NN7 MK20 (nn7mk20-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NN7 MK20 (nn7mk20-il) Reynolds number: 200,000 Max Cl/Cd: 69.89 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nn7mk20-il-200000-n5.txt Download as CSV file: xf-nn7mk20-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4607 0.08417 0.08050 -0.0724 1.0000 0.0133
-12.750 -0.4992 0.07302 0.06920 -0.0793 1.0000 0.0130
-12.500 -0.5309 0.06547 0.06151 -0.0834 1.0000 0.0128
-12.250 -0.5551 0.05946 0.05534 -0.0862 0.9934 0.0128
-12.000 -0.5683 0.05270 0.04826 -0.0924 0.9729 0.0128
-11.500 -0.5666 0.04215 0.03689 -0.1038 0.9390 0.0135
-11.250 -0.5533 0.03843 0.03275 -0.1080 0.9243 0.0137
-11.000 -0.5397 0.03540 0.02927 -0.1108 0.9084 0.0143
-10.750 -0.5229 0.03357 0.02729 -0.1123 0.8938 0.0147
-10.500 -0.5082 0.03215 0.02574 -0.1129 0.8801 0.0152
-10.250 -0.4958 0.03077 0.02418 -0.1126 0.8673 0.0155
-10.000 -0.4832 0.02942 0.02263 -0.1118 0.8563 0.0159
-9.750 -0.4691 0.02814 0.02116 -0.1109 0.8470 0.0165
-9.500 -0.4543 0.02697 0.01981 -0.1098 0.8381 0.0170
-9.250 -0.4387 0.02588 0.01853 -0.1086 0.8304 0.0177
-9.000 -0.4229 0.02496 0.01742 -0.1074 0.8231 0.0184
-8.750 -0.4087 0.02397 0.01639 -0.1062 0.8166 0.0192
-8.500 -0.3930 0.02320 0.01556 -0.1052 0.8098 0.0200
-8.250 -0.3759 0.02247 0.01472 -0.1043 0.8043 0.0212
-8.000 -0.3586 0.02182 0.01398 -0.1033 0.7977 0.0229
-7.750 -0.3418 0.02106 0.01313 -0.1023 0.7922 0.0247
-7.500 -0.3231 0.02046 0.01249 -0.1017 0.7875 0.0269
-7.250 -0.3044 0.01986 0.01181 -0.1009 0.7819 0.0291
-7.000 -0.2856 0.01919 0.01106 -0.1001 0.7769 0.0316
-6.750 -0.2654 0.01861 0.01043 -0.0996 0.7725 0.0349
-6.500 -0.2438 0.01818 0.00992 -0.0992 0.7672 0.0387
-6.250 -0.2235 0.01752 0.00924 -0.0987 0.7628 0.0430
-6.000 -0.2003 0.01707 0.00867 -0.0985 0.7590 0.0480
-5.750 -0.1784 0.01653 0.00815 -0.0981 0.7541 0.0553
-5.500 -0.1552 0.01604 0.00767 -0.0979 0.7495 0.0668
-5.250 -0.1318 0.01550 0.00719 -0.0978 0.7457 0.0940
-5.000 -0.1089 0.01485 0.00668 -0.0978 0.7421 0.1378
-4.750 -0.0888 0.01384 0.00616 -0.0977 0.7374 0.2449
-4.500 -0.0676 0.01292 0.00572 -0.0976 0.7331 0.3637
-4.250 -0.0445 0.01250 0.00574 -0.0971 0.7297 0.4675
-4.000 -0.0183 0.01268 0.00607 -0.0965 0.7260 0.5300
-3.750 0.0089 0.01293 0.00629 -0.0962 0.7216 0.5665
-3.500 0.0366 0.01322 0.00653 -0.0959 0.7177 0.5843
-3.250 0.0651 0.01333 0.00649 -0.0960 0.7144 0.5952
-3.000 0.0926 0.01353 0.00664 -0.0957 0.7105 0.6013
-2.750 0.1201 0.01365 0.00666 -0.0957 0.7060 0.6114
-2.500 0.1475 0.01392 0.00691 -0.0953 0.7021 0.6173
-2.250 0.1761 0.01398 0.00683 -0.0955 0.6988 0.6251
-2.000 0.2032 0.01409 0.00691 -0.0953 0.6947 0.6286
-1.750 0.2304 0.01416 0.00694 -0.0952 0.6904 0.6316
-1.500 0.2584 0.01417 0.00688 -0.0953 0.6866 0.6347
-1.250 0.2872 0.01414 0.00673 -0.0957 0.6835 0.6386
-1.000 0.3145 0.01413 0.00666 -0.0958 0.6791 0.6421
-0.750 0.3416 0.01418 0.00670 -0.0958 0.6749 0.6440
-0.500 0.3694 0.01422 0.00670 -0.0958 0.6712 0.6463
-0.250 0.3980 0.01425 0.00666 -0.0960 0.6680 0.6490
0.000 0.4246 0.01429 0.00669 -0.0960 0.6633 0.6526
0.250 0.4525 0.01429 0.00663 -0.0963 0.6590 0.6569
0.500 0.4800 0.01434 0.00667 -0.0962 0.6554 0.6588
0.750 0.5077 0.01440 0.00671 -0.0963 0.6518 0.6608
1.000 0.5340 0.01445 0.00679 -0.0962 0.6471 0.6630
1.250 0.5615 0.01448 0.00680 -0.0963 0.6430 0.6653
1.500 0.5899 0.01449 0.00677 -0.0966 0.6394 0.6679
1.750 0.6172 0.01452 0.00678 -0.0968 0.6350 0.6709
2.000 0.6439 0.01456 0.00684 -0.0968 0.6303 0.6727
2.250 0.6711 0.01460 0.00689 -0.0968 0.6263 0.6741
2.500 0.6989 0.01465 0.00694 -0.0969 0.6225 0.6758
2.750 0.7242 0.01474 0.00709 -0.0966 0.6172 0.6778
3.000 0.7510 0.01479 0.00717 -0.0966 0.6126 0.6798
3.250 0.7792 0.01483 0.00719 -0.0968 0.6087 0.6818
3.500 0.8046 0.01491 0.00733 -0.0966 0.6032 0.6841
3.750 0.8313 0.01498 0.00741 -0.0967 0.5981 0.6868
4.000 0.8588 0.01503 0.00747 -0.0967 0.5938 0.6884
4.250 0.8830 0.01515 0.00769 -0.0963 0.5879 0.6900
4.500 0.9087 0.01523 0.00782 -0.0960 0.5825 0.6917
4.750 0.9351 0.01530 0.00792 -0.0959 0.5770 0.6936
5.000 0.9585 0.01537 0.00806 -0.0952 0.5681 0.6956
5.250 0.9827 0.01543 0.00814 -0.0947 0.5591 0.6978
5.500 1.0072 0.01551 0.00824 -0.0943 0.5508 0.7004
5.750 1.0308 0.01564 0.00844 -0.0937 0.5428 0.7027
6.000 1.0546 0.01574 0.00858 -0.0931 0.5352 0.7044
6.250 1.0765 0.01588 0.00882 -0.0922 0.5262 0.7062
6.500 1.0995 0.01602 0.00899 -0.0915 0.5180 0.7081
6.750 1.1206 0.01619 0.00925 -0.0905 0.5083 0.7103
7.000 1.1409 0.01637 0.00947 -0.0893 0.4972 0.7126
7.250 1.1588 0.01658 0.00968 -0.0877 0.4822 0.7151
7.500 1.1738 0.01684 0.00990 -0.0856 0.4640 0.7176
7.750 1.1864 0.01714 0.01021 -0.0830 0.4469 0.7195
8.000 1.1975 0.01747 0.01056 -0.0803 0.4318 0.7217
8.250 1.2081 0.01788 0.01098 -0.0775 0.4166 0.7242
8.500 1.2173 0.01841 0.01149 -0.0747 0.3992 0.7267
8.750 1.2251 0.01903 0.01209 -0.0718 0.3798 0.7294
9.000 1.2303 0.01980 0.01281 -0.0687 0.3587 0.7320
9.250 1.2333 0.02068 0.01367 -0.0655 0.3361 0.7340
9.500 1.2334 0.02178 0.01471 -0.0621 0.3124 0.7363
9.750 1.2332 0.02304 0.01590 -0.0590 0.2881 0.7390
10.000 1.2319 0.02449 0.01727 -0.0561 0.2660 0.7420
10.250 1.2309 0.02607 0.01877 -0.0535 0.2441 0.7450
10.500 1.2303 0.02774 0.02039 -0.0511 0.2248 0.7475
10.750 1.2315 0.02938 0.02201 -0.0491 0.2070 0.7498
11.000 1.2334 0.03107 0.02368 -0.0473 0.1901 0.7523
11.250 1.2357 0.03283 0.02544 -0.0457 0.1741 0.7549
11.500 1.2378 0.03469 0.02728 -0.0443 0.1583 0.7577
11.750 1.2389 0.03672 0.02927 -0.0429 0.1423 0.7604
12.000 1.2396 0.03885 0.03137 -0.0417 0.1269 0.7628
12.250 1.2398 0.04112 0.03359 -0.0407 0.1121 0.7655
12.500 1.2421 0.04330 0.03576 -0.0398 0.1004 0.7685
12.750 1.2441 0.04559 0.03803 -0.0391 0.0891 0.7716
13.000 1.2478 0.04779 0.04025 -0.0386 0.0809 0.7747
13.250 1.2499 0.05021 0.04268 -0.0381 0.0736 0.7773
13.500 1.2551 0.05239 0.04494 -0.0378 0.0668 0.7802
13.750 1.2583 0.05484 0.04742 -0.0376 0.0611 0.7833
14.000 1.2637 0.05711 0.04975 -0.0375 0.0551 0.7866
14.250 1.2669 0.05968 0.05237 -0.0374 0.0504 0.7899
14.500 1.2729 0.06198 0.05478 -0.0375 0.0458 0.7933
14.750 1.2755 0.06471 0.05755 -0.0376 0.0409 0.7973
15.000 1.2804 0.06723 0.06018 -0.0377 0.0363 0.8017
15.250 1.2819 0.07021 0.06320 -0.0380 0.0302 0.8061
15.500 1.2828 0.07333 0.06637 -0.0384 0.0253 0.8110
15.750 1.2824 0.07666 0.06976 -0.0389 0.0200 0.8166
16.000 1.2818 0.08012 0.07331 -0.0395 0.0167 0.8230
16.250 1.2803 0.08376 0.07708 -0.0402 0.0148 0.8315
16.500 1.2785 0.08748 0.08098 -0.0410 0.0132 0.8461
16.750 1.2758 0.09126 0.08496 -0.0424 0.0123 0.9850
17.250 1.2668 0.09944 0.09334 -0.0441 0.0110 1.0000
17.500 1.2636 0.10367 0.09771 -0.0455 0.0106 1.0000
17.750 1.2598 0.10808 0.10224 -0.0471 0.0102 1.0000
18.000 1.2557 0.11260 0.10690 -0.0488 0.0099 1.0000
18.250 1.2508 0.11732 0.11174 -0.0507 0.0096 1.0000
18.500 1.2451 0.12225 0.11679 -0.0529 0.0093 1.0000
18.750 1.2390 0.12728 0.12195 -0.0552 0.0091 1.0000
19.000 1.2326 0.13245 0.12723 -0.0577 0.0090 1.0000
19.250 1.2254 0.13784 0.13274 -0.0605 0.0088 1.0000
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Polar data table (+)
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