XFOIL Version 6.96 Calculated polar for: GOE 509 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.2647 0.10834 0.10593 -0.0525 0.9881 0.0089 -11.000 -0.2569 0.10388 0.10149 -0.0559 0.9865 0.0093 -10.000 -0.5059 0.02820 0.02480 -0.1011 0.9575 0.0106 -9.750 -0.4964 0.02447 0.02061 -0.1004 0.9524 0.0109 -9.500 -0.4747 0.02221 0.01799 -0.1007 0.9494 0.0113 -9.250 -0.4655 0.02090 0.01645 -0.0975 0.9415 0.0116 -9.000 -0.4441 0.01945 0.01475 -0.0969 0.9366 0.0119 -8.750 -0.4287 0.01859 0.01377 -0.0946 0.9288 0.0123 -8.500 -0.4066 0.01782 0.01288 -0.0937 0.9214 0.0128 -8.250 -0.3916 0.01726 0.01222 -0.0910 0.9085 0.0132 -7.750 -0.3396 0.01569 0.01031 -0.0904 0.8749 0.0145 -7.500 -0.3049 0.01490 0.00930 -0.0919 0.8548 0.0154 -7.250 -0.2737 0.01450 0.00873 -0.0925 0.8339 0.0163 -7.000 -0.2476 0.01415 0.00820 -0.0921 0.8173 0.0171 -6.750 -0.2231 0.01377 0.00764 -0.0913 0.8047 0.0181 -6.500 -0.1991 0.01339 0.00711 -0.0904 0.7937 0.0191 -6.250 -0.1743 0.01320 0.00684 -0.0897 0.7835 0.0202 -6.000 -0.1492 0.01304 0.00660 -0.0890 0.7737 0.0215 -5.750 -0.1247 0.01278 0.00621 -0.0882 0.7641 0.0228 -5.500 -0.1005 0.01249 0.00582 -0.0874 0.7550 0.0241 -5.250 -0.0753 0.01230 0.00559 -0.0867 0.7473 0.0253 -5.000 -0.0502 0.01217 0.00538 -0.0860 0.7390 0.0269 -4.750 -0.0252 0.01196 0.00509 -0.0853 0.7304 0.0282 -4.500 -0.0010 0.01170 0.00474 -0.0844 0.7213 0.0297 -4.250 0.0241 0.01151 0.00453 -0.0837 0.7128 0.0312 -4.000 0.0488 0.01140 0.00434 -0.0829 0.7034 0.0328 -3.750 0.0734 0.01124 0.00411 -0.0821 0.6918 0.0343 -3.500 0.0980 0.01113 0.00391 -0.0813 0.6803 0.0354 -3.250 0.1215 0.01087 0.00360 -0.0803 0.6692 0.0374 -3.000 0.1458 0.01074 0.00342 -0.0794 0.6577 0.0391 -2.750 0.1702 0.01063 0.00325 -0.0785 0.6459 0.0408 -2.500 0.1943 0.01054 0.00308 -0.0776 0.6328 0.0426 -2.250 0.2180 0.01046 0.00293 -0.0766 0.6181 0.0438 -2.000 0.2408 0.01034 0.00273 -0.0754 0.6001 0.0467 -1.750 0.2628 0.01033 0.00263 -0.0741 0.5764 0.0497 -1.500 0.2833 0.01040 0.00253 -0.0724 0.5401 0.0526 -1.250 0.3025 0.01053 0.00247 -0.0705 0.4984 0.0557 -0.500 0.3665 0.01075 0.00241 -0.0663 0.4387 0.0785 -0.250 0.3892 0.01075 0.00240 -0.0652 0.4311 0.0952 0.000 0.4115 0.01065 0.00239 -0.0641 0.4246 0.1303 0.250 0.4322 0.01050 0.00245 -0.0626 0.4193 0.2139 0.500 0.4554 0.01051 0.00252 -0.0616 0.4151 0.2507 0.750 0.4795 0.01054 0.00257 -0.0608 0.4112 0.2723 1.000 0.5031 0.01058 0.00263 -0.0599 0.4068 0.2903 1.250 0.5260 0.01066 0.00268 -0.0589 0.4015 0.3037 1.500 0.5496 0.01069 0.00273 -0.0579 0.3969 0.3166 1.750 0.5732 0.01071 0.00279 -0.0570 0.3926 0.3316 2.000 0.5961 0.01074 0.00285 -0.0560 0.3889 0.3515 2.250 0.6184 0.01078 0.00292 -0.0549 0.3852 0.3700 2.500 0.6410 0.01079 0.00298 -0.0538 0.3820 0.3917 2.750 0.6612 0.01062 0.00303 -0.0523 0.3781 0.4690 3.750 0.8965 0.01071 0.00416 -0.0805 0.3451 0.9888 4.000 0.9309 0.01090 0.00431 -0.0821 0.3372 0.9925 4.250 0.9663 0.01106 0.00444 -0.0840 0.3280 0.9954 4.500 1.0044 0.01124 0.00457 -0.0865 0.3175 0.9983 4.750 1.0379 0.01140 0.00470 -0.0880 0.3068 1.0000 5.000 1.0569 0.01160 0.00484 -0.0864 0.2941 1.0000 5.250 1.0750 0.01185 0.00502 -0.0845 0.2790 1.0000 5.500 1.0908 0.01219 0.00525 -0.0823 0.2585 1.0000 5.750 1.1049 0.01262 0.00555 -0.0798 0.2339 1.0000 6.000 1.1188 0.01306 0.00587 -0.0772 0.2136 1.0000 6.250 1.1340 0.01342 0.00617 -0.0749 0.2014 1.0000 6.500 1.1495 0.01375 0.00646 -0.0726 0.1920 1.0000 6.750 1.1635 0.01408 0.00676 -0.0700 0.1836 1.0000 7.000 1.1763 0.01438 0.00704 -0.0672 0.1775 1.0000 7.250 1.1892 0.01467 0.00732 -0.0644 0.1725 1.0000 7.500 1.2039 0.01491 0.00760 -0.0620 0.1694 1.0000 7.750 1.2180 0.01521 0.00791 -0.0595 0.1653 1.0000 8.000 1.2314 0.01556 0.00825 -0.0570 0.1604 1.0000 8.250 1.2461 0.01588 0.00859 -0.0547 0.1566 1.0000 8.500 1.2614 0.01619 0.00894 -0.0526 0.1524 1.0000 8.750 1.2759 0.01656 0.00932 -0.0504 0.1478 1.0000 9.000 1.2895 0.01699 0.00975 -0.0481 0.1431 1.0000 9.250 1.3051 0.01734 0.01014 -0.0462 0.1378 1.0000 9.500 1.3173 0.01788 0.01064 -0.0439 0.1251 1.0000 9.750 1.3176 0.01905 0.01157 -0.0399 0.0888 1.0000 10.000 1.3218 0.02005 0.01251 -0.0366 0.0746 1.0000 10.250 1.3295 0.02091 0.01337 -0.0339 0.0609 1.0000 10.500 1.3263 0.02245 0.01477 -0.0300 0.0373 1.0000 10.750 1.3335 0.02343 0.01579 -0.0276 0.0342 1.0000 11.000 1.3416 0.02442 0.01683 -0.0254 0.0320 1.0000 11.250 1.3512 0.02535 0.01784 -0.0235 0.0309 1.0000 11.500 1.3602 0.02636 0.01893 -0.0217 0.0296 1.0000 11.750 1.3683 0.02750 0.02015 -0.0200 0.0285 1.0000 12.000 1.3740 0.02886 0.02158 -0.0182 0.0272 1.0000 12.250 1.3787 0.03037 0.02316 -0.0165 0.0262 1.0000 12.500 1.3826 0.03200 0.02488 -0.0149 0.0251 1.0000 12.750 1.3909 0.03333 0.02630 -0.0137 0.0243 1.0000 13.000 1.3973 0.03485 0.02791 -0.0126 0.0233 1.0000 13.250 1.4020 0.03659 0.02974 -0.0115 0.0224 1.0000 13.500 1.4054 0.03850 0.03173 -0.0105 0.0215 1.0000 13.750 1.4057 0.04080 0.03409 -0.0095 0.0204 1.0000 14.000 1.4071 0.04306 0.03644 -0.0087 0.0197 1.0000 14.250 1.4112 0.04511 0.03859 -0.0082 0.0186 1.0000 14.500 1.4129 0.04750 0.04107 -0.0077 0.0176 1.0000 14.750 1.4126 0.05018 0.04383 -0.0074 0.0168 1.0000 15.000 1.4099 0.05321 0.04693 -0.0072 0.0160 1.0000 15.250 1.4075 0.05634 0.05016 -0.0073 0.0153 1.0000 15.500 1.4047 0.05962 0.05355 -0.0074 0.0146 1.0000 15.750 1.3997 0.06329 0.05731 -0.0078 0.0140 1.0000 16.000 1.3933 0.06725 0.06138 -0.0084 0.0136 1.0000 16.250 1.3879 0.07116 0.06535 -0.0091 0.0126 1.0000 16.500 1.3799 0.07553 0.06981 -0.0101 0.0122 1.0000 16.750 1.3691 0.08035 0.07475 -0.0111 0.0123 1.0000 17.000 1.3626 0.08455 0.07907 -0.0121 0.0115 1.0000 17.250 1.3521 0.08938 0.08400 -0.0133 0.0114 1.0000 17.500 1.3422 0.09417 0.08891 -0.0146 0.0110 1.0000 17.750 1.3319 0.09904 0.09387 -0.0159 0.0107 1.0000 18.000 1.3212 0.10405 0.09898 -0.0174 0.0105 1.0000 18.250 1.3123 0.10883 0.10385 -0.0189 0.0102 1.0000 18.500 1.3019 0.11395 0.10905 -0.0205 0.0098 1.0000 18.750 1.2901 0.11934 0.11453 -0.0224 0.0095 1.0000