XFOIL Version 6.96 Calculated polar for: DEFIANT CANARD BL20 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.6991 0.08681 0.08216 -0.0914 0.6765 0.0149 -18.250 -0.7350 0.07836 0.07357 -0.0960 0.6750 0.0147 -18.000 -0.7668 0.07077 0.06583 -0.1002 0.6712 0.0148 -17.750 -0.7889 0.06474 0.05967 -0.1035 0.6675 0.0151 -17.500 -0.8121 0.05885 0.05364 -0.1066 0.6641 0.0151 -17.250 -0.8311 0.05377 0.04846 -0.1091 0.6609 0.0151 -17.000 -0.8470 0.04931 0.04389 -0.1111 0.6568 0.0151 -16.750 -0.8598 0.04532 0.03980 -0.1128 0.6527 0.0152 -16.500 -0.8686 0.04188 0.03625 -0.1141 0.6482 0.0153 -16.000 -0.8841 0.03539 0.02958 -0.1162 0.6410 0.0157 -15.750 -0.8887 0.03255 0.02665 -0.1169 0.6373 0.0159 -15.500 -0.8908 0.03009 0.02411 -0.1173 0.6334 0.0162 -15.250 -0.8909 0.02803 0.02197 -0.1173 0.6288 0.0163 -15.000 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0.00383 -0.0678 0.5051 0.1098 -5.500 -0.2052 0.01068 0.00372 -0.0676 0.5028 0.1119 -5.250 -0.1777 0.01060 0.00362 -0.0673 0.5000 0.1135 -5.000 -0.1509 0.01049 0.00350 -0.0670 0.4967 0.1161 -4.750 -0.1240 0.01040 0.00340 -0.0667 0.4935 0.1184 -4.500 -0.0970 0.01033 0.00330 -0.0663 0.4904 0.1207 -4.250 -0.0697 0.01027 0.00322 -0.0661 0.4878 0.1228 -4.000 -0.0418 0.01020 0.00314 -0.0659 0.4857 0.1245 -3.750 -0.0145 0.01011 0.00305 -0.0657 0.4829 0.1277 -3.500 0.0127 0.01002 0.00297 -0.0654 0.4799 0.1306 -3.250 0.0401 0.00996 0.00289 -0.0651 0.4768 0.1334 -3.000 0.0674 0.00992 0.00283 -0.0649 0.4738 0.1361 -2.750 0.0945 0.00988 0.00277 -0.0646 0.4706 0.1397 -2.500 0.1220 0.00979 0.00271 -0.0644 0.4684 0.1441 -2.250 0.1497 0.00973 0.00266 -0.0643 0.4658 0.1489 -2.000 0.1769 0.00965 0.00260 -0.0640 0.4629 0.1565 -1.750 0.2040 0.00958 0.00256 -0.0638 0.4600 0.1664 -1.500 0.2305 0.00950 0.00251 -0.0634 0.4568 0.1809 -1.250 0.2565 0.00940 0.00247 -0.0630 0.4534 0.2010 -1.000 0.2830 0.00927 0.00243 -0.0627 0.4511 0.2273 -0.750 0.3095 0.00914 0.00240 -0.0624 0.4488 0.2549 -0.500 0.3360 0.00904 0.00238 -0.0620 0.4458 0.2819 -0.250 0.3625 0.00897 0.00237 -0.0617 0.4426 0.3060 0.000 0.3889 0.00893 0.00238 -0.0614 0.4393 0.3276 0.250 0.4154 0.00893 0.00241 -0.0610 0.4361 0.3443 0.500 0.4427 0.00890 0.00243 -0.0608 0.4338 0.3593 0.750 0.4700 0.00889 0.00245 -0.0607 0.4312 0.3714 1.000 0.4973 0.00890 0.00248 -0.0605 0.4280 0.3831 1.250 0.5241 0.00891 0.00252 -0.0602 0.4248 0.3942 1.500 0.5508 0.00896 0.00256 -0.0599 0.4216 0.4059 1.750 0.5768 0.00898 0.00262 -0.0595 0.4181 0.4221 2.000 0.6038 0.00898 0.00267 -0.0593 0.4156 0.4361 2.250 0.6309 0.00901 0.00272 -0.0591 0.4127 0.4464 2.500 0.6573 0.00904 0.00278 -0.0588 0.4095 0.4567 2.750 0.6834 0.00910 0.00285 -0.0584 0.4061 0.4679 3.000 0.7086 0.00917 0.00293 -0.0579 0.4024 0.4796 3.250 0.7351 0.00921 0.00300 -0.0576 0.3996 0.4901 3.500 0.7611 0.00924 0.00307 -0.0573 0.3969 0.5023 3.750 0.7868 0.00928 0.00314 -0.0569 0.3936 0.5154 4.000 0.8116 0.00934 0.00323 -0.0563 0.3898 0.5287 4.250 0.8355 0.00943 0.00333 -0.0556 0.3859 0.5418 4.500 0.8603 0.00947 0.00343 -0.0550 0.3832 0.5580 4.750 0.8846 0.00949 0.00352 -0.0544 0.3803 0.5803 5.000 0.9072 0.00949 0.00363 -0.0534 0.3768 0.6186 5.250 0.9268 0.00945 0.00376 -0.0519 0.3729 0.6779 5.500 0.9439 0.00943 0.00391 -0.0498 0.3691 0.7449 5.750 0.9611 0.00934 0.00405 -0.0477 0.3666 0.8166 6.000 0.9849 0.00928 0.00423 -0.0468 0.3635 0.8989 6.250 1.0525 0.00952 0.00454 -0.0554 0.3582 0.9480 6.500 1.1046 0.00981 0.00480 -0.0609 0.3530 0.9623 6.750 1.1457 0.01001 0.00500 -0.0639 0.3496 0.9712 7.000 1.1777 0.01020 0.00519 -0.0650 0.3455 0.9798 7.250 1.2089 0.01044 0.00541 -0.0660 0.3410 0.9864 7.500 1.2354 0.01072 0.00566 -0.0661 0.3369 0.9944 8.000 1.3012 0.01116 0.00611 -0.0689 0.3298 1.0000 8.250 1.3119 0.01137 0.00631 -0.0658 0.3261 1.0000 8.500 1.3175 0.01160 0.00653 -0.0618 0.3223 1.0000 8.750 1.3275 0.01185 0.00678 -0.0587 0.3190 1.0000 9.000 1.3417 0.01207 0.00702 -0.0564 0.3162 1.0000 9.250 1.3553 0.01236 0.00732 -0.0542 0.3125 1.0000 9.500 1.3677 0.01273 0.00768 -0.0519 0.3086 1.0000 9.750 1.3782 0.01321 0.00816 -0.0494 0.3043 1.0000 10.000 1.3941 0.01358 0.00855 -0.0479 0.3017 1.0000 10.250 1.4089 0.01402 0.00901 -0.0464 0.2985 1.0000 10.500 1.4213 0.01461 0.00961 -0.0447 0.2944 1.0000 10.750 1.4315 0.01537 0.01038 -0.0429 0.2906 1.0000 11.000 1.4441 0.01611 0.01114 -0.0416 0.2874 1.0000 11.250 1.4580 0.01686 0.01192 -0.0406 0.2843 1.0000 11.500 1.4700 0.01780 0.01288 -0.0396 0.2807 1.0000 11.750 1.4787 0.01905 0.01414 -0.0386 0.2767 1.0000 12.000 1.4870 0.02041 0.01553 -0.0377 0.2729 1.0000 12.250 1.4986 0.02157 0.01672 -0.0371 0.2690 1.0000 12.500 1.5065 0.02302 0.01819 -0.0363 0.2646 1.0000 12.750 1.5087 0.02488 0.02007 -0.0352 0.2600 1.0000 13.000 1.5156 0.02639 0.02160 -0.0344 0.2558 1.0000 13.250 1.5223 0.02793 0.02317 -0.0336 0.2522 1.0000 13.500 1.5219 0.03001 0.02526 -0.0326 0.2471 1.0000 13.750 1.5222 0.03206 0.02733 -0.0316 0.2435 1.0000 14.000 1.5282 0.03366 0.02897 -0.0309 0.2396 1.0000 14.250 1.5302 0.03564 0.03098 -0.0301 0.2355 1.0000 14.500 1.5294 0.03789 0.03325 -0.0293 0.2312 1.0000 14.750 1.5301 0.04010 0.03548 -0.0286 0.2273 1.0000 15.000 1.5351 0.04195 0.03736 -0.0281 0.2232 1.0000 15.250 1.5342 0.04440 0.03984 -0.0276 0.2190 1.0000 15.500 1.5309 0.04707 0.04252 -0.0270 0.2141 1.0000 15.750 1.5348 0.04911 0.04459 -0.0266 0.2104 1.0000 16.000 1.5364 0.05139 0.04690 -0.0263 0.2062 1.0000 16.250 1.5298 0.05451 0.05003 -0.0258 0.2015 1.0000 16.500 1.5348 0.05650 0.05205 -0.0256 0.1979 1.0000 16.750 1.5303 0.05949 0.05506 -0.0253 0.1921 1.0000 17.000 1.5257 0.06251 0.05809 -0.0251 0.1872 1.0000 17.250 1.5257 0.06511 0.06072 -0.0250 0.1828 1.0000 17.500 1.5211 0.06818 0.06380 -0.0249 0.1771 1.0000 17.750 1.5168 0.07129 0.06693 -0.0249 0.1732 1.0000 18.000 1.5184 0.07378 0.06945 -0.0249 0.1687 1.0000 18.250 1.5115 0.07725 0.07294 -0.0250 0.1642 1.0000 18.500 1.5103 0.08007 0.07578 -0.0251 0.1602 1.0000 18.750 1.5077 0.08311 0.07886 -0.0253 0.1560 1.0000 19.000 1.4989 0.08689 0.08264 -0.0256 0.1504 1.0000 19.250 1.4966 0.08995 0.08574 -0.0259 0.1458 1.0000