750 0.9424 0.01787 0.01038 -0.0632 0.3322 1.0000 7.000 0.9315 0.01954 0.01137 -0.0568 0.2220 1.0000 7.250 0.9316 0.02101 0.01238 -0.0524 0.1619 1.0000 7.500 0.9399 0.02207 0.01323 -0.0494 0.1395 1.0000 7.750 0.9525 0.02290 0.01401 -0.0470 0.1273 1.0000 8.000 0.9657 0.02373 0.01480 -0.0448 0.1187 1.0000 8.250 0.9795 0.02456 0.01559 -0.0427 0.1113 1.0000 8.500 0.9947 0.02538 0.01641 -0.0408 0.1055 1.0000 8.750 1.0111 0.02610 0.01715 -0.0392 0.0998 1.0000 9.000 1.0277 0.02711 0.01808 -0.0377 0.0942 1.0000 9.250 1.0453 0.02776 0.01883 -0.0362 0.0893 1.0000 9.500 1.0626 0.02858 0.01963 -0.0348 0.0844 1.0000 9.750 1.0834 0.02956 0.02062 -0.0340 0.0794 1.0000 10.000 1.1011 0.03034 0.02149 -0.0326 0.0749 1.0000 10.250 1.1277 0.03162 0.02265 -0.0328 0.0693 1.0000 10.500 1.1427 0.03238 0.02359 -0.0309 0.0661 1.0000 10.750 1.1595 0.03329 0.02457 -0.0295 0.0622 1.0000 11.000 1.1875 0.03478 0.02602 -0.0300 0.0579 1.0000 11.250 1.2008 0.03575 0.02719 -0.0279 0.0552 1.0000 11.500 1.2158 0.03680 0.02835 -0.0264 0.0525 1.0000 11.750 1.2342 0.03795 0.02946 -0.0255 0.0500 1.0000 12.000 1.2546 0.03981 0.03152 -0.0248 0.0477 1.0000 12.250 1.2624 0.04107 0.03302 -0.0222 0.0456 1.0000 12.500 1.2745 0.04256 0.03466 -0.0203 0.0440 1.0000 12.750 1.2848 0.04394 0.03613 -0.0184 0.0426 1.0000 13.000 1.3063 0.04641 0.03859 -0.0185 0.0406 1.0000 13.250 1.3021 0.04822 0.04073 -0.0146 0.0399 1.0000 13.500 1.2984 0.05040 0.04323 -0.0112 0.0391 1.0000 13.750 1.2940 0.05264 0.04576 -0.0079 0.0381 1.0000 14.000 1.2891 0.05502 0.04836 -0.0049 0.0372 1.0000 14.250 1.2829 0.05774 0.05131 -0.0021 0.0366 1.0000 14.500 1.2734 0.06077 0.05459 0.0008 0.0363 1.0000 14.750 1.2717 0.06283 0.05673 0.0027 0.0355 1.0000 15.000 1.2652 0.06545 0.05949 0.0047 0.0350 1.0000 15.250 1.2483 0.06935 0.06364 0.0070 0.0350 1.0000 15.500 1.2431 0.07221 0.06656 0.0083 0.0344 1.0000 15.750 1.2196 0.07696 0.07158 0.0098 0.0344 1.0000 16.000 1.2016 0.08155 0.07633 0.0105 0.0341 1.0000 16.250 1.1703 0.08775 0.08282 0.0103 0.0343 1.0000 16.500 1.1427 0.09413 0.08942 0.0090 0.0343 1.0000