DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 200,000 Max Cl/Cd: 64.5 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd2-il-200000.txt Download as CSV file: xf-defcnd2-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2882 0.10347 0.10028 -0.0478 1.0000 0.0522
-10.000 -0.2953 0.10218 0.09908 -0.0454 1.0000 0.0534
-9.750 -0.3030 0.10049 0.09746 -0.0443 0.9982 0.0550
-9.500 -0.2913 0.09501 0.09198 -0.0512 0.9918 0.0579
-9.250 -0.3041 0.08422 0.08120 -0.0726 0.9803 0.0603
-9.000 -0.3157 0.07735 0.07413 -0.0842 0.9691 0.0606
-8.750 -0.2779 0.07362 0.07061 -0.0795 0.9700 0.0627
-8.500 -0.2597 0.07046 0.06745 -0.0819 0.9636 0.0643
-8.250 -0.2496 0.06495 0.06185 -0.0895 0.9561 0.0665
-8.000 -0.2486 0.06006 0.05682 -0.0943 0.9446 0.0686
-7.750 -0.2245 0.04054 0.03710 -0.0976 0.9154 0.0753
-7.500 -0.2086 0.03767 0.03422 -0.0974 0.9088 0.0769
-7.250 -0.2058 0.03518 0.03166 -0.0958 0.8981 0.0790
-7.000 -0.2051 0.03243 0.02872 -0.0940 0.8887 0.0822
-6.750 -0.2371 0.04317 0.03854 -0.0944 0.8951 0.0883
-6.500 -0.2382 0.03247 0.02687 -0.0892 0.8858 0.0467
-6.250 -0.2263 0.02820 0.02197 -0.0865 0.8789 0.0424
-6.000 -0.2099 0.02654 0.02004 -0.0845 0.8698 0.0428
-5.750 -0.1874 0.02453 0.01763 -0.0832 0.8634 0.0428
-5.500 -0.1673 0.02274 0.01550 -0.0814 0.8547 0.0422
-5.250 -0.1407 0.02127 0.01380 -0.0807 0.8483 0.0423
-5.000 -0.1177 0.02020 0.01260 -0.0795 0.8394 0.0433
-4.750 -0.0905 0.01916 0.01141 -0.0790 0.8326 0.0446
-4.500 -0.0677 0.01849 0.01066 -0.0777 0.8229 0.0471
-4.250 -0.0414 0.01792 0.00995 -0.0770 0.8152 0.0492
-4.000 -0.0208 0.01672 0.00878 -0.0755 0.8055 0.0521
-3.750 0.0014 0.01611 0.00815 -0.0742 0.7964 0.0559
-3.500 0.0243 0.01553 0.00749 -0.0729 0.7878 0.0616
-3.250 0.0441 0.01494 0.00693 -0.0712 0.7777 0.0742
-3.000 0.0605 0.01379 0.00620 -0.0690 0.7691 0.1554
-2.750 0.0742 0.01279 0.00584 -0.0666 0.7586 0.3116
-2.500 0.0815 0.01171 0.00569 -0.0627 0.7479 0.5336
-2.250 0.0967 0.01129 0.00576 -0.0593 0.7382 0.7038
-2.000 0.1181 0.01116 0.00576 -0.0570 0.7269 0.7720
-1.750 0.1413 0.01115 0.00579 -0.0550 0.7148 0.8211
-1.500 0.1672 0.01120 0.00580 -0.0536 0.7028 0.8566
-1.250 0.1977 0.01129 0.00579 -0.0533 0.6908 0.8804
-1.000 0.2321 0.01146 0.00581 -0.0537 0.6786 0.9019
-0.750 0.2719 0.01166 0.00584 -0.0554 0.6657 0.9172
-0.500 0.3188 0.01191 0.00590 -0.0586 0.6513 0.9293
-0.250 0.3736 0.01222 0.00601 -0.0634 0.6354 0.9413
0.000 0.4194 0.01242 0.00602 -0.0668 0.6188 0.9518
0.250 0.4639 0.01253 0.00595 -0.0703 0.6030 0.9580
0.500 0.5010 0.01264 0.00588 -0.0724 0.5885 0.9653
0.750 0.5388 0.01273 0.00581 -0.0747 0.5744 0.9714
1.000 0.5771 0.01283 0.00574 -0.0772 0.5607 0.9774
1.250 0.6133 0.01294 0.00571 -0.0793 0.5476 0.9837
1.500 0.6524 0.01301 0.00567 -0.0821 0.5346 0.9892
1.750 0.6900 0.01311 0.00566 -0.0847 0.5226 0.9949
2.000 0.7295 0.01320 0.00561 -0.0877 0.5124 1.0000
2.250 0.7460 0.01329 0.00566 -0.0860 0.5039 1.0000
2.500 0.7628 0.01341 0.00572 -0.0844 0.4967 1.0000
2.750 0.7792 0.01351 0.00578 -0.0827 0.4896 1.0000
3.000 0.7973 0.01367 0.00584 -0.0812 0.4842 1.0000
3.250 0.8137 0.01378 0.00598 -0.0795 0.4781 1.0000
3.500 0.8315 0.01393 0.00610 -0.0779 0.4728 1.0000
3.750 0.8506 0.01414 0.00623 -0.0765 0.4684 1.0000
4.000 0.8684 0.01431 0.00643 -0.0748 0.4632 1.0000
4.250 0.8877 0.01449 0.00660 -0.0734 0.4585 1.0000
4.500 0.9088 0.01473 0.00677 -0.0724 0.4547 1.0000
4.750 0.9276 0.01494 0.00704 -0.0709 0.4500 1.0000
5.000 0.9475 0.01516 0.00726 -0.0696 0.4455 1.0000
5.250 0.9689 0.01539 0.00747 -0.0685 0.4416 1.0000
5.500 0.9903 0.01567 0.00774 -0.0675 0.4376 1.0000
5.750 1.0100 0.01592 0.00805 -0.0662 0.4331 1.0000
6.000 1.0313 0.01616 0.00830 -0.0652 0.4288 1.0000
6.250 1.0550 0.01647 0.00856 -0.0646 0.4250 1.0000
6.500 1.0738 0.01675 0.00894 -0.0631 0.4203 1.0000
6.750 1.0945 0.01703 0.00925 -0.0620 0.4156 1.0000
7.000 1.1178 0.01733 0.00952 -0.0614 0.4114 1.0000
7.250 1.1383 0.01769 0.00996 -0.0602 0.4069 1.0000
7.500 1.1582 0.01802 0.01037 -0.0590 0.4022 1.0000
7.750 1.1816 0.01837 0.01071 -0.0584 0.3980 1.0000
8.000 1.2049 0.01882 0.01119 -0.0579 0.3939 1.0000
8.250 1.2231 0.01923 0.01173 -0.0565 0.3892 1.0000
8.500 1.2457 0.01965 0.01219 -0.0558 0.3851 1.0000
8.750 1.2733 0.02016 0.01266 -0.0561 0.3814 1.0000
9.000 1.2888 0.02063 0.01330 -0.0542 0.3764 1.0000
9.250 1.3076 0.02093 0.01365 -0.0529 0.3703 1.0000
9.500 1.3294 0.02133 0.01403 -0.0521 0.3640 1.0000
9.750 1.3428 0.02169 0.01455 -0.0499 0.3583 1.0000
10.000 1.3658 0.02207 0.01493 -0.0493 0.3534 1.0000
10.250 1.3830 0.02253 0.01549 -0.0478 0.3479 1.0000
10.500 1.3950 0.02287 0.01597 -0.0454 0.3421 1.0000
10.750 1.4167 0.02311 0.01613 -0.0446 0.3350 1.0000
11.000 1.4190 0.02343 0.01669 -0.0406 0.3293 1.0000
11.250 1.4290 0.02356 0.01683 -0.0377 0.3223 1.0000
11.500 1.4267 0.02385 0.01728 -0.0329 0.3160 1.0000
11.750 1.4248 0.02408 0.01760 -0.0284 0.3085 1.0000
12.000 1.4258 0.02453 0.01821 -0.0248 0.3018 1.0000
12.250 1.4229 0.02499 0.01874 -0.0209 0.2924 1.0000
12.500 1.4264 0.02575 0.01970 -0.0184 0.2844 1.0000
12.750 1.4236 0.02668 0.02067 -0.0154 0.2718 1.0000
13.000 1.4215 0.02794 0.02193 -0.0128 0.2596 1.0000
13.250 1.4193 0.02947 0.02346 -0.0106 0.2479 1.0000
13.500 1.4147 0.03135 0.02533 -0.0084 0.2348 1.0000
13.750 1.4101 0.03341 0.02740 -0.0066 0.2221 1.0000
14.000 1.4076 0.03554 0.02969 -0.0052 0.2025 1.0000
14.250 1.3931 0.03873 0.03280 -0.0037 0.1705 1.0000
14.500 1.3696 0.04308 0.03700 -0.0025 0.1513 1.0000
14.750 1.3531 0.04716 0.04108 -0.0018 0.1388 1.0000
15.000 1.3354 0.05166 0.04558 -0.0016 0.1268 1.0000
15.250 1.3164 0.05658 0.05051 -0.0018 0.1159 1.0000
15.500 1.2948 0.06205 0.05597 -0.0024 0.1042 1.0000
15.750 1.2824 0.06653 0.06053 -0.0030 0.0961 1.0000
16.000 1.2652 0.07177 0.06580 -0.0039 0.0873 1.0000
16.250 1.2463 0.07739 0.07144 -0.0051 0.0776 1.0000
16.500 1.2273 0.08318 0.07722 -0.0064 0.0670 1.0000
16.750 1.2077 0.08924 0.08324 -0.0080 0.0545 1.0000
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Polar data table (+)
Polar graphs
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