DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 50,000 Max Cl/Cd: 8.41 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd2-il-50000.txt Download as CSV file: xf-defcnd2-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL110 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2795 0.11404 0.10789 -0.0344 1.0000 0.2512
-9.250 -0.2771 0.11113 0.10507 -0.0327 1.0000 0.2581
-9.000 -0.2958 0.11070 0.10480 -0.0305 1.0000 0.2673
-8.750 -0.2891 0.10772 0.10189 -0.0279 1.0000 0.2758
-8.500 -0.3238 0.10842 0.10277 -0.0248 1.0000 0.2835
-8.250 -0.3144 0.10550 0.09989 -0.0218 1.0000 0.2962
-8.000 -0.3296 0.10416 0.09868 -0.0189 1.0000 0.3031
-7.750 -0.3528 0.10393 0.09858 -0.0155 1.0000 0.3142
-7.500 -0.3509 0.10165 0.09636 -0.0125 1.0000 0.3283
-7.250 -0.3534 0.09964 0.09443 -0.0095 1.0000 0.3418
-7.000 -0.3604 0.09795 0.09284 -0.0064 1.0000 0.3547
-6.750 -0.4171 0.09927 0.09437 -0.0017 1.0000 0.3620
-6.500 -0.3810 0.09501 0.09010 0.0002 1.0000 0.3839
-6.250 -0.3897 0.09349 0.08867 0.0037 1.0000 0.4003
-6.000 -0.3988 0.09213 0.08740 0.0073 1.0000 0.4181
-5.750 -0.4253 0.09176 0.08717 0.0123 1.0000 0.4383
-5.500 -0.4144 0.08923 0.08469 0.0150 1.0000 0.4605
-4.750 -0.3903 0.08352 0.07911 0.0227 0.9957 0.5542
-4.500 -0.5037 0.05866 0.05229 -0.0228 0.9845 0.1574
-4.250 -0.4648 0.05323 0.04607 -0.0270 0.9721 0.1379
-4.000 -0.4244 0.04926 0.04114 -0.0301 0.9584 0.1277
-3.750 -0.3833 0.04633 0.03763 -0.0329 0.9438 0.1253
-3.500 -0.3428 0.04422 0.03488 -0.0352 0.9291 0.1283
-3.250 -0.3034 0.04248 0.03256 -0.0369 0.9155 0.1311
-3.000 -0.2643 0.04076 0.03071 -0.0388 0.9037 0.1365
-2.750 -0.2177 0.03949 0.02918 -0.0416 0.8929 0.1488
-2.500 0.0881 0.03475 0.02756 -0.0772 0.8966 1.0000
-2.250 0.1119 0.03479 0.02725 -0.0783 0.8821 1.0000
-2.000 0.1353 0.03491 0.02706 -0.0790 0.8676 1.0000
-1.750 0.1575 0.03508 0.02695 -0.0794 0.8533 1.0000
-1.500 0.1795 0.03529 0.02690 -0.0795 0.8391 1.0000
-1.250 0.2013 0.03552 0.02690 -0.0794 0.8250 1.0000
-1.000 0.2245 0.03576 0.02692 -0.0793 0.8114 1.0000
-0.750 0.2792 0.03560 0.02645 -0.0839 0.8016 1.0000
-0.500 0.2844 0.03614 0.02686 -0.0810 0.7872 1.0000
-0.250 0.2855 0.03681 0.02741 -0.0775 0.7731 1.0000
0.000 0.2825 0.03764 0.02811 -0.0734 0.7595 1.0000
0.250 0.2815 0.03851 0.02884 -0.0697 0.7465 1.0000
0.500 0.2918 0.03926 0.02944 -0.0676 0.7350 1.0000
0.750 0.3315 0.03942 0.02941 -0.0693 0.7262 1.0000
1.000 0.3106 0.04104 0.03092 -0.0633 0.7141 1.0000
1.250 0.3074 0.04248 0.03223 -0.0599 0.7052 1.0000
1.500 0.3278 0.04331 0.03292 -0.0593 0.6975 1.0000
1.750 0.3150 0.04516 0.03467 -0.0551 0.6887 1.0000
2.000 0.3509 0.04557 0.03493 -0.0561 0.6815 1.0000
2.250 0.3355 0.04753 0.03681 -0.0519 0.6720 1.0000
2.500 0.3620 0.04815 0.03730 -0.0517 0.6632 1.0000
2.750 0.3711 0.04939 0.03844 -0.0500 0.6542 1.0000
3.000 0.3770 0.05087 0.03984 -0.0481 0.6459 1.0000
3.250 0.3994 0.05178 0.04067 -0.0478 0.6384 1.0000
3.500 0.3985 0.05381 0.04262 -0.0458 0.6319 1.0000
3.750 0.4057 0.05551 0.04428 -0.0446 0.6254 1.0000
4.000 0.4304 0.05668 0.04538 -0.0447 0.6199 1.0000
4.250 0.4148 0.05951 0.04818 -0.0422 0.6146 1.0000
4.500 0.4322 0.06104 0.04967 -0.0419 0.6089 1.0000
4.750 0.4400 0.06306 0.05166 -0.0411 0.6034 1.0000
5.000 0.4344 0.06567 0.05424 -0.0397 0.5991 1.0000
5.250 0.4393 0.06805 0.05660 -0.0391 0.5963 1.0000
5.500 0.4339 0.07114 0.05969 -0.0385 0.5982 1.0000
5.750 0.4367 0.07427 0.06281 -0.0386 0.6034 1.0000
6.000 0.3291 0.08259 0.07131 -0.0374 0.7206 1.0000
6.250 0.3474 0.08471 0.07340 -0.0379 0.7132 1.0000
6.500 0.3633 0.08719 0.07585 -0.0383 0.7089 1.0000
6.750 0.3685 0.08842 0.07707 -0.0373 0.7005 1.0000
7.000 0.3951 0.09153 0.08017 -0.0389 0.6962 1.0000
7.250 0.3917 0.09246 0.08110 -0.0371 0.6894 1.0000
7.500 0.4117 0.09489 0.08353 -0.0379 0.6831 1.0000
7.750 0.4217 0.09699 0.08563 -0.0377 0.6780 1.0000
8.000 0.4357 0.09885 0.08750 -0.0377 0.6689 1.0000
8.250 0.4493 0.10131 0.08997 -0.0380 0.6638 1.0000
8.500 0.4587 0.10289 0.09158 -0.0376 0.6550 1.0000
8.750 0.4835 0.10636 0.09507 -0.0390 0.6504 1.0000
9.000 0.4841 0.10717 0.09591 -0.0377 0.6400 1.0000
9.250 0.5035 0.11024 0.09902 -0.0386 0.6348 1.0000
9.500 0.5099 0.11159 0.10043 -0.0380 0.6246 1.0000
9.750 0.5209 0.11400 0.10288 -0.0381 0.6179 1.0000
10.000 0.5375 0.11633 0.10528 -0.0385 0.6085 1.0000
10.250 0.5415 0.11818 0.10717 -0.0381 0.6004 1.0000
10.500 0.5670 0.12156 0.11063 -0.0393 0.5923 1.0000
10.750 0.5647 0.12279 0.11191 -0.0384 0.5826 1.0000
11.000 0.5974 0.12742 0.11666 -0.0402 0.5761 1.0000
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Polar data table (+)
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