NACA M6 (nacam6-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M6 (nacam6-il) Reynolds number: 500,000 Max Cl/Cd: 89.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam6-il-500000.txt Download as CSV file: xf-nacam6-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4779 0.10403 0.10157 -0.0214 1.0000 0.0355
-10.750 -0.5084 0.09148 0.08905 -0.0330 1.0000 0.0384
-10.500 -0.5307 0.08256 0.08018 -0.0379 1.0000 0.0388
-10.250 -0.5272 0.08039 0.07802 -0.0378 1.0000 0.0392
-10.000 -0.5351 0.07507 0.07272 -0.0422 1.0000 0.0394
-9.750 -0.5512 0.06955 0.06717 -0.0456 1.0000 0.0396
-9.500 -0.5676 0.06545 0.06301 -0.0458 1.0000 0.0398
-9.250 -0.5831 0.06230 0.05982 -0.0438 1.0000 0.0401
-9.000 -0.5966 0.06003 0.05752 -0.0404 1.0000 0.0404
-8.750 -0.6086 0.05734 0.05476 -0.0370 1.0000 0.0408
-8.500 -0.6169 0.05465 0.05200 -0.0338 1.0000 0.0414
-8.250 -0.6263 0.05170 0.04894 -0.0301 1.0000 0.0424
-7.250 -0.6280 0.02631 0.02129 -0.0207 0.9571 0.0371
-7.000 -0.5993 0.02330 0.01790 -0.0216 0.9448 0.0365
-6.750 -0.5675 0.02109 0.01536 -0.0227 0.9306 0.0362
-6.500 -0.5376 0.01974 0.01376 -0.0233 0.9137 0.0366
-6.250 -0.5111 0.01867 0.01247 -0.0230 0.8961 0.0369
-6.000 -0.4859 0.01769 0.01129 -0.0223 0.8789 0.0371
-5.750 -0.4608 0.01681 0.01023 -0.0216 0.8624 0.0373
-5.500 -0.4358 0.01611 0.00939 -0.0209 0.8465 0.0375
-5.250 -0.4106 0.01544 0.00860 -0.0203 0.8312 0.0377
-5.000 -0.3854 0.01488 0.00792 -0.0196 0.8165 0.0380
-4.750 -0.3605 0.01443 0.00736 -0.0188 0.8027 0.0383
-4.500 -0.3352 0.01352 0.00636 -0.0183 0.7897 0.0392
-4.250 -0.3116 0.01295 0.00573 -0.0174 0.7770 0.0399
-4.000 -0.2882 0.01253 0.00527 -0.0164 0.7649 0.0405
-3.750 -0.2650 0.01220 0.00488 -0.0153 0.7538 0.0412
-3.500 -0.2419 0.01190 0.00452 -0.0142 0.7431 0.0420
-3.250 -0.2184 0.01162 0.00420 -0.0132 0.7327 0.0429
-3.000 -0.1950 0.01140 0.00390 -0.0122 0.7235 0.0439
-2.750 -0.1713 0.01117 0.00363 -0.0112 0.7138 0.0450
-2.500 -0.1478 0.01094 0.00334 -0.0101 0.7051 0.0464
-2.250 -0.1242 0.01070 0.00310 -0.0091 0.6962 0.0494
-2.000 -0.0999 0.01055 0.00291 -0.0083 0.6880 0.0531
-1.750 -0.0761 0.01034 0.00274 -0.0073 0.6796 0.0619
-1.500 -0.0543 0.00995 0.00257 -0.0060 0.6720 0.1156
-1.250 -0.0323 0.00962 0.00245 -0.0048 0.6637 0.1766
-1.000 -0.0111 0.00928 0.00235 -0.0035 0.6566 0.2527
-0.750 0.0042 0.00856 0.00221 -0.0011 0.6489 0.4123
-0.500 0.0421 0.00688 0.00221 -0.0034 0.6419 0.8723
-0.250 0.1130 0.00733 0.00267 -0.0122 0.6330 0.9090
0.000 0.1526 0.00774 0.00299 -0.0142 0.6254 0.9210
0.250 0.1971 0.00828 0.00349 -0.0172 0.6171 0.9301
0.500 0.2429 0.00887 0.00398 -0.0203 0.6090 0.9405
0.750 0.2866 0.00937 0.00445 -0.0232 0.6008 0.9506
1.000 0.3370 0.00968 0.00466 -0.0277 0.5926 0.9543
1.250 0.3718 0.00988 0.00485 -0.0290 0.5840 0.9605
1.500 0.4185 0.01005 0.00493 -0.0328 0.5753 0.9646
1.750 0.4579 0.01008 0.00495 -0.0352 0.5652 0.9681
2.000 0.4853 0.01017 0.00500 -0.0352 0.5553 0.9720
2.250 0.5140 0.01019 0.00496 -0.0354 0.5451 0.9744
2.500 0.5472 0.01012 0.00488 -0.0366 0.5352 0.9758
2.750 0.5785 0.01012 0.00483 -0.0375 0.5266 0.9775
3.000 0.6088 0.01010 0.00482 -0.0381 0.5171 0.9796
3.250 0.6364 0.01017 0.00486 -0.0382 0.5084 0.9824
3.500 0.6643 0.01022 0.00489 -0.0383 0.4983 0.9848
3.750 0.6970 0.01014 0.00480 -0.0395 0.4862 0.9862
4.000 0.7283 0.01012 0.00475 -0.0403 0.4745 0.9879
4.250 0.7580 0.01014 0.00474 -0.0409 0.4633 0.9898
4.500 0.7876 0.01016 0.00476 -0.0414 0.4500 0.9921
4.750 0.8167 0.01024 0.00481 -0.0419 0.4347 0.9943
5.000 0.8473 0.01023 0.00474 -0.0427 0.4161 0.9958
5.250 0.8779 0.01026 0.00473 -0.0436 0.3983 0.9976
5.500 0.9094 0.01030 0.00473 -0.0446 0.3779 0.9995
5.750 0.9334 0.01045 0.00483 -0.0441 0.3586 1.0000
6.000 0.9537 0.01066 0.00499 -0.0427 0.3399 1.0000
6.250 0.9733 0.01091 0.00517 -0.0413 0.3180 1.0000
6.500 0.9924 0.01120 0.00538 -0.0399 0.2933 1.0000
6.750 1.0106 0.01157 0.00564 -0.0383 0.2647 1.0000
7.000 1.0278 0.01200 0.00595 -0.0365 0.2348 1.0000
7.250 1.0437 0.01253 0.00631 -0.0346 0.2034 1.0000
7.500 1.0587 0.01311 0.00673 -0.0326 0.1717 1.0000
7.750 1.0715 0.01384 0.00724 -0.0302 0.1306 1.0000
8.000 1.0811 0.01477 0.00791 -0.0273 0.0903 1.0000
8.250 1.0933 0.01548 0.00852 -0.0248 0.0723 1.0000
8.500 1.1061 0.01611 0.00911 -0.0223 0.0606 1.0000
8.750 1.1190 0.01672 0.00969 -0.0199 0.0535 1.0000
9.000 1.1321 0.01729 0.01025 -0.0174 0.0486 1.0000
9.250 1.1437 0.01792 0.01090 -0.0148 0.0453 1.0000
9.500 1.1564 0.01845 0.01147 -0.0123 0.0427 1.0000
9.750 1.1651 0.01916 0.01218 -0.0093 0.0403 1.0000
10.000 1.1716 0.01990 0.01297 -0.0059 0.0384 1.0000
10.250 1.1796 0.02048 0.01362 -0.0027 0.0369 1.0000
10.500 1.1801 0.02106 0.01425 0.0019 0.0356 1.0000
10.750 1.1787 0.02177 0.01500 0.0065 0.0347 1.0000
11.000 1.1729 0.02289 0.01615 0.0111 0.0334 1.0000
11.250 1.1689 0.02419 0.01751 0.0149 0.0326 1.0000
11.500 1.1753 0.02510 0.01851 0.0172 0.0317 1.0000
11.750 1.1800 0.02622 0.01970 0.0195 0.0307 1.0000
12.000 1.1833 0.02755 0.02108 0.0216 0.0297 1.0000
12.250 1.1863 0.02901 0.02259 0.0234 0.0289 1.0000
12.500 1.1854 0.03089 0.02451 0.0252 0.0281 1.0000
12.750 1.1803 0.03324 0.02693 0.0271 0.0273 1.0000
13.000 1.1861 0.03478 0.02855 0.0281 0.0268 1.0000
13.250 1.1914 0.03643 0.03030 0.0291 0.0260 1.0000
13.500 1.1940 0.03836 0.03230 0.0301 0.0254 1.0000
13.750 1.1979 0.04022 0.03423 0.0308 0.0246 1.0000
14.000 1.2005 0.04224 0.03630 0.0315 0.0242 1.0000
14.250 1.2020 0.04441 0.03849 0.0320 0.0235 1.0000
14.500 1.1997 0.04692 0.04104 0.0330 0.0231 1.0000
14.750 1.2001 0.04925 0.04345 0.0336 0.0226 1.0000
15.000 1.2029 0.05148 0.04581 0.0338 0.0221 1.0000
15.250 1.2048 0.05384 0.04826 0.0340 0.0217 1.0000
15.500 1.2064 0.05630 0.05081 0.0341 0.0212 1.0000
15.750 1.2073 0.05887 0.05346 0.0341 0.0208 1.0000
16.000 1.2083 0.06147 0.05614 0.0341 0.0205 1.0000
16.250 1.2090 0.06419 0.05893 0.0338 0.0202 1.0000
16.500 1.2093 0.06703 0.06182 0.0334 0.0197 1.0000
16.750 1.2093 0.06984 0.06467 0.0332 0.0194 1.0000
17.000 1.2082 0.07261 0.06748 0.0335 0.0190 1.0000
17.250 1.2047 0.07612 0.07112 0.0327 0.0187 1.0000
17.500 1.2019 0.07963 0.07476 0.0320 0.0185 1.0000
17.750 1.1979 0.08345 0.07871 0.0307 0.0182 1.0000
18.000 1.1925 0.08747 0.08287 0.0296 0.0179 1.0000
18.250 1.1884 0.09134 0.08685 0.0284 0.0178 1.0000
18.500 1.1825 0.09571 0.09134 0.0266 0.0175 1.0000
18.750 1.1752 0.10018 0.09594 0.0252 0.0174 1.0000
19.000 1.1681 0.10490 0.10076 0.0231 0.0170 1.0000
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Polar data table (+)
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