NN7 MK20 (nn7mk20-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NN7 MK20 (nn7mk20-il) Reynolds number: 100,000 Max Cl/Cd: 44.16 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nn7mk20-il-100000.txt Download as CSV file: xf-nn7mk20-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3534 0.11831 0.11394 -0.0546 1.0000 0.1302
-11.000 -0.3984 0.11928 0.11510 -0.0499 1.0000 0.1306
-10.750 -0.4236 0.11779 0.11375 -0.0468 1.0000 0.1314
-10.500 -0.4011 0.11644 0.11238 -0.0411 1.0000 0.1337
-10.250 -0.3781 0.11236 0.10827 -0.0443 0.9960 0.1399
-10.000 -0.3840 0.10612 0.10207 -0.0517 0.9903 0.1480
-9.750 -0.3597 0.10266 0.09857 -0.0539 0.9859 0.1559
-9.500 -0.3474 0.09810 0.09402 -0.0581 0.9818 0.1663
-8.500 -0.5280 0.05441 0.04885 -0.0903 0.9341 0.0676
-8.250 -0.5255 0.04959 0.04296 -0.0905 0.9271 0.0602
-8.000 -0.5168 0.04640 0.03952 -0.0894 0.9200 0.0594
-7.750 -0.4979 0.04339 0.03609 -0.0897 0.9143 0.0595
-7.500 -0.4681 0.04044 0.03256 -0.0916 0.9110 0.0614
-7.250 -0.4629 0.03859 0.03062 -0.0888 0.9033 0.0628
-7.000 -0.4331 0.03640 0.02823 -0.0897 0.8991 0.0650
-6.750 -0.3942 0.03444 0.02604 -0.0918 0.8964 0.0690
-6.500 -0.3874 0.03405 0.02541 -0.0886 0.8885 0.0727
-6.250 -0.3583 0.03228 0.02372 -0.0889 0.8847 0.0783
-6.000 -0.3202 0.03114 0.02243 -0.0907 0.8817 0.0877
-5.500 -0.2911 0.02972 0.02121 -0.0866 0.8698 0.1040
-5.250 -0.2602 0.02858 0.02023 -0.0873 0.8667 0.1206
-5.000 -0.2596 0.02827 0.02005 -0.0835 0.8593 0.1365
-4.750 -0.2503 0.02548 0.01873 -0.0832 0.8540 0.3239
-4.500 -0.2235 0.02751 0.02174 -0.0791 0.8507 0.5739
-4.250 -0.2256 0.02877 0.02288 -0.0738 0.8423 0.5963
-4.000 -0.1997 0.03071 0.02473 -0.0706 0.8379 0.6164
-3.750 -0.1649 0.03284 0.02675 -0.0680 0.8352 0.6431
-3.500 -0.1789 0.03399 0.02790 -0.0609 0.8258 0.6570
-3.250 -0.1566 0.03562 0.02948 -0.0559 0.8220 0.6758
-3.000 -0.1479 0.03629 0.03007 -0.0521 0.8162 0.6901
-2.750 -0.1391 0.03675 0.03044 -0.0488 0.8098 0.7040
-2.500 -0.1107 0.03700 0.03056 -0.0474 0.8063 0.7195
-2.250 -0.1106 0.03739 0.03088 -0.0438 0.7990 0.7321
-2.000 -0.0952 0.03745 0.03087 -0.0411 0.7937 0.7417
-1.750 -0.0621 0.03722 0.03049 -0.0416 0.7905 0.7527
-1.500 -0.0680 0.03762 0.03085 -0.0376 0.7823 0.7633
-1.250 -0.0430 0.03751 0.03062 -0.0374 0.7774 0.7737
-1.000 -0.0064 0.03712 0.03010 -0.0385 0.7746 0.7808
-0.750 -0.0129 0.03771 0.03065 -0.0353 0.7653 0.7880
-0.500 0.0180 0.03742 0.03026 -0.0359 0.7611 0.7938
-0.250 0.0345 0.03765 0.03041 -0.0353 0.7552 0.7997
0.000 0.0512 0.03790 0.03058 -0.0351 0.7484 0.8053
0.250 0.0871 0.03757 0.03017 -0.0363 0.7449 0.8100
0.500 0.0896 0.03833 0.03088 -0.0343 0.7366 0.8151
0.750 0.1201 0.03835 0.03082 -0.0357 0.7317 0.8197
1.000 0.1603 0.03797 0.03037 -0.0373 0.7288 0.8241
1.250 0.1544 0.03907 0.03147 -0.0345 0.7189 0.8287
1.500 0.1935 0.03904 0.03135 -0.0369 0.7151 0.8331
1.750 0.1969 0.03976 0.03208 -0.0347 0.7067 0.8370
2.000 0.2246 0.03991 0.03220 -0.0353 0.7016 0.8411
2.250 0.2674 0.03973 0.03197 -0.0378 0.6989 0.8448
2.500 0.2646 0.04112 0.03335 -0.0359 0.6886 0.8482
2.750 0.3008 0.04094 0.03316 -0.0371 0.6849 0.8513
3.000 0.3032 0.04219 0.03442 -0.0356 0.6761 0.8545
3.250 0.3364 0.04230 0.03451 -0.0369 0.6712 0.8578
3.500 0.3809 0.04207 0.03427 -0.0393 0.6686 0.8608
3.750 0.3735 0.04386 0.03608 -0.0372 0.6577 0.8635
4.000 0.4134 0.04361 0.03585 -0.0387 0.6545 0.8663
4.250 0.4097 0.04534 0.03761 -0.0369 0.6443 0.8699
4.500 0.4479 0.04527 0.03755 -0.0385 0.6403 0.8732
4.750 0.4537 0.04682 0.03913 -0.0378 0.6310 0.8761
5.000 0.4884 0.04686 0.03920 -0.0390 0.6261 0.8789
5.250 0.5357 0.04616 0.03854 -0.0410 0.6236 0.8824
5.500 0.5309 0.04817 0.04059 -0.0393 0.6116 0.8863
5.750 0.5792 0.04742 0.03990 -0.0413 0.6089 0.8900
6.000 0.5774 0.04941 0.04195 -0.0401 0.5970 0.8936
6.250 0.6270 0.04835 0.04096 -0.0419 0.5942 0.8974
6.500 0.6278 0.05023 0.04293 -0.0409 0.5821 0.9022
6.750 0.6487 0.05097 0.04374 -0.0411 0.5737 0.9075
7.000 0.6808 0.05084 0.04373 -0.0418 0.5671 0.9135
7.250 0.7142 0.05072 0.04374 -0.0426 0.5609 0.9201
7.500 0.7403 0.05114 0.04430 -0.0434 0.5520 0.9284
8.250 0.8221 0.05202 0.04557 -0.0458 0.5257 1.0000
8.500 0.8750 0.04988 0.04356 -0.0472 0.5222 1.0000
8.750 0.9383 0.04650 0.04035 -0.0487 0.5210 1.0000
9.000 1.0128 0.04177 0.03582 -0.0505 0.5208 1.0000
9.250 1.0952 0.03622 0.03046 -0.0529 0.5155 1.0000
9.500 1.2061 0.02988 0.02427 -0.0592 0.5055 1.0000
9.750 1.2383 0.02898 0.02345 -0.0593 0.4906 1.0000
10.000 1.2616 0.02857 0.02309 -0.0585 0.4738 1.0000
10.250 1.2672 0.02909 0.02367 -0.0559 0.4557 1.0000
10.500 1.2791 0.02937 0.02398 -0.0541 0.4353 1.0000
10.750 1.2916 0.02972 0.02432 -0.0524 0.4129 1.0000
11.000 1.2922 0.03084 0.02544 -0.0498 0.3889 1.0000
11.250 1.2914 0.03222 0.02677 -0.0474 0.3630 1.0000
11.500 1.2894 0.03385 0.02829 -0.0451 0.3351 1.0000
11.750 1.2846 0.03584 0.03011 -0.0429 0.3060 1.0000
12.000 1.2784 0.03814 0.03220 -0.0408 0.2770 1.0000
12.250 1.2717 0.04067 0.03448 -0.0388 0.2494 1.0000
12.500 1.2671 0.04321 0.03674 -0.0371 0.2242 1.0000
12.750 1.2637 0.04588 0.03929 -0.0357 0.2015 1.0000
13.000 1.2657 0.04819 0.04140 -0.0346 0.1830 1.0000
13.250 1.2724 0.05023 0.04324 -0.0337 0.1671 1.0000
13.500 1.2768 0.05249 0.04551 -0.0329 0.1542 1.0000
13.750 1.2801 0.05487 0.04791 -0.0322 0.1428 1.0000
14.000 1.2816 0.05739 0.05046 -0.0317 0.1324 1.0000
14.250 1.2814 0.06007 0.05309 -0.0314 0.1227 1.0000
14.500 1.2787 0.06299 0.05600 -0.0313 0.1136 1.0000
14.750 1.2756 0.06619 0.05934 -0.0312 0.1053 1.0000
15.000 1.2781 0.06885 0.06195 -0.0311 0.0972 1.0000
15.250 1.2748 0.07222 0.06543 -0.0313 0.0895 1.0000
15.500 1.2724 0.07566 0.06896 -0.0314 0.0814 1.0000
15.750 1.2696 0.07915 0.07238 -0.0315 0.0725 1.0000
16.000 1.2614 0.08342 0.07675 -0.0322 0.0648 1.0000
16.250 1.2571 0.08749 0.08093 -0.0325 0.0574 1.0000
16.500 1.2626 0.09027 0.08357 -0.0323 0.0507 1.0000
16.750 1.2578 0.09464 0.08827 -0.0330 0.0474 1.0000
17.000 1.2571 0.09830 0.09203 -0.0337 0.0443 1.0000
17.250 1.2667 0.10075 0.09439 -0.0336 0.0410 1.0000
17.500 1.2574 0.10581 0.09976 -0.0351 0.0398 1.0000
17.750 1.2482 0.11098 0.10521 -0.0370 0.0386 1.0000
18.000 1.2391 0.11628 0.11075 -0.0390 0.0376 1.0000
18.250 1.2290 0.12185 0.11655 -0.0414 0.0368 1.0000
18.500 1.2161 0.12805 0.12297 -0.0444 0.0362 1.0000
18.750 1.2001 0.13502 0.13017 -0.0481 0.0360 1.0000
19.000 1.1754 0.14409 0.13953 -0.0535 0.0364 1.0000
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Polar data table (+)
Polar graphs
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