NN7 MK20 (nn7mk20-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NN7 MK20 (nn7mk20-il) Reynolds number: 200,000 Max Cl/Cd: 70.22 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nn7mk20-il-200000.txt Download as CSV file: xf-nn7mk20-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NN7 MK20
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3211 0.11462 0.11126 -0.0592 1.0000 0.0577
-11.750 -0.3487 0.10812 0.10490 -0.0643 1.0000 0.0602
-11.500 -0.3880 0.09965 0.09654 -0.0717 0.9965 0.0607
-11.250 -0.3716 0.09463 0.09156 -0.0724 0.9921 0.0620
-11.000 -0.3394 0.09468 0.09159 -0.0711 0.9870 0.0638
-10.750 -0.3218 0.09092 0.08781 -0.0749 0.9812 0.0669
-10.500 -0.3291 0.08100 0.07791 -0.0852 0.9725 0.0694
-10.250 -0.3575 0.06877 0.06552 -0.1000 0.9623 0.0702
-10.000 -0.4448 0.04738 0.04292 -0.1164 0.9414 0.0369
-9.750 -0.4461 0.04224 0.03738 -0.1179 0.9287 0.0345
-9.500 -0.4469 0.03798 0.03258 -0.1176 0.9165 0.0332
-9.250 -0.4352 0.03550 0.02978 -0.1173 0.9075 0.0336
-9.000 -0.4241 0.03291 0.02681 -0.1162 0.8981 0.0336
-8.750 -0.4107 0.03041 0.02391 -0.1148 0.8895 0.0333
-8.500 -0.3907 0.02841 0.02162 -0.1140 0.8826 0.0335
-8.250 -0.3701 0.02687 0.01989 -0.1132 0.8757 0.0343
-8.000 -0.3478 0.02549 0.01833 -0.1124 0.8692 0.0356
-7.750 -0.3235 0.02426 0.01690 -0.1118 0.8640 0.0374
-7.500 -0.3027 0.02308 0.01559 -0.1106 0.8569 0.0399
-7.250 -0.2808 0.02203 0.01459 -0.1100 0.8517 0.0438
-7.000 -0.2601 0.02137 0.01385 -0.1090 0.8457 0.0478
-6.750 -0.2421 0.02034 0.01282 -0.1075 0.8399 0.0520
-6.500 -0.2202 0.01975 0.01218 -0.1070 0.8353 0.0581
-6.250 -0.2039 0.01906 0.01151 -0.1057 0.8287 0.0640
-6.000 -0.1832 0.01849 0.01091 -0.1050 0.8235 0.0713
-5.750 -0.1621 0.01775 0.01016 -0.1045 0.8196 0.0822
-5.500 -0.1445 0.01708 0.00955 -0.1035 0.8132 0.1015
-5.250 -0.1345 0.01493 0.00832 -0.1029 0.8080 0.2660
-5.000 -0.1186 0.01391 0.00839 -0.1015 0.8042 0.4936
-4.750 -0.0945 0.01437 0.00889 -0.1005 0.7985 0.5486
-4.500 -0.0669 0.01487 0.00932 -0.0999 0.7940 0.5742
-4.250 -0.0380 0.01540 0.00969 -0.0995 0.7905 0.5945
-4.000 -0.0121 0.01619 0.01043 -0.0984 0.7858 0.6105
-3.750 0.0135 0.01737 0.01165 -0.0964 0.7809 0.6238
-3.500 0.0406 0.01827 0.01251 -0.0948 0.7770 0.6320
-3.250 0.0695 0.01850 0.01258 -0.0948 0.7739 0.6422
-3.000 0.0917 0.01905 0.01317 -0.0930 0.7683 0.6461
-2.750 0.1185 0.01921 0.01321 -0.0929 0.7638 0.6568
-2.500 0.1451 0.01960 0.01356 -0.0916 0.7604 0.6604
-2.250 0.1701 0.01988 0.01379 -0.0907 0.7563 0.6665
-2.000 0.1939 0.01998 0.01384 -0.0902 0.7511 0.6741
-1.750 0.2196 0.02016 0.01398 -0.0892 0.7472 0.6786
-1.500 0.2502 0.02000 0.01367 -0.0904 0.7441 0.6865
-1.250 0.2721 0.02006 0.01374 -0.0894 0.7389 0.6894
-1.000 0.2966 0.02009 0.01374 -0.0887 0.7343 0.6927
-0.750 0.3252 0.01998 0.01356 -0.0890 0.7307 0.6970
-0.500 0.3560 0.01981 0.01326 -0.0904 0.7274 0.7027
-0.250 0.3764 0.01988 0.01339 -0.0890 0.7216 0.7052
0.000 0.4029 0.01982 0.01330 -0.0889 0.7176 0.7083
0.250 0.4330 0.01969 0.01309 -0.0895 0.7144 0.7121
0.500 0.4601 0.01970 0.01305 -0.0903 0.7094 0.7173
0.750 0.4832 0.01967 0.01305 -0.0895 0.7045 0.7196
1.000 0.5112 0.01956 0.01292 -0.0895 0.7009 0.7225
1.250 0.5417 0.01946 0.01275 -0.0901 0.6979 0.7261
1.500 0.5640 0.01959 0.01293 -0.0899 0.6915 0.7305
1.750 0.5919 0.01949 0.01280 -0.0902 0.6873 0.7334
2.000 0.6216 0.01933 0.01262 -0.0905 0.6841 0.7358
2.250 0.6438 0.01943 0.01278 -0.0898 0.6784 0.7385
2.500 0.6708 0.01941 0.01276 -0.0900 0.6734 0.7415
2.750 0.7031 0.01927 0.01257 -0.0912 0.6699 0.7444
3.000 0.7295 0.01933 0.01264 -0.0915 0.6647 0.7470
3.250 0.7531 0.01930 0.01269 -0.0909 0.6591 0.7491
3.500 0.7832 0.01916 0.01253 -0.0914 0.6553 0.7512
3.750 0.8092 0.01920 0.01260 -0.0914 0.6502 0.7534
4.000 0.8340 0.01925 0.01271 -0.0913 0.6442 0.7558
4.250 0.8662 0.01913 0.01257 -0.0923 0.6401 0.7587
4.500 0.8919 0.01922 0.01271 -0.0924 0.6342 0.7613
4.750 0.9175 0.01909 0.01262 -0.0921 0.6278 0.7631
5.000 0.9494 0.01879 0.01231 -0.0927 0.6223 0.7650
5.250 0.9707 0.01876 0.01238 -0.0918 0.6137 0.7672
5.500 1.0040 0.01854 0.01211 -0.0928 0.6087 0.7698
5.750 1.0240 0.01867 0.01238 -0.0918 0.6004 0.7727
6.000 1.0563 0.01853 0.01220 -0.0927 0.5947 0.7753
6.250 1.0765 0.01856 0.01235 -0.0916 0.5866 0.7772
6.500 1.1054 0.01839 0.01222 -0.0918 0.5802 0.7794
6.750 1.1262 0.01845 0.01240 -0.0908 0.5718 0.7818
7.000 1.1567 0.01821 0.01213 -0.0912 0.5639 0.7845
7.250 1.1751 0.01814 0.01215 -0.0896 0.5518 0.7876
7.500 1.1949 0.01803 0.01210 -0.0883 0.5393 0.7904
7.750 1.2145 0.01796 0.01210 -0.0868 0.5279 0.7928
8.000 1.2359 0.01794 0.01212 -0.0858 0.5170 0.7955
8.250 1.2551 0.01798 0.01219 -0.0843 0.5047 0.7984
8.500 1.2702 0.01811 0.01238 -0.0823 0.4909 0.8014
8.750 1.2844 0.01829 0.01262 -0.0801 0.4764 0.8044
9.000 1.2943 0.01846 0.01283 -0.0771 0.4614 0.8076
9.250 1.3017 0.01873 0.01312 -0.0737 0.4458 0.8112
9.500 1.3075 0.01918 0.01358 -0.0703 0.4288 0.8150
9.750 1.3115 0.01978 0.01420 -0.0669 0.4098 0.8185
10.000 1.3133 0.02045 0.01487 -0.0632 0.3897 0.8219
10.250 1.3132 0.02133 0.01573 -0.0597 0.3677 0.8258
10.500 1.3115 0.02247 0.01683 -0.0562 0.3435 0.8300
10.750 1.3082 0.02385 0.01815 -0.0530 0.3175 0.8343
11.000 1.3024 0.02556 0.01976 -0.0499 0.2901 0.8390
11.250 1.2958 0.02757 0.02165 -0.0472 0.2640 0.8441
11.500 1.2886 0.02982 0.02377 -0.0447 0.2392 0.8491
11.750 1.2827 0.03217 0.02604 -0.0428 0.2137 0.8544
12.000 1.2768 0.03469 0.02846 -0.0411 0.1898 0.8605
12.250 1.2704 0.03741 0.03109 -0.0397 0.1675 0.8675
12.500 1.2681 0.03999 0.03366 -0.0387 0.1476 0.8776
12.750 1.2685 0.04273 0.03644 -0.0387 0.1304 0.9040
13.000 1.2645 0.04505 0.03874 -0.0373 0.1191 1.0000
13.250 1.2646 0.04771 0.04135 -0.0368 0.1088 1.0000
13.500 1.2642 0.05047 0.04407 -0.0365 0.0998 1.0000
13.750 1.2691 0.05280 0.04645 -0.0363 0.0915 1.0000
14.000 1.2696 0.05560 0.04922 -0.0362 0.0853 1.0000
14.250 1.2750 0.05796 0.05167 -0.0362 0.0789 1.0000
14.500 1.2743 0.06098 0.05466 -0.0361 0.0736 1.0000
14.750 1.2806 0.06338 0.05719 -0.0364 0.0672 1.0000
15.000 1.2786 0.06670 0.06048 -0.0365 0.0619 1.0000
15.250 1.2821 0.06956 0.06343 -0.0370 0.0535 1.0000
15.500 1.2808 0.07302 0.06695 -0.0375 0.0447 1.0000
15.750 1.2732 0.07740 0.07130 -0.0381 0.0356 1.0000
16.000 1.2650 0.08194 0.07586 -0.0388 0.0306 1.0000
16.250 1.2613 0.08596 0.07993 -0.0396 0.0274 1.0000
16.500 1.2527 0.09067 0.08468 -0.0405 0.0251 1.0000
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Polar data table (+)
Polar graphs
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