NACA M12 AIRFOIL (m12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M12 AIRFOIL (m12-il) Reynolds number: 100,000 Max Cl/Cd: 48.78 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m12-il-100000-n5.txt Download as CSV file: xf-m12-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M12 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6060 0.07627 0.07086 -0.0427 1.0000 0.0452
-10.000 -0.6281 0.06979 0.06429 -0.0463 1.0000 0.0449
-9.750 -0.6517 0.06484 0.05923 -0.0464 1.0000 0.0448
-9.500 -0.6718 0.06012 0.05431 -0.0454 1.0000 0.0448
-9.250 -0.6894 0.05528 0.04914 -0.0437 1.0000 0.0449
-9.000 -0.7038 0.05067 0.04407 -0.0411 1.0000 0.0454
-8.750 -0.6984 0.04818 0.04150 -0.0394 1.0000 0.0460
-8.500 -0.6906 0.04615 0.03936 -0.0377 1.0000 0.0467
-8.250 -0.6841 0.04388 0.03689 -0.0356 1.0000 0.0472
-8.000 -0.6791 0.04130 0.03404 -0.0331 1.0000 0.0476
-7.750 -0.6722 0.03892 0.03137 -0.0306 1.0000 0.0480
-7.500 -0.6635 0.03677 0.02894 -0.0281 1.0000 0.0484
-7.250 -0.6534 0.03485 0.02674 -0.0256 1.0000 0.0490
-7.000 -0.6419 0.03327 0.02492 -0.0233 1.0000 0.0500
-6.750 -0.6296 0.03177 0.02314 -0.0210 1.0000 0.0512
-6.500 -0.6162 0.03031 0.02139 -0.0188 1.0000 0.0522
-6.250 -0.5994 0.02888 0.01967 -0.0172 0.9994 0.0529
-6.000 -0.5645 0.02724 0.01769 -0.0190 0.9942 0.0538
-5.750 -0.5304 0.02577 0.01607 -0.0207 0.9884 0.0548
-5.500 -0.4945 0.02459 0.01484 -0.0228 0.9830 0.0561
-5.250 -0.4601 0.02368 0.01387 -0.0245 0.9761 0.0581
-5.000 -0.4240 0.02281 0.01289 -0.0264 0.9701 0.0609
-4.750 -0.3889 0.02194 0.01190 -0.0280 0.9630 0.0633
-4.500 -0.3534 0.02100 0.01096 -0.0298 0.9569 0.0655
-4.250 -0.3204 0.02026 0.01023 -0.0310 0.9488 0.0685
-4.000 -0.2869 0.01959 0.00952 -0.0322 0.9412 0.0728
-3.750 -0.2551 0.01893 0.00888 -0.0331 0.9325 0.0792
-3.500 -0.2241 0.01836 0.00833 -0.0338 0.9235 0.0902
-3.250 -0.1926 0.01773 0.00781 -0.0346 0.9148 0.1083
-3.000 -0.1643 0.01721 0.00739 -0.0347 0.9044 0.1365
-2.750 -0.1331 0.01664 0.00697 -0.0354 0.8961 0.1783
-2.500 -0.1079 0.01600 0.00669 -0.0351 0.8845 0.2493
-2.250 -0.0865 0.01482 0.00645 -0.0341 0.8740 0.4449
-2.000 -0.0608 0.01383 0.00674 -0.0321 0.8656 0.7390
-1.750 -0.0210 0.01397 0.00700 -0.0330 0.8560 0.8377
-1.500 0.0155 0.01411 0.00703 -0.0336 0.8467 0.8824
-1.250 0.0515 0.01429 0.00710 -0.0344 0.8355 0.9140
-1.000 0.0946 0.01447 0.00714 -0.0367 0.8248 0.9379
-0.750 0.1517 0.01462 0.00713 -0.0419 0.8159 0.9626
-0.500 0.2088 0.01467 0.00706 -0.0476 0.8039 0.9836
-0.250 0.2635 0.01454 0.00681 -0.0531 0.7917 0.9970
0.000 0.2937 0.01445 0.00661 -0.0538 0.7786 1.0000
0.250 0.3170 0.01439 0.00644 -0.0529 0.7656 1.0000
0.500 0.3404 0.01435 0.00631 -0.0521 0.7522 1.0000
0.750 0.3639 0.01434 0.00622 -0.0514 0.7385 1.0000
1.000 0.3875 0.01434 0.00615 -0.0506 0.7251 1.0000
1.250 0.4110 0.01435 0.00610 -0.0498 0.7120 1.0000
1.500 0.4345 0.01438 0.00605 -0.0490 0.6991 1.0000
1.750 0.4580 0.01442 0.00601 -0.0481 0.6862 1.0000
2.000 0.4812 0.01448 0.00604 -0.0472 0.6720 1.0000
2.250 0.5044 0.01456 0.00607 -0.0463 0.6576 1.0000
2.500 0.5275 0.01464 0.00610 -0.0454 0.6429 1.0000
2.750 0.5506 0.01474 0.00616 -0.0444 0.6281 1.0000
3.000 0.5736 0.01485 0.00623 -0.0434 0.6136 1.0000
3.250 0.5967 0.01497 0.00632 -0.0425 0.5998 1.0000
3.500 0.6197 0.01511 0.00643 -0.0415 0.5864 1.0000
3.750 0.6427 0.01527 0.00655 -0.0405 0.5734 1.0000
4.000 0.6655 0.01544 0.00672 -0.0395 0.5595 1.0000
4.250 0.6882 0.01563 0.00692 -0.0386 0.5457 1.0000
4.500 0.7108 0.01583 0.00713 -0.0375 0.5319 1.0000
4.750 0.7332 0.01605 0.00734 -0.0365 0.5179 1.0000
5.000 0.7555 0.01628 0.00759 -0.0354 0.5036 1.0000
5.250 0.7776 0.01652 0.00784 -0.0343 0.4886 1.0000
5.500 0.7991 0.01678 0.00810 -0.0331 0.4717 1.0000
5.750 0.8199 0.01704 0.00836 -0.0317 0.4520 1.0000
6.000 0.8401 0.01734 0.00860 -0.0303 0.4307 1.0000
6.250 0.8597 0.01765 0.00891 -0.0288 0.4070 1.0000
6.500 0.8786 0.01801 0.00920 -0.0272 0.3822 1.0000
6.750 0.8971 0.01841 0.00958 -0.0256 0.3544 1.0000
7.000 0.9150 0.01888 0.00997 -0.0239 0.3256 1.0000
7.250 0.9323 0.01941 0.01042 -0.0222 0.2966 1.0000
7.500 0.9490 0.02002 0.01093 -0.0205 0.2680 1.0000
7.750 0.9647 0.02072 0.01154 -0.0187 0.2395 1.0000
8.000 0.9796 0.02150 0.01221 -0.0169 0.2115 1.0000
8.250 0.9938 0.02235 0.01296 -0.0150 0.1823 1.0000
8.500 1.0069 0.02329 0.01379 -0.0130 0.1536 1.0000
8.750 1.0190 0.02431 0.01472 -0.0110 0.1302 1.0000
9.000 1.0295 0.02542 0.01574 -0.0088 0.1134 1.0000
9.250 1.0397 0.02654 0.01682 -0.0066 0.1012 1.0000
9.500 1.0492 0.02766 0.01796 -0.0043 0.0924 1.0000
9.750 1.0553 0.02886 0.01914 -0.0016 0.0862 1.0000
10.000 1.0625 0.03000 0.02036 0.0009 0.0811 1.0000
10.250 1.0694 0.03124 0.02167 0.0032 0.0765 1.0000
10.500 1.0735 0.03273 0.02313 0.0055 0.0730 1.0000
10.750 1.0828 0.03402 0.02456 0.0072 0.0692 1.0000
11.000 1.0905 0.03545 0.02608 0.0089 0.0661 1.0000
11.250 1.0965 0.03705 0.02771 0.0104 0.0634 1.0000
11.500 1.1038 0.03871 0.02942 0.0118 0.0608 1.0000
11.750 1.1125 0.04030 0.03119 0.0130 0.0581 1.0000
12.000 1.1200 0.04200 0.03298 0.0141 0.0557 1.0000
12.250 1.1262 0.04382 0.03484 0.0150 0.0536 1.0000
12.500 1.1330 0.04576 0.03681 0.0160 0.0517 1.0000
12.750 1.1398 0.04775 0.03903 0.0168 0.0497 1.0000
13.000 1.1456 0.04985 0.04128 0.0176 0.0478 1.0000
13.250 1.1500 0.05204 0.04360 0.0181 0.0461 1.0000
13.500 1.1542 0.05426 0.04586 0.0186 0.0446 1.0000
13.750 1.1589 0.05665 0.04828 0.0191 0.0432 1.0000
14.000 1.1586 0.05962 0.05154 0.0193 0.0420 1.0000
14.250 1.1571 0.06278 0.05494 0.0193 0.0408 1.0000
14.500 1.1542 0.06612 0.05847 0.0190 0.0397 1.0000
14.750 1.1505 0.06956 0.06208 0.0184 0.0387 1.0000
15.000 1.1474 0.07297 0.06560 0.0178 0.0377 1.0000
15.250 1.1452 0.07629 0.06900 0.0171 0.0369 1.0000
15.500 1.1427 0.07982 0.07259 0.0164 0.0361 1.0000
15.750 1.1271 0.08546 0.07853 0.0142 0.0357 1.0000
16.000 1.1097 0.09171 0.08506 0.0114 0.0353 1.0000
16.250 1.0900 0.09874 0.09233 0.0079 0.0351 1.0000
16.500 1.0670 0.10678 0.10062 0.0035 0.0349 1.0000
16.750 1.0394 0.11636 0.11044 -0.0022 0.0350 1.0000
17.000 1.0045 0.12845 0.12276 -0.0097 0.0352 1.0000
17.250 0.9516 0.14673 0.14123 -0.0210 0.0357 1.0000
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