N-11 (n11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-11 (n11-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.42 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n11-il-1000000.txt Download as CSV file: xf-n11-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3611 0.09742 0.09579 -0.0390 1.0000 0.0204
-11.000 -0.3689 0.09380 0.09219 -0.0388 1.0000 0.0205
-10.750 -0.5031 0.03126 0.02879 -0.1018 0.9842 0.0200
-10.500 -0.4900 0.02533 0.02218 -0.1053 0.9791 0.0208
-10.250 -0.4628 0.02392 0.02069 -0.1065 0.9758 0.0213
-10.000 -0.4324 0.02315 0.01987 -0.1077 0.9732 0.0217
-9.750 -0.4020 0.02256 0.01924 -0.1087 0.9707 0.0221
-9.500 -0.3801 0.02163 0.01821 -0.1081 0.9636 0.0225
-9.250 -0.3551 0.02040 0.01681 -0.1081 0.9582 0.0231
-9.000 -0.3319 0.01939 0.01562 -0.1076 0.9507 0.0238
-8.750 -0.3070 0.01849 0.01454 -0.1072 0.9433 0.0244
-8.500 -0.2823 0.01788 0.01376 -0.1066 0.9336 0.0248
-8.250 -0.2578 0.01696 0.01260 -0.1062 0.9236 0.0252
-8.000 -0.2363 0.01469 0.01007 -0.1056 0.9116 0.0259
-7.750 -0.2108 0.01403 0.00934 -0.1052 0.8984 0.0265
-7.500 -0.1847 0.01353 0.00873 -0.1048 0.8851 0.0270
-7.250 -0.1585 0.01297 0.00806 -0.1045 0.8727 0.0274
-7.000 -0.1322 0.01244 0.00740 -0.1041 0.8610 0.0279
-6.750 -0.1058 0.01196 0.00679 -0.1037 0.8499 0.0283
-6.500 -0.0791 0.01152 0.00624 -0.1033 0.8395 0.0288
-6.250 -0.0521 0.01116 0.00579 -0.1030 0.8305 0.0294
-6.000 -0.0249 0.01089 0.00542 -0.1027 0.8221 0.0299
-5.750 0.0025 0.01054 0.00502 -0.1025 0.8149 0.0302
-5.500 0.0298 0.01025 0.00465 -0.1023 0.8075 0.0304
-5.250 0.0574 0.01000 0.00435 -0.1021 0.7997 0.0306
-5.000 0.0837 0.00940 0.00367 -0.1017 0.7919 0.0311
-4.750 0.1107 0.00894 0.00315 -0.1015 0.7846 0.0318
-4.500 0.1380 0.00865 0.00282 -0.1013 0.7766 0.0325
-4.250 0.1657 0.00844 0.00258 -0.1012 0.7684 0.0335
-4.000 0.1932 0.00828 0.00237 -0.1009 0.7589 0.0344
-3.750 0.2210 0.00812 0.00217 -0.1008 0.7484 0.0351
-3.500 0.2487 0.00799 0.00200 -0.1007 0.7382 0.0359
-3.250 0.2764 0.00790 0.00184 -0.1005 0.7272 0.0367
-3.000 0.3042 0.00781 0.00171 -0.1004 0.7150 0.0373
-2.750 0.3319 0.00769 0.00155 -0.1002 0.7018 0.0397
-2.500 0.3593 0.00762 0.00144 -0.1000 0.6875 0.0432
-2.250 0.3864 0.00749 0.00136 -0.0998 0.6723 0.0703
-2.000 0.4132 0.00734 0.00132 -0.0996 0.6566 0.1227
-1.750 0.4401 0.00726 0.00132 -0.0995 0.6413 0.1687
-1.500 0.4673 0.00722 0.00133 -0.0993 0.6273 0.2054
-1.250 0.4943 0.00718 0.00134 -0.0992 0.6126 0.2469
-1.000 0.5207 0.00702 0.00137 -0.0990 0.5972 0.3387
-0.750 0.5465 0.00674 0.00143 -0.0989 0.5829 0.4859
-0.500 0.5714 0.00637 0.00151 -0.0984 0.5709 0.6642
-0.250 0.5915 0.00578 0.00165 -0.0963 0.5593 0.9556
0.000 0.6409 0.00590 0.00168 -0.1012 0.5428 1.0000
0.250 0.6665 0.00603 0.00172 -0.1007 0.5279 1.0000
0.500 0.6924 0.00614 0.00177 -0.1003 0.5142 1.0000
0.750 0.7182 0.00628 0.00183 -0.0999 0.4992 1.0000
1.000 0.7435 0.00646 0.00190 -0.0994 0.4802 1.0000
1.250 0.7689 0.00664 0.00198 -0.0990 0.4566 1.0000
1.500 0.7936 0.00689 0.00208 -0.0985 0.4284 1.0000
1.750 0.8180 0.00718 0.00221 -0.0979 0.3979 1.0000
2.000 0.8429 0.00744 0.00235 -0.0974 0.3751 1.0000
2.250 0.8682 0.00768 0.00249 -0.0970 0.3589 1.0000
2.500 0.8940 0.00787 0.00262 -0.0967 0.3467 1.0000
2.750 0.9199 0.00807 0.00277 -0.0965 0.3361 1.0000
3.000 0.9455 0.00828 0.00292 -0.0962 0.3263 1.0000
3.250 0.9720 0.00843 0.00305 -0.0960 0.3196 1.0000
3.500 0.9976 0.00863 0.00322 -0.0958 0.3121 1.0000
3.750 1.0241 0.00878 0.00335 -0.0957 0.3059 1.0000
4.000 1.0498 0.00898 0.00352 -0.0954 0.2985 1.0000
4.250 1.0759 0.00915 0.00368 -0.0953 0.2904 1.0000
4.500 1.1012 0.00937 0.00385 -0.0950 0.2818 1.0000
4.750 1.1274 0.00952 0.00401 -0.0949 0.2751 1.0000
5.000 1.1524 0.00976 0.00420 -0.0945 0.2646 1.0000
5.250 1.1778 0.00996 0.00438 -0.0943 0.2544 1.0000
5.500 1.2028 0.01020 0.00458 -0.0940 0.2432 1.0000
5.750 1.2269 0.01049 0.00481 -0.0936 0.2281 1.0000
6.000 1.2494 0.01090 0.00510 -0.0929 0.2067 1.0000
6.250 1.2709 0.01137 0.00545 -0.0921 0.1842 1.0000
6.500 1.2924 0.01184 0.00582 -0.0913 0.1677 1.0000
6.750 1.3140 0.01227 0.00619 -0.0905 0.1537 1.0000
7.000 1.3349 0.01276 0.00659 -0.0896 0.1375 1.0000
7.250 1.3486 0.01374 0.00728 -0.0877 0.0925 1.0000
7.500 1.3648 0.01452 0.00793 -0.0860 0.0726 1.0000
7.750 1.3789 0.01541 0.00866 -0.0841 0.0484 1.0000
8.000 1.3845 0.01673 0.00977 -0.0807 0.0183 1.0000
8.250 1.4004 0.01730 0.01037 -0.0789 0.0161 1.0000
8.500 1.4166 0.01785 0.01097 -0.0773 0.0152 1.0000
8.750 1.4310 0.01852 0.01168 -0.0754 0.0142 1.0000
9.000 1.4431 0.01934 0.01256 -0.0733 0.0131 1.0000
9.250 1.4585 0.01994 0.01322 -0.0717 0.0127 1.0000
9.500 1.4726 0.02065 0.01398 -0.0700 0.0123 1.0000
9.750 1.4853 0.02145 0.01484 -0.0683 0.0118 1.0000
10.000 1.4969 0.02233 0.01578 -0.0664 0.0114 1.0000
10.250 1.5066 0.02338 0.01688 -0.0645 0.0110 1.0000
10.500 1.5125 0.02473 0.01832 -0.0622 0.0106 1.0000
10.750 1.5144 0.02643 0.02014 -0.0598 0.0102 1.0000
11.000 1.5248 0.02757 0.02134 -0.0584 0.0101 1.0000
11.250 1.5330 0.02892 0.02276 -0.0570 0.0099 1.0000
11.500 1.5404 0.03040 0.02431 -0.0557 0.0097 1.0000
11.750 1.5465 0.03204 0.02603 -0.0544 0.0094 1.0000
12.000 1.5518 0.03381 0.02788 -0.0532 0.0092 1.0000
12.250 1.5561 0.03574 0.02989 -0.0522 0.0089 1.0000
12.500 1.5587 0.03789 0.03212 -0.0512 0.0087 1.0000
12.750 1.5594 0.04031 0.03462 -0.0504 0.0086 1.0000
13.000 1.5575 0.04311 0.03751 -0.0496 0.0084 1.0000
13.250 1.5527 0.04637 0.04086 -0.0491 0.0083 1.0000
13.500 1.5442 0.05021 0.04482 -0.0488 0.0081 1.0000
13.750 1.5318 0.05475 0.04948 -0.0488 0.0080 1.0000
14.000 1.5161 0.05989 0.05475 -0.0492 0.0079 1.0000
14.250 1.5021 0.06500 0.05999 -0.0498 0.0078 1.0000
14.500 1.4983 0.06890 0.06398 -0.0505 0.0078 1.0000
14.750 1.4924 0.07314 0.06833 -0.0513 0.0077 1.0000
15.000 1.4860 0.07750 0.07279 -0.0522 0.0077 1.0000
15.250 1.4778 0.08223 0.07762 -0.0534 0.0076 1.0000
15.500 1.4688 0.08714 0.08264 -0.0546 0.0076 1.0000
15.750 1.4595 0.09215 0.08774 -0.0560 0.0075 1.0000
16.000 1.4503 0.09721 0.09290 -0.0574 0.0074 1.0000
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Polar data table (+)
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