XFOIL Version 6.96 Calculated polar for: DF 101 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.3632 0.09140 0.08926 -0.0355 1.0000 0.0252 -10.500 -0.5933 0.03466 0.03193 -0.0664 1.0000 0.0117 -10.250 -0.6123 0.03162 0.02872 -0.0681 1.0000 0.0116 -10.000 -0.6304 0.02974 0.02673 -0.0659 1.0000 0.0115 -9.750 -0.5818 0.03185 0.02926 -0.0661 1.0000 0.0132 -9.500 -0.7050 0.03943 0.03604 -0.0555 1.0000 0.0115 -9.250 -0.5767 0.03336 0.03090 -0.0610 1.0000 0.0172 -9.000 -0.6015 0.03243 0.02995 -0.0550 1.0000 0.0174 -8.750 -0.7012 0.02864 0.02424 -0.0516 0.9941 0.0118 -8.500 -0.6781 0.02587 0.02116 -0.0525 0.9901 0.0119 -8.250 -0.6513 0.02334 0.01832 -0.0537 0.9867 0.0120 -8.000 -0.6209 0.02144 0.01623 -0.0552 0.9843 0.0123 -7.750 -0.5903 0.01996 0.01458 -0.0565 0.9818 0.0128 -7.500 -0.5618 0.01880 0.01329 -0.0570 0.9776 0.0134 -7.250 -0.5299 0.01755 0.01190 -0.0582 0.9747 0.0139 -7.000 -0.4958 0.01651 0.01072 -0.0598 0.9726 0.0147 -6.750 -0.4598 0.01573 0.00981 -0.0616 0.9711 0.0154 -6.500 -0.4331 0.01433 0.00836 -0.0620 0.9666 0.0169 -6.250 -0.4026 0.01379 0.00779 -0.0627 0.9621 0.0187 -6.000 -0.3698 0.01324 0.00714 -0.0637 0.9588 0.0203 -5.750 -0.3426 0.01223 0.00608 -0.0638 0.9540 0.0236 -5.500 -0.3162 0.01181 0.00560 -0.0634 0.9475 0.0266 -5.250 -0.2882 0.01117 0.00493 -0.0634 0.9426 0.0329 -5.000 -0.2642 0.01071 0.00446 -0.0625 0.9352 0.0405 -4.750 -0.2389 0.01012 0.00395 -0.0619 0.9289 0.0650 -4.500 -0.2169 0.00939 0.00360 -0.0610 0.9214 0.1445 -4.250 -0.1913 0.00908 0.00340 -0.0604 0.9146 0.1834 -4.000 -0.1654 0.00891 0.00324 -0.0599 0.9074 0.2062 -3.750 -0.1393 0.00872 0.00308 -0.0594 0.9000 0.2274 -3.500 -0.1131 0.00857 0.00294 -0.0589 0.8924 0.2459 -3.250 -0.0866 0.00843 0.00279 -0.0584 0.8847 0.2634 -3.000 -0.0605 0.00826 0.00267 -0.0579 0.8762 0.2847 -2.500 -0.0080 0.00794 0.00243 -0.0570 0.8587 0.3315 -2.250 0.0186 0.00780 0.00230 -0.0566 0.8499 0.3528 -2.000 0.0448 0.00763 0.00218 -0.0561 0.8400 0.3781 -1.750 0.0707 0.00746 0.00208 -0.0556 0.8291 0.4099 -1.500 0.0964 0.00726 0.00199 -0.0550 0.8183 0.4520 -1.250 0.1216 0.00704 0.00190 -0.0544 0.8068 0.5075 -1.000 0.1460 0.00681 0.00184 -0.0535 0.7943 0.5746 -0.750 0.1699 0.00658 0.00180 -0.0525 0.7803 0.6443 -0.500 0.1931 0.00635 0.00176 -0.0513 0.7656 0.7170 -0.250 0.2154 0.00610 0.00178 -0.0497 0.7511 0.8045 0.000 0.2415 0.00601 0.00186 -0.0487 0.7371 0.8855 0.250 0.2741 0.00608 0.00192 -0.0493 0.7231 0.9295 0.500 0.3089 0.00618 0.00195 -0.0504 0.7087 0.9526 0.750 0.3464 0.00629 0.00199 -0.0523 0.6938 0.9671 1.000 0.3891 0.00641 0.00201 -0.0553 0.6784 0.9757 1.250 0.4291 0.00653 0.00205 -0.0578 0.6630 0.9840 1.500 0.4719 0.00662 0.00206 -0.0610 0.6461 0.9900 1.750 0.5138 0.00671 0.00208 -0.0640 0.6286 0.9962 2.000 0.5515 0.00680 0.00209 -0.0662 0.6108 1.0000 2.250 0.5745 0.00689 0.00212 -0.0652 0.5948 1.0000 2.500 0.5972 0.00700 0.00216 -0.0642 0.5776 1.0000 2.750 0.6197 0.00713 0.00221 -0.0631 0.5594 1.0000 3.000 0.6424 0.00726 0.00229 -0.0620 0.5408 1.0000 3.250 0.6647 0.00741 0.00237 -0.0609 0.5199 1.0000 3.500 0.6867 0.00760 0.00246 -0.0597 0.4972 1.0000 3.750 0.7085 0.00780 0.00257 -0.0585 0.4730 1.0000 4.000 0.7299 0.00803 0.00271 -0.0572 0.4456 1.0000 4.250 0.7509 0.00830 0.00286 -0.0559 0.4163 1.0000 4.500 0.7717 0.00860 0.00304 -0.0546 0.3862 1.0000 4.750 0.7922 0.00894 0.00324 -0.0532 0.3561 1.0000 5.000 0.8128 0.00928 0.00347 -0.0519 0.3282 1.0000 5.250 0.8338 0.00962 0.00371 -0.0506 0.3049 1.0000 5.500 0.8547 0.00996 0.00396 -0.0493 0.2834 1.0000 5.750 0.8758 0.01030 0.00422 -0.0481 0.2655 1.0000 6.000 0.8974 0.01062 0.00450 -0.0470 0.2504 1.0000 6.250 0.9190 0.01095 0.00477 -0.0459 0.2363 1.0000 6.500 0.9408 0.01127 0.00506 -0.0448 0.2237 1.0000 6.750 0.9629 0.01157 0.00534 -0.0438 0.2113 1.0000 7.000 0.9849 0.01189 0.00564 -0.0428 0.1982 1.0000 7.250 1.0070 0.01221 0.00594 -0.0419 0.1860 1.0000 7.500 1.0289 0.01255 0.00624 -0.0409 0.1731 1.0000 7.750 1.0506 0.01289 0.00656 -0.0399 0.1614 1.0000 8.000 1.0718 0.01326 0.00690 -0.0389 0.1511 1.0000 8.250 1.0935 0.01361 0.00725 -0.0379 0.1407 1.0000 8.500 1.1149 0.01397 0.00762 -0.0369 0.1304 1.0000 8.750 1.1355 0.01437 0.00801 -0.0358 0.1193 1.0000 9.000 1.1552 0.01483 0.00843 -0.0345 0.1063 1.0000 9.250 1.1737 0.01536 0.00890 -0.0332 0.0913 1.0000 9.500 1.1899 0.01604 0.00949 -0.0315 0.0731 1.0000 9.750 1.2016 0.01701 0.01029 -0.0292 0.0475 1.0000 10.000 1.2089 0.01817 0.01132 -0.0261 0.0299 1.0000 10.250 1.2172 0.01911 0.01227 -0.0231 0.0247 1.0000 10.500 1.2283 0.01986 0.01308 -0.0206 0.0224 1.0000 10.750 1.2365 0.02082 0.01409 -0.0178 0.0205 1.0000 11.000 1.2425 0.02192 0.01528 -0.0150 0.0193 1.0000 11.250 1.2527 0.02280 0.01627 -0.0128 0.0185 1.0000 11.500 1.2614 0.02381 0.01736 -0.0106 0.0178 1.0000 11.750 1.2684 0.02495 0.01859 -0.0084 0.0171 1.0000 12.000 1.2744 0.02620 0.01993 -0.0063 0.0164 1.0000 12.250 1.2777 0.02771 0.02152 -0.0042 0.0158 1.0000 12.500 1.2789 0.02944 0.02334 -0.0022 0.0155 1.0000 12.750 1.2753 0.03169 0.02570 -0.0002 0.0150 1.0000 13.000 1.2667 0.03454 0.02867 0.0017 0.0146 1.0000 13.250 1.2724 0.03628 0.03053 0.0026 0.0143 1.0000 13.500 1.2757 0.03832 0.03267 0.0033 0.0140 1.0000 13.750 1.2756 0.04078 0.03526 0.0040 0.0138 1.0000 14.000 1.2768 0.04322 0.03780 0.0043 0.0135 1.0000 14.250 1.2752 0.04607 0.04079 0.0045 0.0133 1.0000 14.500 1.2734 0.04907 0.04390 0.0044 0.0129 1.0000 14.750 1.2704 0.05233 0.04728 0.0041 0.0127 1.0000 15.000 1.2673 0.05575 0.05080 0.0035 0.0124 1.0000 15.250 1.2642 0.05928 0.05445 0.0026 0.0123 1.0000 15.500 1.2589 0.06324 0.05851 0.0015 0.0120 1.0000 15.750 1.2535 0.06736 0.06272 0.0002 0.0117 1.0000 16.000 1.2478 0.07164 0.06710 -0.0013 0.0116 1.0000 16.250 1.2395 0.07639 0.07194 -0.0030 0.0113 1.0000 16.500 1.2294 0.08145 0.07711 -0.0048 0.0111 1.0000 16.750 1.2182 0.08682 0.08262 -0.0067 0.0109 1.0000