N-11 (n11-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 200,000 Max Cl/Cd: 75.63 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n11-il-200000.txt Download as CSV file: xf-n11-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: N-11
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3433 0.09315 0.08984 -0.0322 1.0000 0.0605
-9.250 -0.3594 0.09186 0.08864 -0.0294 1.0000 0.0616
-9.000 -0.3827 0.09119 0.08807 -0.0254 1.0000 0.0621
-8.750 -0.3818 0.08303 0.07982 -0.0512 0.9893 0.0656
-8.500 -0.3702 0.07894 0.07582 -0.0468 0.9875 0.0669
-8.250 -0.3472 0.07686 0.07373 -0.0456 0.9851 0.0688
-8.000 -0.3232 0.07308 0.06991 -0.0504 0.9799 0.0717
-7.750 -0.2883 0.06166 0.05813 -0.0732 0.9709 0.0791
-7.500 -0.2700 0.05935 0.05589 -0.0724 0.9649 0.0804
-7.250 -0.2431 0.05695 0.05347 -0.0741 0.9607 0.0830
-7.000 -0.1579 0.03504 0.03152 -0.0861 0.9429 0.0946
-6.750 -0.1394 0.03262 0.02906 -0.0864 0.9352 0.0970
-6.500 -0.1121 0.02688 0.02280 -0.0930 0.9302 0.1077
-6.250 -0.0796 0.02389 0.01986 -0.0952 0.9282 0.1102
-6.000 -0.0902 0.02707 0.02100 -0.0966 0.9325 0.0643
-5.750 -0.0525 0.02399 0.01750 -0.0990 0.9298 0.0625
-5.500 -0.0122 0.02173 0.01483 -0.1015 0.9278 0.0618
-5.250 0.0149 0.02052 0.01337 -0.1012 0.9197 0.0627
-5.000 0.0518 0.01935 0.01196 -0.1027 0.9158 0.0641
-4.750 0.0907 0.01814 0.01056 -0.1044 0.9129 0.0648
-4.500 0.1185 0.01736 0.00967 -0.1040 0.9038 0.0656
-4.250 0.1544 0.01599 0.00830 -0.1052 0.8989 0.0678
-4.000 0.1828 0.01531 0.00764 -0.1049 0.8898 0.0706
-3.750 0.2169 0.01466 0.00695 -0.1056 0.8835 0.0757
-3.500 0.2439 0.01405 0.00636 -0.1051 0.8732 0.0811
-3.250 0.2748 0.01349 0.00577 -0.1051 0.8650 0.0917
-3.000 0.3025 0.01268 0.00526 -0.1048 0.8547 0.1476
-2.750 0.3294 0.01227 0.00505 -0.1044 0.8434 0.2187
-2.500 0.3570 0.01185 0.00484 -0.1042 0.8332 0.2873
-2.250 0.3820 0.01117 0.00473 -0.1036 0.8228 0.4537
-2.000 0.3978 0.01011 0.00484 -0.1003 0.8117 0.8047
-1.750 0.4619 0.00987 0.00458 -0.1070 0.8032 1.0000
-1.500 0.4876 0.00993 0.00449 -0.1064 0.7916 1.0000
-1.250 0.5126 0.01001 0.00444 -0.1056 0.7793 1.0000
-1.000 0.5381 0.01008 0.00438 -0.1049 0.7674 1.0000
-0.750 0.5643 0.01014 0.00431 -0.1043 0.7560 1.0000
-0.500 0.5899 0.01021 0.00426 -0.1037 0.7440 1.0000
-0.250 0.6151 0.01028 0.00425 -0.1030 0.7311 1.0000
0.000 0.6406 0.01035 0.00423 -0.1024 0.7183 1.0000
0.250 0.6663 0.01042 0.00421 -0.1018 0.7052 1.0000
0.500 0.6920 0.01050 0.00420 -0.1012 0.6916 1.0000
0.750 0.7177 0.01060 0.00419 -0.1006 0.6778 1.0000
1.000 0.7433 0.01072 0.00421 -0.1000 0.6633 1.0000
1.250 0.7685 0.01085 0.00425 -0.0993 0.6475 1.0000
1.500 0.7933 0.01101 0.00431 -0.0986 0.6301 1.0000
1.750 0.8178 0.01118 0.00439 -0.0978 0.6116 1.0000
2.000 0.8421 0.01139 0.00449 -0.0971 0.5927 1.0000
2.250 0.8662 0.01162 0.00460 -0.0963 0.5735 1.0000
2.500 0.8900 0.01185 0.00475 -0.0955 0.5531 1.0000
2.750 0.9136 0.01210 0.00494 -0.0947 0.5329 1.0000
3.000 0.9370 0.01239 0.00512 -0.0938 0.5130 1.0000
3.250 0.9603 0.01270 0.00533 -0.0930 0.4932 1.0000
3.500 0.9835 0.01302 0.00558 -0.0922 0.4739 1.0000
3.750 1.0068 0.01336 0.00585 -0.0915 0.4564 1.0000
4.000 1.0299 0.01371 0.00613 -0.0907 0.4401 1.0000
4.250 1.0529 0.01407 0.00642 -0.0900 0.4247 1.0000
4.500 1.0758 0.01444 0.00674 -0.0892 0.4100 1.0000
4.750 1.0986 0.01482 0.00707 -0.0885 0.3966 1.0000
5.000 1.1216 0.01524 0.00743 -0.0878 0.3852 1.0000
5.250 1.1448 0.01565 0.00782 -0.0872 0.3749 1.0000
5.500 1.1682 0.01606 0.00826 -0.0866 0.3650 1.0000
5.750 1.1914 0.01655 0.00869 -0.0861 0.3559 1.0000
6.000 1.2139 0.01696 0.00914 -0.0854 0.3458 1.0000
6.250 1.2359 0.01740 0.00962 -0.0846 0.3352 1.0000
6.500 1.2565 0.01786 0.01006 -0.0836 0.3232 1.0000
6.750 1.2760 0.01831 0.01048 -0.0825 0.3103 1.0000
7.000 1.2955 0.01868 0.01092 -0.0813 0.2985 1.0000
7.250 1.3154 0.01908 0.01143 -0.0802 0.2879 1.0000
7.500 1.3340 0.01952 0.01189 -0.0789 0.2770 1.0000
7.750 1.3511 0.01996 0.01234 -0.0774 0.2651 1.0000
8.000 1.3687 0.02034 0.01282 -0.0760 0.2531 1.0000
8.250 1.3854 0.02077 0.01336 -0.0745 0.2414 1.0000
8.500 1.3994 0.02124 0.01388 -0.0725 0.2287 1.0000
8.750 1.4121 0.02181 0.01447 -0.0704 0.2134 1.0000
9.000 1.4238 0.02251 0.01517 -0.0683 0.1977 1.0000
9.250 1.4328 0.02341 0.01601 -0.0660 0.1805 1.0000
9.500 1.4416 0.02442 0.01702 -0.0638 0.1633 1.0000
9.750 1.4477 0.02567 0.01820 -0.0615 0.1393 1.0000
10.000 1.4490 0.02735 0.01969 -0.0588 0.1016 1.0000
10.250 1.4416 0.02980 0.02189 -0.0556 0.0766 1.0000
10.500 1.4380 0.03213 0.02415 -0.0530 0.0545 1.0000
10.750 1.4347 0.03456 0.02649 -0.0508 0.0409 1.0000
11.000 1.4328 0.03697 0.02893 -0.0490 0.0360 1.0000
11.250 1.4314 0.03945 0.03150 -0.0475 0.0335 1.0000
11.500 1.4269 0.04234 0.03450 -0.0462 0.0318 1.0000
11.750 1.4220 0.04540 0.03769 -0.0451 0.0307 1.0000
12.000 1.4181 0.04849 0.04094 -0.0444 0.0298 1.0000
12.250 1.4128 0.05187 0.04447 -0.0439 0.0291 1.0000
12.500 1.4064 0.05554 0.04827 -0.0437 0.0284 1.0000
12.750 1.3990 0.05946 0.05233 -0.0438 0.0278 1.0000
13.000 1.3909 0.06363 0.05662 -0.0441 0.0273 1.0000
13.250 1.3820 0.06802 0.06112 -0.0446 0.0268 1.0000
13.500 1.3723 0.07258 0.06578 -0.0452 0.0263 1.0000
13.750 1.3625 0.07718 0.07045 -0.0458 0.0258 1.0000
14.000 1.3541 0.08148 0.07480 -0.0462 0.0254 1.0000
14.250 1.3514 0.08523 0.07868 -0.0468 0.0249 1.0000
14.500 1.3490 0.08890 0.08247 -0.0473 0.0245 1.0000
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Polar data table (+)
Polar graphs
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