M6 (85%) (m685-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 200,000 Max Cl/Cd: 66.92 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-m685-il-200000.txt Download as CSV file: xf-m685-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: M6 (85%)
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4894 0.08961 0.08600 -0.0266 1.0000 0.0565
-9.000 -0.5141 0.08325 0.07967 -0.0352 1.0000 0.0573
-8.750 -0.5422 0.07936 0.07572 -0.0356 1.0000 0.0576
-8.500 -0.5652 0.07593 0.07213 -0.0345 1.0000 0.0578
-8.250 -0.5563 0.07038 0.06673 -0.0339 1.0000 0.0588
-8.000 -0.5441 0.06837 0.06480 -0.0320 1.0000 0.0601
-7.750 -0.5425 0.06580 0.06221 -0.0305 1.0000 0.0614
-7.500 -0.5441 0.06285 0.05922 -0.0291 1.0000 0.0629
-7.250 -0.5477 0.05962 0.05587 -0.0273 1.0000 0.0657
-7.000 -0.5757 0.05543 0.05111 -0.0226 1.0000 0.0697
-6.750 -0.5648 0.05180 0.04764 -0.0213 1.0000 0.0710
-6.500 -0.5564 0.04975 0.04565 -0.0191 1.0000 0.0729
-6.250 -0.5530 0.04770 0.04354 -0.0160 1.0000 0.0751
-6.000 -0.5646 0.04912 0.04429 -0.0086 1.0000 0.0822
-5.750 -0.5735 0.04328 0.03856 -0.0052 1.0000 0.0840
-5.500 -0.5602 0.03044 0.02403 -0.0011 0.9924 0.0481
-5.250 -0.5255 0.02722 0.02040 -0.0031 0.9860 0.0478
-5.000 -0.4903 0.02498 0.01775 -0.0047 0.9781 0.0484
-4.750 -0.4532 0.02237 0.01485 -0.0068 0.9719 0.0491
-4.500 -0.4138 0.02054 0.01279 -0.0090 0.9651 0.0494
-4.250 -0.3732 0.01896 0.01110 -0.0115 0.9587 0.0503
-4.000 -0.3316 0.01770 0.00976 -0.0142 0.9518 0.0519
-3.750 -0.2896 0.01661 0.00862 -0.0169 0.9449 0.0547
-3.500 -0.2497 0.01563 0.00757 -0.0191 0.9356 0.0583
-3.250 -0.2139 0.01468 0.00670 -0.0208 0.9241 0.0644
-3.000 -0.1784 0.01395 0.00598 -0.0222 0.9122 0.0739
-2.750 -0.1461 0.01333 0.00539 -0.0230 0.8989 0.0867
-2.500 -0.1189 0.01275 0.00488 -0.0226 0.8837 0.1122
-2.250 -0.0988 0.01184 0.00444 -0.0210 0.8683 0.2071
-2.000 -0.0869 0.01076 0.00414 -0.0179 0.8528 0.4007
-1.750 0.0082 0.00998 0.00504 -0.0298 0.8464 0.9074
-1.500 0.0900 0.01115 0.00597 -0.0388 0.8367 0.9448
-1.250 0.1618 0.01162 0.00625 -0.0469 0.8232 0.9678
-1.000 0.2369 0.01157 0.00601 -0.0563 0.8091 0.9875
-0.750 0.2978 0.01114 0.00542 -0.0633 0.7940 1.0000
-0.500 0.3187 0.01113 0.00529 -0.0621 0.7788 1.0000
-0.250 0.3398 0.01113 0.00518 -0.0608 0.7648 1.0000
0.000 0.3612 0.01114 0.00509 -0.0596 0.7517 1.0000
0.250 0.3827 0.01116 0.00501 -0.0585 0.7394 1.0000
0.500 0.4044 0.01117 0.00496 -0.0573 0.7269 1.0000
0.750 0.4260 0.01120 0.00493 -0.0562 0.7145 1.0000
1.000 0.4480 0.01124 0.00490 -0.0551 0.7032 1.0000
1.250 0.4702 0.01129 0.00488 -0.0540 0.6924 1.0000
1.500 0.4920 0.01133 0.00489 -0.0528 0.6800 1.0000
1.750 0.5141 0.01138 0.00491 -0.0517 0.6681 1.0000
2.000 0.5361 0.01143 0.00491 -0.0505 0.6560 1.0000
2.250 0.5581 0.01149 0.00491 -0.0493 0.6437 1.0000
2.500 0.5801 0.01153 0.00495 -0.0481 0.6307 1.0000
2.750 0.6020 0.01159 0.00500 -0.0469 0.6179 1.0000
3.000 0.6243 0.01166 0.00507 -0.0458 0.6062 1.0000
3.250 0.6468 0.01175 0.00513 -0.0447 0.5951 1.0000
3.500 0.6689 0.01182 0.00521 -0.0435 0.5824 1.0000
3.750 0.6907 0.01189 0.00530 -0.0423 0.5684 1.0000
4.000 0.7124 0.01196 0.00537 -0.0410 0.5538 1.0000
4.250 0.7339 0.01203 0.00545 -0.0397 0.5384 1.0000
4.500 0.7553 0.01212 0.00555 -0.0383 0.5224 1.0000
4.750 0.7765 0.01221 0.00563 -0.0369 0.5051 1.0000
5.000 0.7968 0.01229 0.00569 -0.0354 0.4826 1.0000
5.250 0.8167 0.01241 0.00579 -0.0338 0.4581 1.0000
5.500 0.8367 0.01257 0.00594 -0.0322 0.4334 1.0000
5.750 0.8559 0.01279 0.00611 -0.0305 0.4046 1.0000
6.000 0.8744 0.01308 0.00632 -0.0288 0.3703 1.0000
6.250 0.8910 0.01350 0.00659 -0.0268 0.3247 1.0000
6.500 0.9052 0.01416 0.00697 -0.0245 0.2646 1.0000
6.750 0.9148 0.01524 0.00760 -0.0216 0.1858 1.0000
7.000 0.9194 0.01683 0.00859 -0.0182 0.1000 1.0000
7.250 0.9256 0.01827 0.00981 -0.0147 0.0721 1.0000
7.500 0.9344 0.01941 0.01091 -0.0115 0.0597 1.0000
7.750 0.9470 0.02022 0.01179 -0.0089 0.0533 1.0000
8.000 0.9534 0.02146 0.01300 -0.0055 0.0487 1.0000
8.250 0.9648 0.02234 0.01396 -0.0027 0.0463 1.0000
8.500 0.9755 0.02328 0.01493 0.0001 0.0442 1.0000
8.750 0.9857 0.02430 0.01596 0.0028 0.0427 1.0000
9.000 0.9958 0.02558 0.01722 0.0055 0.0414 1.0000
9.250 1.0097 0.02737 0.01901 0.0075 0.0401 1.0000
9.500 1.0262 0.02856 0.02031 0.0093 0.0395 1.0000
9.750 1.0433 0.02986 0.02173 0.0108 0.0390 1.0000
10.000 1.0595 0.03120 0.02320 0.0125 0.0383 1.0000
10.250 1.0752 0.03264 0.02479 0.0141 0.0376 1.0000
10.500 1.0896 0.03419 0.02651 0.0159 0.0369 1.0000
10.750 1.1029 0.03601 0.02851 0.0177 0.0365 1.0000
11.000 1.1143 0.03805 0.03077 0.0197 0.0365 1.0000
11.250 1.1219 0.04030 0.03327 0.0221 0.0365 1.0000
11.500 1.1250 0.04269 0.03592 0.0248 0.0366 1.0000
11.750 1.1212 0.04506 0.03855 0.0285 0.0368 1.0000
12.000 1.1140 0.04754 0.04127 0.0322 0.0371 1.0000
12.250 1.1037 0.05027 0.04424 0.0355 0.0373 1.0000
12.500 1.0919 0.05328 0.04748 0.0381 0.0378 1.0000
12.750 1.0774 0.05660 0.05102 0.0402 0.0381 1.0000
13.000 1.0608 0.06028 0.05491 0.0414 0.0385 1.0000
13.250 1.0428 0.06437 0.05919 0.0419 0.0388 1.0000
13.500 1.0251 0.06895 0.06393 0.0416 0.0392 1.0000
13.750 1.0059 0.07414 0.06927 0.0407 0.0396 1.0000
14.000 1.0079 0.07815 0.07336 0.0407 0.0407 1.0000
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Polar data table (+)
Polar graphs
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