NACA M6 (nacam6-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M6 (nacam6-il) Reynolds number: 200,000 Max Cl/Cd: 67.81 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam6-il-200000.txt Download as CSV file: xf-nacam6-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA M6
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4505 0.10071 0.09691 -0.0266 1.0000 0.0723
-10.000 -0.4980 0.09219 0.08847 -0.0409 1.0000 0.0742
-9.750 -0.5321 0.08739 0.08362 -0.0439 1.0000 0.0744
-9.500 -0.4926 0.08365 0.08001 -0.0399 1.0000 0.0759
-9.250 -0.4740 0.08275 0.07912 -0.0361 1.0000 0.0773
-9.000 -0.4745 0.07950 0.07590 -0.0371 1.0000 0.0788
-8.750 -0.4858 0.07548 0.07189 -0.0387 1.0000 0.0799
-8.500 -0.5016 0.07197 0.06838 -0.0384 1.0000 0.0812
-8.250 -0.5219 0.06899 0.06539 -0.0359 1.0000 0.0824
-8.000 -0.5691 0.06627 0.06240 -0.0311 1.0000 0.0863
-7.750 -0.6059 0.06585 0.06161 -0.0237 1.0000 0.0871
-7.500 -0.6025 0.05926 0.05523 -0.0228 1.0000 0.0884
-7.250 -0.6062 0.05738 0.05343 -0.0188 1.0000 0.0891
-7.000 -0.6000 0.05542 0.05152 -0.0170 0.9974 0.0902
-6.750 -0.5708 0.05233 0.04834 -0.0197 0.9889 0.0928
-6.500 -0.5582 0.04812 0.04346 -0.0209 0.9745 0.1022
-6.250 -0.5231 0.04468 0.04013 -0.0240 0.9696 0.1044
-6.000 -0.5214 0.03190 0.02541 -0.0185 0.9560 0.0629
-5.750 -0.4928 0.02819 0.02146 -0.0194 0.9464 0.0610
-5.500 -0.4569 0.02540 0.01829 -0.0211 0.9396 0.0599
-5.250 -0.4251 0.02349 0.01606 -0.0217 0.9277 0.0598
-5.000 -0.3913 0.02203 0.01433 -0.0227 0.9165 0.0607
-4.750 -0.3563 0.02062 0.01268 -0.0238 0.9059 0.0611
-4.500 -0.3251 0.01948 0.01134 -0.0241 0.8927 0.0616
-4.250 -0.2956 0.01857 0.01030 -0.0242 0.8792 0.0622
-4.000 -0.2669 0.01785 0.00944 -0.0240 0.8662 0.0630
-3.750 -0.2367 0.01675 0.00832 -0.0243 0.8546 0.0646
-3.500 -0.2108 0.01613 0.00771 -0.0238 0.8426 0.0674
-3.250 -0.1867 0.01568 0.00724 -0.0228 0.8298 0.0704
-3.000 -0.1625 0.01525 0.00674 -0.0218 0.8184 0.0733
-2.750 -0.1397 0.01466 0.00613 -0.0205 0.8083 0.0775
-2.500 -0.1183 0.01429 0.00576 -0.0191 0.7964 0.0838
-2.250 -0.0973 0.01381 0.00532 -0.0174 0.7863 0.1003
-2.000 -0.0805 0.01294 0.00494 -0.0152 0.7767 0.1935
-1.750 -0.0677 0.01215 0.00473 -0.0124 0.7665 0.3290
-1.500 0.0533 0.01152 0.00603 -0.0296 0.7593 0.8970
-1.250 0.1237 0.01280 0.00714 -0.0364 0.7489 0.9285
-1.000 0.1980 0.01366 0.00779 -0.0446 0.7394 0.9527
-0.750 0.2736 0.01396 0.00794 -0.0537 0.7282 0.9743
-0.500 0.3377 0.01362 0.00747 -0.0610 0.7174 0.9880
-0.250 0.3974 0.01302 0.00671 -0.0677 0.7077 1.0000
0.000 0.4179 0.01296 0.00662 -0.0665 0.6971 1.0000
0.250 0.4390 0.01295 0.00652 -0.0654 0.6882 1.0000
0.500 0.4600 0.01292 0.00643 -0.0642 0.6785 1.0000
0.750 0.4813 0.01292 0.00638 -0.0631 0.6693 1.0000
1.000 0.5029 0.01292 0.00632 -0.0620 0.6606 1.0000
1.250 0.5243 0.01294 0.00631 -0.0609 0.6516 1.0000
1.500 0.5461 0.01296 0.00626 -0.0599 0.6431 1.0000
1.750 0.5675 0.01298 0.00629 -0.0587 0.6334 1.0000
2.000 0.5897 0.01302 0.00624 -0.0577 0.6253 1.0000
2.250 0.6109 0.01303 0.00628 -0.0565 0.6147 1.0000
2.500 0.6327 0.01307 0.00626 -0.0553 0.6052 1.0000
2.750 0.6543 0.01308 0.00626 -0.0542 0.5948 1.0000
3.000 0.6758 0.01313 0.00631 -0.0530 0.5845 1.0000
3.250 0.6981 0.01318 0.00629 -0.0519 0.5757 1.0000
3.500 0.7194 0.01323 0.00639 -0.0507 0.5650 1.0000
3.750 0.7414 0.01331 0.00645 -0.0496 0.5561 1.0000
4.000 0.7632 0.01337 0.00654 -0.0484 0.5464 1.0000
4.250 0.7848 0.01346 0.00666 -0.0473 0.5363 1.0000
4.500 0.8068 0.01355 0.00668 -0.0461 0.5265 1.0000
4.750 0.8276 0.01360 0.00679 -0.0448 0.5141 1.0000
5.000 0.8486 0.01367 0.00689 -0.0435 0.5019 1.0000
5.250 0.8697 0.01377 0.00699 -0.0422 0.4900 1.0000
5.500 0.8904 0.01386 0.00707 -0.0408 0.4769 1.0000
5.750 0.9101 0.01393 0.00715 -0.0392 0.4602 1.0000
6.000 0.9294 0.01402 0.00726 -0.0375 0.4417 1.0000
6.250 0.9486 0.01415 0.00739 -0.0359 0.4227 1.0000
6.500 0.9678 0.01433 0.00757 -0.0343 0.4052 1.0000
6.750 0.9866 0.01455 0.00777 -0.0327 0.3869 1.0000
7.000 1.0046 0.01482 0.00801 -0.0309 0.3674 1.0000
7.250 1.0225 0.01509 0.00831 -0.0292 0.3448 1.0000
7.500 1.0387 0.01548 0.00862 -0.0272 0.3204 1.0000
7.750 1.0540 0.01592 0.00901 -0.0250 0.2910 1.0000
8.000 1.0671 0.01651 0.00949 -0.0226 0.2556 1.0000
8.250 1.0760 0.01737 0.01013 -0.0197 0.2129 1.0000
8.500 1.0796 0.01859 0.01104 -0.0160 0.1582 1.0000
9.000 1.0793 0.02138 0.01330 -0.0075 0.0933 1.0000
9.250 1.0796 0.02258 0.01445 -0.0033 0.0841 1.0000
9.500 1.0788 0.02370 0.01556 0.0011 0.0779 1.0000
9.750 1.0728 0.02473 0.01660 0.0064 0.0739 1.0000
10.000 1.0718 0.02564 0.01758 0.0106 0.0701 1.0000
10.250 1.0691 0.02683 0.01877 0.0146 0.0668 1.0000
10.500 1.0663 0.02835 0.02026 0.0182 0.0641 1.0000
10.750 1.0717 0.02944 0.02146 0.0207 0.0614 1.0000
11.000 1.0759 0.03071 0.02276 0.0230 0.0585 1.0000
11.250 1.0796 0.03218 0.02422 0.0252 0.0562 1.0000
11.500 1.0864 0.03369 0.02573 0.0272 0.0541 1.0000
11.750 1.0950 0.03497 0.02713 0.0289 0.0523 1.0000
12.000 1.1030 0.03633 0.02854 0.0305 0.0502 1.0000
12.250 1.1112 0.03770 0.02991 0.0320 0.0483 1.0000
12.500 1.1270 0.03927 0.03142 0.0334 0.0462 1.0000
12.750 1.1336 0.04079 0.03312 0.0348 0.0450 1.0000
13.000 1.1429 0.04234 0.03481 0.0362 0.0437 1.0000
13.250 1.1502 0.04399 0.03655 0.0374 0.0422 1.0000
13.500 1.1590 0.04564 0.03826 0.0385 0.0411 1.0000
14.000 1.1816 0.04963 0.04238 0.0406 0.0387 1.0000
14.250 1.1776 0.05205 0.04504 0.0417 0.0380 1.0000
14.500 1.1758 0.05467 0.04787 0.0426 0.0373 1.0000
14.750 1.1734 0.05757 0.05098 0.0434 0.0369 1.0000
15.000 1.1677 0.06067 0.05429 0.0439 0.0363 1.0000
15.250 1.1608 0.06409 0.05791 0.0441 0.0360 1.0000
15.500 1.1524 0.06765 0.06165 0.0440 0.0356 1.0000
15.750 1.1413 0.07166 0.06586 0.0436 0.0353 1.0000
16.000 1.1279 0.07607 0.07046 0.0428 0.0352 1.0000
16.250 1.1156 0.08045 0.07500 0.0417 0.0348 1.0000
16.500 1.1104 0.08407 0.07869 0.0409 0.0342 1.0000
16.750 1.0651 0.09386 0.08889 0.0364 0.0350 1.0000
17.000 1.0205 0.10479 0.10015 0.0308 0.0357 1.0000
17.250 0.9739 0.11743 0.11306 0.0237 0.0367 1.0000
17.500 0.9240 0.13229 0.12811 0.0151 0.0378 1.0000
17.750 0.8833 0.14664 0.14255 0.0074 0.0387 1.0000
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