M6 (85%) (m685-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: M6 (85%) (m685-il) Reynolds number: 100,000 Max Cl/Cd: 49.51 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m685-il-100000-n5.txt Download as CSV file: xf-m685-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4942 0.11975 0.11426 -0.0128 1.0000 0.0381
-11.000 -0.4902 0.11598 0.11050 -0.0136 1.0000 0.0366
-10.500 -0.5094 0.10228 0.09690 -0.0215 1.0000 0.0319
-10.250 -0.5101 0.09795 0.09260 -0.0231 1.0000 0.0317
-10.000 -0.5130 0.09323 0.08792 -0.0252 1.0000 0.0317
-9.750 -0.5142 0.08913 0.08387 -0.0269 1.0000 0.0314
-9.500 -0.5237 0.08317 0.07797 -0.0308 1.0000 0.0314
-9.250 -0.5377 0.07677 0.07160 -0.0355 1.0000 0.0315
-9.000 -0.5492 0.07232 0.06715 -0.0367 1.0000 0.0312
-8.750 -0.5678 0.06761 0.06240 -0.0362 1.0000 0.0312
-8.500 -0.5824 0.06302 0.05771 -0.0350 1.0000 0.0311
-8.250 -0.5960 0.05819 0.05272 -0.0332 1.0000 0.0312
-7.750 -0.6004 0.05254 0.04683 -0.0288 1.0000 0.0335
-7.500 -0.5986 0.05004 0.04418 -0.0264 1.0000 0.0345
-7.250 -0.5973 0.04735 0.04129 -0.0236 1.0000 0.0363
-7.000 -0.6003 0.04367 0.03722 -0.0199 1.0000 0.0378
-6.750 -0.5995 0.04038 0.03354 -0.0163 1.0000 0.0381
-6.500 -0.5962 0.03742 0.03020 -0.0126 1.0000 0.0382
-6.250 -0.5906 0.03486 0.02727 -0.0091 1.0000 0.0383
-6.000 -0.5833 0.03259 0.02463 -0.0057 1.0000 0.0386
-5.750 -0.5746 0.03063 0.02230 -0.0024 1.0000 0.0389
-5.500 -0.5487 0.02842 0.01958 -0.0024 0.9942 0.0394
-5.250 -0.5146 0.02637 0.01732 -0.0042 0.9857 0.0404
-5.000 -0.4798 0.02484 0.01562 -0.0059 0.9763 0.0417
-4.750 -0.4448 0.02355 0.01414 -0.0075 0.9665 0.0437
-4.500 -0.4088 0.02235 0.01274 -0.0092 0.9569 0.0467
-4.250 -0.3711 0.02115 0.01143 -0.0113 0.9485 0.0496
-4.000 -0.3368 0.02030 0.01057 -0.0128 0.9369 0.0534
-3.750 -0.3017 0.01949 0.00967 -0.0142 0.9257 0.0588
-3.500 -0.2660 0.01871 0.00891 -0.0159 0.9151 0.0645
-3.250 -0.2333 0.01795 0.00809 -0.0168 0.9024 0.0711
-3.000 -0.2019 0.01732 0.00742 -0.0174 0.8890 0.0808
-2.750 -0.1718 0.01666 0.00679 -0.0177 0.8755 0.0959
-2.500 -0.1425 0.01604 0.00634 -0.0180 0.8620 0.1288
-2.250 -0.1138 0.01545 0.00593 -0.0181 0.8488 0.1839
-2.000 -0.0235 0.01302 0.00621 -0.0300 0.8455 0.8247
-1.750 0.0272 0.01367 0.00667 -0.0328 0.8337 0.9092
-1.500 0.0880 0.01420 0.00694 -0.0383 0.8217 0.9447
-1.250 0.1509 0.01445 0.00696 -0.0448 0.8082 0.9714
-1.000 0.2257 0.01424 0.00652 -0.0544 0.7946 0.9950
-0.750 0.2623 0.01406 0.00619 -0.0563 0.7795 1.0000
-0.500 0.2855 0.01404 0.00605 -0.0555 0.7649 1.0000
-0.250 0.3087 0.01404 0.00593 -0.0547 0.7511 1.0000
0.000 0.3315 0.01405 0.00582 -0.0538 0.7381 1.0000
0.250 0.3542 0.01407 0.00575 -0.0528 0.7255 1.0000
0.500 0.3767 0.01411 0.00572 -0.0518 0.7126 1.0000
0.750 0.3991 0.01415 0.00570 -0.0508 0.7007 1.0000
1.000 0.4216 0.01420 0.00568 -0.0498 0.6895 1.0000
1.250 0.4440 0.01427 0.00570 -0.0487 0.6780 1.0000
1.500 0.4663 0.01434 0.00574 -0.0477 0.6664 1.0000
1.750 0.4887 0.01442 0.00579 -0.0466 0.6554 1.0000
2.000 0.5112 0.01450 0.00583 -0.0455 0.6448 1.0000
2.250 0.5334 0.01460 0.00594 -0.0444 0.6330 1.0000
2.500 0.5557 0.01470 0.00604 -0.0433 0.6215 1.0000
2.750 0.5779 0.01480 0.00612 -0.0422 0.6096 1.0000
3.000 0.5999 0.01490 0.00620 -0.0409 0.5970 1.0000
3.250 0.6217 0.01501 0.00635 -0.0397 0.5832 1.0000
3.500 0.6435 0.01513 0.00649 -0.0385 0.5695 1.0000
3.750 0.6654 0.01526 0.00664 -0.0373 0.5562 1.0000
4.000 0.6872 0.01540 0.00683 -0.0360 0.5432 1.0000
4.250 0.7090 0.01556 0.00701 -0.0348 0.5306 1.0000
4.500 0.7305 0.01572 0.00721 -0.0335 0.5166 1.0000
4.750 0.7516 0.01589 0.00743 -0.0321 0.5006 1.0000
5.000 0.7720 0.01606 0.00765 -0.0306 0.4809 1.0000
5.250 0.7918 0.01625 0.00785 -0.0290 0.4591 1.0000
5.500 0.8110 0.01647 0.00808 -0.0272 0.4341 1.0000
5.750 0.8293 0.01675 0.00832 -0.0254 0.4052 1.0000
6.000 0.8466 0.01710 0.00859 -0.0234 0.3694 1.0000
6.250 0.8625 0.01758 0.00894 -0.0213 0.3283 1.0000
6.500 0.8773 0.01819 0.00937 -0.0191 0.2813 1.0000
6.750 0.8896 0.01902 0.00994 -0.0167 0.2278 1.0000
7.000 0.9000 0.02008 0.01069 -0.0141 0.1721 1.0000
7.250 0.9089 0.02131 0.01159 -0.0113 0.1191 1.0000
7.500 0.9172 0.02256 0.01261 -0.0085 0.0890 1.0000
7.750 0.9258 0.02375 0.01370 -0.0056 0.0734 1.0000
8.000 0.9351 0.02483 0.01479 -0.0028 0.0626 1.0000
8.250 0.9440 0.02588 0.01589 0.0000 0.0559 1.0000
8.500 0.9524 0.02691 0.01695 0.0028 0.0512 1.0000
8.750 0.9587 0.02804 0.01813 0.0059 0.0480 1.0000
9.000 0.9659 0.02911 0.01929 0.0088 0.0452 1.0000
9.250 0.9720 0.03019 0.02041 0.0118 0.0424 1.0000
9.750 0.9767 0.03254 0.02286 0.0186 0.0391 1.0000
10.000 0.9820 0.03374 0.02416 0.0214 0.0377 1.0000
10.250 0.9884 0.03503 0.02554 0.0238 0.0366 1.0000
10.500 0.9955 0.03643 0.02702 0.0260 0.0355 1.0000
10.750 1.0033 0.03789 0.02856 0.0280 0.0345 1.0000
11.000 1.0124 0.03941 0.03015 0.0297 0.0339 1.0000
11.250 1.0216 0.04105 0.03184 0.0312 0.0331 1.0000
11.500 1.0331 0.04291 0.03374 0.0325 0.0325 1.0000
11.750 1.0429 0.04489 0.03588 0.0339 0.0320 1.0000
12.000 1.0501 0.04695 0.03817 0.0354 0.0317 1.0000
12.250 1.0540 0.04926 0.04074 0.0368 0.0314 1.0000
12.500 1.0555 0.05176 0.04346 0.0380 0.0311 1.0000
12.750 1.0535 0.05454 0.04649 0.0391 0.0309 1.0000
13.000 1.0481 0.05762 0.04982 0.0399 0.0307 1.0000
13.250 1.0399 0.06100 0.05344 0.0402 0.0305 1.0000
13.500 1.0292 0.06480 0.05747 0.0401 0.0305 1.0000
13.750 1.0156 0.06906 0.06196 0.0394 0.0303 1.0000
14.000 0.9992 0.07391 0.06704 0.0380 0.0303 1.0000
14.250 0.9801 0.07942 0.07277 0.0359 0.0302 1.0000
14.500 0.9585 0.08572 0.07928 0.0329 0.0303 1.0000
14.750 0.9346 0.09294 0.08669 0.0291 0.0306 1.0000
15.000 0.9065 0.10164 0.09557 0.0241 0.0308 1.0000
15.250 0.8744 0.11230 0.10636 0.0176 0.0312 1.0000
15.500 0.8417 0.12446 0.11862 0.0105 0.0317 1.0000
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