DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 100,000 Max Cl/Cd: 41.67 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd2-il-100000.txt Download as CSV file: xf-defcnd2-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3759 0.10251 0.09860 -0.0343 1.0000 0.1145
-8.500 -0.4138 0.10137 0.09758 -0.0339 1.0000 0.1151
-8.250 -0.4542 0.09812 0.09436 -0.0403 0.9939 0.1156
-8.000 -0.3829 0.09369 0.08993 -0.0338 0.9950 0.1208
-7.750 -0.3783 0.08901 0.08526 -0.0409 0.9866 0.1274
-7.500 -0.4167 0.08227 0.07835 -0.0544 0.9706 0.1314
-7.250 -0.3629 0.07947 0.07569 -0.0519 0.9700 0.1393
-7.000 -0.3843 0.07355 0.06951 -0.0606 0.9553 0.1469
-6.750 -0.3525 0.07093 0.06698 -0.0597 0.9490 0.1571
-6.500 -0.3352 0.06662 0.06261 -0.0631 0.9413 0.1672
-6.250 -0.3331 0.06307 0.05891 -0.0646 0.9296 0.1795
-5.750 -0.3154 0.04781 0.04176 -0.0685 0.9101 0.1005
-5.500 -0.3012 0.04206 0.03569 -0.0669 0.9003 0.0817
-5.250 -0.2681 0.03746 0.03009 -0.0674 0.8949 0.0717
-5.000 -0.2464 0.03498 0.02725 -0.0663 0.8844 0.0708
-4.750 -0.2013 0.03256 0.02425 -0.0688 0.8799 0.0726
-4.500 -0.1746 0.03091 0.02224 -0.0681 0.8694 0.0736
-4.250 -0.1276 0.02812 0.01929 -0.0710 0.8649 0.0758
-4.000 -0.0972 0.02676 0.01788 -0.0710 0.8546 0.0795
-3.750 -0.0523 0.02517 0.01615 -0.0732 0.8489 0.0882
-3.500 -0.0276 0.02410 0.01518 -0.0722 0.8378 0.0969
-3.250 0.0085 0.02253 0.01372 -0.0728 0.8323 0.1189
-3.000 0.0204 0.02126 0.01294 -0.0696 0.8200 0.1861
-2.750 0.0198 0.01916 0.01256 -0.0643 0.8087 0.4984
-2.500 0.0465 0.01871 0.01303 -0.0601 0.8027 0.7999
-2.250 0.1027 0.01948 0.01367 -0.0613 0.7939 0.8825
-2.000 0.2120 0.01997 0.01367 -0.0732 0.7891 0.9232
-1.750 0.3066 0.01999 0.01331 -0.0844 0.7798 0.9491
-1.500 0.3915 0.01945 0.01243 -0.0946 0.7709 0.9731
-1.250 0.4561 0.01885 0.01160 -0.1021 0.7574 0.9917
-1.000 0.4973 0.01839 0.01095 -0.1053 0.7436 1.0000
-0.750 0.5135 0.01829 0.01074 -0.1036 0.7302 1.0000
-0.500 0.5302 0.01817 0.01051 -0.1020 0.7171 1.0000
-0.250 0.5474 0.01803 0.01025 -0.1003 0.7040 1.0000
0.000 0.5652 0.01789 0.00996 -0.0988 0.6915 1.0000
0.250 0.5838 0.01772 0.00965 -0.0973 0.6792 1.0000
0.500 0.6019 0.01759 0.00939 -0.0957 0.6664 1.0000
0.750 0.6186 0.01757 0.00926 -0.0940 0.6530 1.0000
1.000 0.6355 0.01758 0.00916 -0.0923 0.6400 1.0000
1.250 0.6529 0.01763 0.00911 -0.0907 0.6279 1.0000
1.500 0.6714 0.01769 0.00904 -0.0892 0.6170 1.0000
1.750 0.6911 0.01775 0.00895 -0.0879 0.6068 1.0000
2.000 0.7064 0.01797 0.00911 -0.0860 0.5953 1.0000
2.250 0.7237 0.01818 0.00922 -0.0843 0.5852 1.0000
2.500 0.7446 0.01834 0.00922 -0.0832 0.5768 1.0000
2.750 0.7592 0.01869 0.00958 -0.0812 0.5675 1.0000
3.000 0.7818 0.01893 0.00966 -0.0803 0.5608 1.0000
3.250 0.7959 0.01937 0.01014 -0.0782 0.5526 1.0000
3.500 0.8193 0.01966 0.01031 -0.0776 0.5467 1.0000
3.750 0.8336 0.02018 0.01089 -0.0755 0.5397 1.0000
4.000 0.8546 0.02056 0.01121 -0.0745 0.5338 1.0000
4.250 0.8745 0.02104 0.01166 -0.0733 0.5282 1.0000
4.500 0.8906 0.02159 0.01228 -0.0715 0.5220 1.0000
4.750 0.9146 0.02198 0.01260 -0.0710 0.5170 1.0000
5.000 0.9304 0.02261 0.01330 -0.0692 0.5113 1.0000
5.250 0.9480 0.02318 0.01392 -0.0677 0.5055 1.0000
5.500 0.9738 0.02359 0.01428 -0.0675 0.5009 1.0000
5.750 0.9862 0.02436 0.01519 -0.0652 0.4952 1.0000
6.000 1.0043 0.02497 0.01585 -0.0638 0.4896 1.0000
6.250 1.0317 0.02538 0.01620 -0.0638 0.4853 1.0000
6.500 1.0402 0.02633 0.01735 -0.0611 0.4794 1.0000
6.750 1.0582 0.02700 0.01808 -0.0597 0.4741 1.0000
7.000 1.0878 0.02737 0.01840 -0.0601 0.4699 1.0000
7.250 1.0911 0.02855 0.01980 -0.0567 0.4636 1.0000
7.500 1.1101 0.02922 0.02056 -0.0555 0.4585 1.0000
7.750 1.1403 0.02966 0.02098 -0.0560 0.4548 1.0000
8.000 1.1368 0.03130 0.02287 -0.0519 0.4492 1.0000
8.250 1.1505 0.03235 0.02404 -0.0503 0.4446 1.0000
8.500 1.1757 0.03302 0.02476 -0.0501 0.4413 1.0000
8.750 1.1834 0.03452 0.02641 -0.0478 0.4375 1.0000
9.000 1.1627 0.03723 0.02937 -0.0422 0.4324 1.0000
9.250 1.1687 0.03887 0.03113 -0.0400 0.4289 1.0000
9.500 1.2020 0.03927 0.03159 -0.0409 0.4262 1.0000
10.250 1.0530 0.05448 0.04706 -0.0217 0.4098 1.0000
11.000 1.2101 0.04777 0.04070 -0.0240 0.3947 1.0000
11.250 0.7494 0.10534 0.09782 -0.0275 0.3943 1.0000
11.500 0.7424 0.11011 0.10266 -0.0285 0.3943 1.0000
11.750 0.7487 0.11420 0.10685 -0.0295 0.3959 1.0000
12.000 0.7682 0.11076 0.10344 -0.0263 0.3612 1.0000
12.250 0.8450 0.10453 0.09739 -0.0230 0.3511 1.0000
13.000 1.4353 0.04346 0.03727 -0.0200 0.3353 1.0000
13.250 1.3647 0.04942 0.04345 -0.0126 0.3345 1.0000
13.500 1.3892 0.04754 0.04163 -0.0110 0.3219 1.0000
13.750 1.3044 0.05697 0.05121 -0.0068 0.3210 1.0000
14.000 1.3626 0.05082 0.04513 -0.0055 0.3045 1.0000
14.250 1.3652 0.05055 0.04493 -0.0035 0.2918 1.0000
14.500 1.2802 0.06249 0.05704 -0.0026 0.2919 1.0000
14.750 1.2815 0.06310 0.05774 -0.0016 0.2798 1.0000
15.000 1.2986 0.06157 0.05625 -0.0004 0.2636 1.0000
15.250 1.2940 0.06356 0.05828 -0.0001 0.2477 1.0000
15.500 1.2786 0.06743 0.06214 -0.0004 0.2311 1.0000
15.750 1.2611 0.07223 0.06697 -0.0011 0.2169 1.0000
16.000 1.2337 0.07883 0.07363 -0.0026 0.2034 1.0000
16.250 1.2061 0.08585 0.08071 -0.0046 0.1894 1.0000
16.500 1.2042 0.08874 0.08338 -0.0054 0.1690 1.0000
16.750 1.1946 0.09290 0.08733 -0.0063 0.1522 1.0000
17.000 1.1847 0.09722 0.09151 -0.0073 0.1378 1.0000
17.250 1.1752 0.10164 0.09583 -0.0084 0.1250 1.0000
17.500 1.1642 0.10644 0.10055 -0.0098 0.1126 1.0000
17.750 1.1518 0.11159 0.10562 -0.0115 0.0998 1.0000
18.000 1.1408 0.11657 0.11050 -0.0131 0.0874 1.0000
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