NN7 MK20 (nn7mk20-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NN7 MK20 (nn7mk20-il) Reynolds number: 100,000 Max Cl/Cd: 43.8 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nn7mk20-il-100000-n5.txt Download as CSV file: xf-nn7mk20-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4499 0.07946 0.07440 -0.0787 1.0000 0.0238
-11.750 -0.4712 0.07479 0.06973 -0.0803 1.0000 0.0236
-11.500 -0.4980 0.07027 0.06518 -0.0814 0.9983 0.0236
-11.250 -0.5058 0.06416 0.05885 -0.0877 0.9825 0.0234
-11.000 -0.5160 0.05848 0.05288 -0.0931 0.9677 0.0235
-10.750 -0.5206 0.05337 0.04740 -0.0982 0.9553 0.0235
-10.500 -0.5221 0.04901 0.04262 -0.1019 0.9420 0.0237
-10.000 -0.5077 0.04255 0.03552 -0.1055 0.9190 0.0243
-9.750 -0.4908 0.04008 0.03281 -0.1069 0.9110 0.0249
-9.500 -0.4769 0.03815 0.03066 -0.1069 0.9007 0.0256
-9.250 -0.4589 0.03636 0.02860 -0.1072 0.8929 0.0267
-9.000 -0.4424 0.03482 0.02681 -0.1068 0.8841 0.0285
-8.750 -0.4229 0.03320 0.02479 -0.1065 0.8768 0.0303
-8.500 -0.4009 0.03148 0.02298 -0.1062 0.8698 0.0316
-8.250 -0.3768 0.03012 0.02155 -0.1062 0.8642 0.0333
-8.000 -0.3571 0.02911 0.02044 -0.1053 0.8566 0.0356
-7.750 -0.3330 0.02816 0.01923 -0.1050 0.8512 0.0389
-7.500 -0.3150 0.02710 0.01825 -0.1040 0.8444 0.0419
-7.250 -0.2948 0.02631 0.01740 -0.1033 0.8383 0.0457
-7.000 -0.2746 0.02551 0.01649 -0.1024 0.8329 0.0500
-6.750 -0.2590 0.02477 0.01578 -0.1012 0.8262 0.0542
-6.500 -0.2383 0.02412 0.01499 -0.1005 0.8214 0.0603
-6.250 -0.2224 0.02340 0.01429 -0.0993 0.8153 0.0662
-6.000 -0.2039 0.02278 0.01362 -0.0984 0.8095 0.0753
-5.750 -0.1835 0.02202 0.01289 -0.0979 0.8052 0.0924
-5.500 -0.1675 0.02132 0.01230 -0.0968 0.7992 0.1205
-5.250 -0.1540 0.02005 0.01156 -0.0960 0.7938 0.2114
-5.000 -0.1384 0.01873 0.01101 -0.0954 0.7897 0.3712
-4.750 -0.1209 0.01911 0.01197 -0.0926 0.7841 0.4735
-4.500 -0.0958 0.01971 0.01256 -0.0914 0.7794 0.5336
-4.250 -0.0681 0.02059 0.01332 -0.0903 0.7757 0.5739
-4.000 -0.0429 0.02114 0.01369 -0.0895 0.7712 0.5959
-3.750 -0.0194 0.02180 0.01428 -0.0877 0.7660 0.6048
-3.500 0.0069 0.02220 0.01454 -0.0868 0.7620 0.6160
-3.250 0.0352 0.02232 0.01446 -0.0869 0.7589 0.6272
-3.000 0.0559 0.02274 0.01484 -0.0851 0.7531 0.6329
-2.750 0.0812 0.02277 0.01472 -0.0850 0.7485 0.6424
-2.500 0.1080 0.02294 0.01478 -0.0843 0.7451 0.6472
-2.250 0.1327 0.02292 0.01464 -0.0841 0.7405 0.6537
-2.000 0.1559 0.02293 0.01456 -0.0837 0.7352 0.6587
-1.750 0.1825 0.02291 0.01445 -0.0834 0.7314 0.6622
-1.500 0.2120 0.02279 0.01419 -0.0839 0.7284 0.6669
-1.250 0.2330 0.02282 0.01416 -0.0835 0.7222 0.6726
-1.000 0.2580 0.02285 0.01412 -0.0830 0.7178 0.6754
-0.750 0.2864 0.02277 0.01396 -0.0831 0.7145 0.6789
-0.500 0.3101 0.02281 0.01395 -0.0829 0.7096 0.6837
-0.250 0.3344 0.02283 0.01390 -0.0829 0.7044 0.6882
0.000 0.3615 0.02279 0.01382 -0.0827 0.7008 0.6910
0.250 0.3905 0.02271 0.01368 -0.0830 0.6978 0.6944
0.500 0.4095 0.02291 0.01390 -0.0821 0.6911 0.6987
0.750 0.4377 0.02286 0.01378 -0.0827 0.6870 0.7028
1.000 0.4669 0.02276 0.01364 -0.0829 0.6839 0.7052
1.250 0.4861 0.02297 0.01389 -0.0818 0.6779 0.7080
1.500 0.5113 0.02301 0.01392 -0.0817 0.6732 0.7110
1.750 0.5419 0.02291 0.01377 -0.0825 0.6698 0.7143
2.000 0.5661 0.02304 0.01390 -0.0824 0.6647 0.7176
2.250 0.5876 0.02318 0.01408 -0.0816 0.6592 0.7197
2.500 0.6166 0.02310 0.01400 -0.0820 0.6555 0.7218
2.750 0.6430 0.02314 0.01407 -0.0820 0.6513 0.7245
3.000 0.6620 0.02343 0.01441 -0.0810 0.6448 0.7275
3.250 0.6920 0.02338 0.01436 -0.0817 0.6409 0.7304
3.500 0.7219 0.02335 0.01432 -0.0824 0.6372 0.7326
3.750 0.7367 0.02373 0.01482 -0.0806 0.6299 0.7347
4.000 0.7653 0.02368 0.01481 -0.0809 0.6259 0.7372
4.250 0.7920 0.02373 0.01490 -0.0809 0.6214 0.7399
4.500 0.8094 0.02410 0.01537 -0.0797 0.6144 0.7428
4.750 0.8408 0.02402 0.01532 -0.0805 0.6103 0.7453
5.000 0.8603 0.02431 0.01569 -0.0796 0.6041 0.7476
5.250 0.8818 0.02447 0.01596 -0.0788 0.5980 0.7498
5.500 0.9150 0.02425 0.01578 -0.0796 0.5940 0.7524
5.750 0.9259 0.02473 0.01639 -0.0773 0.5851 0.7554
6.000 0.9602 0.02440 0.01608 -0.0783 0.5794 0.7583
6.250 0.9725 0.02479 0.01660 -0.0762 0.5698 0.7610
6.500 1.0065 0.02441 0.01627 -0.0770 0.5640 0.7631
6.750 1.0138 0.02491 0.01691 -0.0741 0.5542 0.7657
7.000 1.0448 0.02470 0.01676 -0.0745 0.5479 0.7687
7.250 1.0544 0.02516 0.01737 -0.0720 0.5383 0.7720
7.500 1.0740 0.02531 0.01759 -0.0709 0.5299 0.7753
7.750 1.0938 0.02535 0.01773 -0.0696 0.5211 0.7779
8.000 1.1025 0.02583 0.01833 -0.0670 0.5110 0.7808
8.250 1.1228 0.02593 0.01853 -0.0659 0.5011 0.7839
8.500 1.1410 0.02605 0.01869 -0.0645 0.4884 0.7872
8.750 1.1520 0.02644 0.01914 -0.0623 0.4733 0.7906
9.000 1.1595 0.02701 0.01976 -0.0597 0.4564 0.7941
9.250 1.1683 0.02765 0.02044 -0.0576 0.4392 0.7979
9.500 1.1778 0.02839 0.02123 -0.0557 0.4223 0.8019
9.750 1.1870 0.02922 0.02211 -0.0539 0.4047 0.8055
10.000 1.1960 0.03008 0.02299 -0.0521 0.3859 0.8091
10.250 1.2003 0.03136 0.02431 -0.0502 0.3655 0.8131
10.500 1.2052 0.03267 0.02560 -0.0484 0.3433 0.8175
10.750 1.2077 0.03418 0.02710 -0.0466 0.3194 0.8219
11.000 1.2094 0.03585 0.02870 -0.0449 0.2954 0.8268
11.250 1.2098 0.03774 0.03053 -0.0433 0.2720 0.8321
11.500 1.2094 0.03976 0.03253 -0.0418 0.2507 0.8374
11.750 1.2090 0.04191 0.03467 -0.0405 0.2304 0.8436
12.000 1.2080 0.04421 0.03696 -0.0394 0.2117 0.8506
12.250 1.2072 0.04658 0.03934 -0.0384 0.1945 0.8598
12.500 1.2071 0.04895 0.04180 -0.0377 0.1777 0.8760
12.750 1.2014 0.05117 0.04406 -0.0361 0.1641 1.0000
13.000 1.2014 0.05390 0.04677 -0.0358 0.1499 1.0000
13.250 1.2015 0.05669 0.04953 -0.0355 0.1379 1.0000
13.500 1.2029 0.05941 0.05226 -0.0353 0.1274 1.0000
13.750 1.2055 0.06207 0.05496 -0.0352 0.1182 1.0000
14.000 1.2064 0.06494 0.05781 -0.0352 0.1106 1.0000
14.250 1.2089 0.06772 0.06068 -0.0352 0.1027 1.0000
14.500 1.2101 0.07069 0.06366 -0.0354 0.0955 1.0000
14.750 1.2099 0.07392 0.06692 -0.0358 0.0884 1.0000
15.000 1.2107 0.07712 0.07020 -0.0363 0.0810 1.0000
15.250 1.2070 0.08096 0.07401 -0.0371 0.0745 1.0000
15.500 1.2081 0.08430 0.07748 -0.0379 0.0675 1.0000
15.750 1.2044 0.08830 0.08148 -0.0389 0.0626 1.0000
16.000 1.2063 0.09162 0.08497 -0.0397 0.0574 1.0000
16.250 1.2037 0.09564 0.08907 -0.0409 0.0531 1.0000
16.500 1.2017 0.09964 0.09317 -0.0421 0.0486 1.0000
16.750 1.1989 0.10385 0.09751 -0.0435 0.0441 1.0000
17.000 1.1930 0.10859 0.10229 -0.0453 0.0406 1.0000
17.250 1.1898 0.11304 0.10692 -0.0470 0.0360 1.0000
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