DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 100,000 Max Cl/Cd: 47.87 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd2-il-100000-n5.txt Download as CSV file: xf-defcnd2-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3208 0.09591 0.09130 -0.0540 1.0000 0.0315
-10.000 -0.3242 0.09369 0.08916 -0.0529 1.0000 0.0313
-9.750 -0.3351 0.09155 0.08713 -0.0513 1.0000 0.0310
-9.500 -0.3291 0.08623 0.08183 -0.0560 0.9908 0.0307
-9.250 -0.3236 0.07963 0.07524 -0.0630 0.9803 0.0303
-9.000 -0.3230 0.07102 0.06659 -0.0734 0.9690 0.0298
-8.750 -0.3302 0.06326 0.05867 -0.0819 0.9553 0.0293
-8.500 -0.3402 0.05729 0.05246 -0.0855 0.9408 0.0293
-8.250 -0.3467 0.05226 0.04709 -0.0868 0.9278 0.0297
-8.000 -0.3472 0.04812 0.04259 -0.0868 0.9165 0.0297
-7.750 -0.3433 0.04406 0.03805 -0.0863 0.9076 0.0302
-7.500 -0.3379 0.04085 0.03440 -0.0847 0.8973 0.0305
-7.250 -0.3278 0.03785 0.03095 -0.0833 0.8886 0.0306
-7.000 -0.3132 0.03517 0.02778 -0.0820 0.8806 0.0308
-6.750 -0.2979 0.03288 0.02504 -0.0804 0.8720 0.0311
-6.500 -0.2769 0.03080 0.02251 -0.0794 0.8647 0.0314
-6.250 -0.2570 0.02902 0.02048 -0.0783 0.8565 0.0320
-6.000 -0.2329 0.02767 0.01899 -0.0779 0.8496 0.0331
-5.750 -0.2108 0.02672 0.01790 -0.0770 0.8415 0.0351
-5.500 -0.1853 0.02557 0.01653 -0.0765 0.8344 0.0371
-5.250 -0.1612 0.02444 0.01520 -0.0756 0.8263 0.0383
-5.000 -0.1351 0.02336 0.01395 -0.0750 0.8188 0.0396
-4.750 -0.1135 0.02240 0.01299 -0.0739 0.8102 0.0413
-4.500 -0.0888 0.02166 0.01219 -0.0732 0.8025 0.0446
-4.250 -0.0676 0.02108 0.01150 -0.0718 0.7927 0.0483
-4.000 -0.0449 0.02032 0.01069 -0.0708 0.7845 0.0526
-3.750 -0.0240 0.01975 0.01003 -0.0692 0.7742 0.0584
-3.500 -0.0035 0.01913 0.00941 -0.0677 0.7638 0.0696
-3.250 0.0187 0.01844 0.00881 -0.0665 0.7546 0.0970
-3.000 0.0381 0.01784 0.00840 -0.0649 0.7435 0.1459
-2.750 0.0553 0.01705 0.00810 -0.0632 0.7331 0.2487
-2.500 0.0661 0.01573 0.00787 -0.0602 0.7239 0.4857
-2.250 0.0831 0.01528 0.00808 -0.0570 0.7131 0.6837
-2.000 0.1068 0.01522 0.00806 -0.0554 0.7021 0.7496
-1.750 0.1352 0.01523 0.00802 -0.0545 0.6918 0.7991
-1.500 0.1680 0.01529 0.00798 -0.0544 0.6812 0.8378
-1.250 0.2026 0.01542 0.00798 -0.0549 0.6690 0.8670
-1.000 0.2415 0.01559 0.00798 -0.0563 0.6571 0.8943
-0.750 0.2887 0.01581 0.00799 -0.0593 0.6449 0.9169
-0.500 0.3332 0.01591 0.00787 -0.0622 0.6327 0.9301
-0.250 0.3698 0.01595 0.00770 -0.0640 0.6205 0.9401
0.000 0.4084 0.01598 0.00753 -0.0662 0.6075 0.9474
0.250 0.4422 0.01602 0.00741 -0.0676 0.5947 0.9558
0.500 0.4785 0.01607 0.00728 -0.0696 0.5817 0.9629
0.750 0.5120 0.01613 0.00717 -0.0710 0.5692 0.9706
1.000 0.5476 0.01620 0.00707 -0.0729 0.5571 0.9776
1.500 0.6173 0.01639 0.00697 -0.0766 0.5348 0.9917
1.750 0.6531 0.01650 0.00696 -0.0788 0.5246 0.9984
2.000 0.6750 0.01663 0.00698 -0.0781 0.5163 1.0000
2.250 0.6909 0.01678 0.00709 -0.0762 0.5076 1.0000
2.500 0.7080 0.01696 0.00714 -0.0745 0.5002 1.0000
2.750 0.7239 0.01714 0.00731 -0.0726 0.4913 1.0000
3.000 0.7415 0.01733 0.00739 -0.0710 0.4841 1.0000
3.250 0.7581 0.01754 0.00759 -0.0692 0.4760 1.0000
3.500 0.7766 0.01776 0.00772 -0.0676 0.4699 1.0000
3.750 0.7944 0.01799 0.00797 -0.0660 0.4631 1.0000
4.000 0.8134 0.01823 0.00817 -0.0646 0.4574 1.0000
4.250 0.8330 0.01849 0.00838 -0.0633 0.4524 1.0000
4.500 0.8520 0.01877 0.00867 -0.0619 0.4468 1.0000
4.750 0.8720 0.01904 0.00892 -0.0606 0.4420 1.0000
5.000 0.8923 0.01933 0.00919 -0.0594 0.4375 1.0000
5.250 0.9116 0.01965 0.00954 -0.0581 0.4325 1.0000
5.500 0.9318 0.01995 0.00984 -0.0569 0.4281 1.0000
5.750 0.9533 0.02026 0.01012 -0.0559 0.4243 1.0000
6.000 0.9721 0.02063 0.01057 -0.0546 0.4195 1.0000
6.250 0.9920 0.02098 0.01095 -0.0534 0.4152 1.0000
6.500 1.0135 0.02131 0.01130 -0.0525 0.4115 1.0000
6.750 1.0337 0.02170 0.01173 -0.0514 0.4076 1.0000
7.000 1.0528 0.02213 0.01224 -0.0502 0.4033 1.0000
7.250 1.0734 0.02252 0.01267 -0.0492 0.3994 1.0000
7.500 1.0962 0.02290 0.01307 -0.0485 0.3961 1.0000
7.750 1.1147 0.02340 0.01367 -0.0473 0.3921 1.0000
8.000 1.1332 0.02389 0.01427 -0.0460 0.3879 1.0000
8.250 1.1544 0.02433 0.01475 -0.0452 0.3840 1.0000
8.750 1.1934 0.02538 0.01601 -0.0431 0.3765 1.0000
9.000 1.2114 0.02596 0.01672 -0.0418 0.3727 1.0000
9.250 1.2328 0.02650 0.01734 -0.0411 0.3693 1.0000
9.500 1.2586 0.02702 0.01791 -0.0411 0.3665 1.0000
9.750 1.2725 0.02778 0.01886 -0.0394 0.3630 1.0000
10.000 1.2856 0.02853 0.01980 -0.0375 0.3591 1.0000
10.250 1.3043 0.02901 0.02035 -0.0364 0.3540 1.0000
10.500 1.3178 0.02952 0.02096 -0.0345 0.3478 1.0000
10.750 1.3208 0.03013 0.02171 -0.0310 0.3411 1.0000
11.000 1.3414 0.03041 0.02198 -0.0301 0.3349 1.0000
11.250 1.3326 0.03138 0.02319 -0.0252 0.3291 1.0000
11.500 1.3418 0.03201 0.02394 -0.0230 0.3236 1.0000
11.750 1.3508 0.03269 0.02474 -0.0208 0.3185 1.0000
12.000 1.3430 0.03404 0.02633 -0.0171 0.3129 1.0000
12.250 1.3503 0.03481 0.02722 -0.0152 0.3075 1.0000
12.500 1.3432 0.03642 0.02906 -0.0122 0.3018 1.0000
12.750 1.3375 0.03803 0.03086 -0.0097 0.2955 1.0000
13.000 1.3332 0.03976 0.03276 -0.0077 0.2894 1.0000
13.250 1.3236 0.04203 0.03521 -0.0057 0.2826 1.0000
13.500 1.3167 0.04422 0.03754 -0.0042 0.2754 1.0000
13.750 1.3137 0.04617 0.03957 -0.0030 0.2671 1.0000
14.000 1.2992 0.04951 0.04304 -0.0020 0.2585 1.0000
14.250 1.2936 0.05204 0.04560 -0.0013 0.2482 1.0000
14.500 1.2858 0.05497 0.04851 -0.0008 0.2363 1.0000
14.750 1.2639 0.06013 0.05384 -0.0011 0.2277 1.0000
15.000 1.2444 0.06529 0.05911 -0.0018 0.2179 1.0000
15.250 1.2214 0.07123 0.06516 -0.0029 0.2070 1.0000
15.500 1.1790 0.08054 0.07467 -0.0055 0.1966 1.0000
15.750 1.1512 0.08797 0.08223 -0.0076 0.1852 1.0000
16.000 1.1620 0.08882 0.08278 -0.0075 0.1598 1.0000
16.500 1.1417 0.09774 0.09137 -0.0097 0.1307 1.0000
16.750 1.1294 0.10285 0.09643 -0.0112 0.1187 1.0000
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