NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 50,000 Max Cl/Cd: 25.27 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m18-il-50000-n5.txt Download as CSV file: xf-m18-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M18 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3734 0.11892 0.11213 -0.0162 1.0000 0.1243
-9.500 -0.3831 0.11708 0.11039 -0.0203 1.0000 0.1277
-9.250 -0.3964 0.11515 0.10859 -0.0253 1.0000 0.1286
-9.000 -0.3758 0.10956 0.10301 -0.0239 1.0000 0.1302
-8.750 -0.3604 0.10552 0.09899 -0.0235 1.0000 0.1327
-8.500 -0.3530 0.10219 0.09572 -0.0245 1.0000 0.1355
-8.250 -0.3505 0.09907 0.09267 -0.0264 1.0000 0.1385
-8.000 -0.3609 0.09652 0.09025 -0.0301 1.0000 0.1427
-7.500 -0.4113 0.09464 0.08863 -0.0327 0.9995 0.1450
-7.250 -0.3784 0.08849 0.08253 -0.0326 0.9913 0.1473
-6.750 -0.3465 0.07540 0.06872 -0.0500 0.9507 0.0977
-6.250 -0.3050 0.06514 0.05805 -0.0556 0.9242 0.0823
-6.000 -0.2841 0.06161 0.05439 -0.0570 0.9118 0.0807
-5.750 -0.2671 0.05832 0.05089 -0.0578 0.8978 0.0791
-5.500 -0.2509 0.05515 0.04746 -0.0581 0.8842 0.0776
-5.250 -0.2347 0.05213 0.04413 -0.0579 0.8712 0.0765
-5.000 -0.2173 0.04947 0.04115 -0.0575 0.8593 0.0768
-4.750 -0.1987 0.04701 0.03833 -0.0568 0.8485 0.0776
-4.500 -0.1810 0.04475 0.03573 -0.0559 0.8363 0.0782
-4.250 -0.1617 0.04253 0.03314 -0.0549 0.8255 0.0781
-4.000 -0.1405 0.04037 0.03056 -0.0538 0.8163 0.0778
-3.750 -0.1196 0.03851 0.02834 -0.0528 0.8053 0.0777
-3.500 -0.0965 0.03674 0.02617 -0.0518 0.7962 0.0780
-3.250 -0.0728 0.03515 0.02421 -0.0509 0.7866 0.0785
-3.000 -0.0481 0.03378 0.02247 -0.0502 0.7772 0.0799
-2.500 0.0040 0.03150 0.01960 -0.0491 0.7592 0.0851
-2.250 0.0316 0.03050 0.01843 -0.0486 0.7514 0.0875
-2.000 0.0599 0.02968 0.01744 -0.0486 0.7418 0.0900
-1.750 0.0935 0.02878 0.01630 -0.0489 0.7347 0.0936
-1.500 0.1270 0.02815 0.01547 -0.0497 0.7251 0.0987
-1.250 0.1581 0.02753 0.01481 -0.0499 0.7182 0.1074
-1.000 0.1850 0.02713 0.01438 -0.0498 0.7087 0.1173
-0.750 0.2115 0.02657 0.01376 -0.0490 0.7021 0.1317
-0.250 0.3643 0.02315 0.01286 -0.0665 0.6865 1.0000
0.250 0.4113 0.02359 0.01278 -0.0650 0.6707 1.0000
0.500 0.4341 0.02392 0.01293 -0.0643 0.6623 1.0000
0.750 0.4572 0.02414 0.01295 -0.0634 0.6553 1.0000
1.000 0.4799 0.02448 0.01315 -0.0627 0.6479 1.0000
1.250 0.5024 0.02480 0.01334 -0.0619 0.6405 1.0000
1.500 0.5256 0.02504 0.01342 -0.0610 0.6347 1.0000
1.750 0.5468 0.02556 0.01389 -0.0603 0.6264 1.0000
2.000 0.5701 0.02579 0.01399 -0.0594 0.6210 1.0000
2.250 0.5907 0.02640 0.01457 -0.0587 0.6133 1.0000
2.500 0.6127 0.02678 0.01488 -0.0578 0.6071 1.0000
2.750 0.6355 0.02710 0.01512 -0.0568 0.6018 1.0000
3.000 0.6542 0.02786 0.01590 -0.0560 0.5939 1.0000
3.250 0.6771 0.02818 0.01615 -0.0550 0.5888 1.0000
3.500 0.6959 0.02891 0.01691 -0.0541 0.5820 1.0000
3.750 0.7156 0.02951 0.01751 -0.0531 0.5755 1.0000
4.000 0.7396 0.02973 0.01768 -0.0521 0.5712 1.0000
4.250 0.7535 0.03086 0.01891 -0.0509 0.5631 1.0000
4.500 0.7750 0.03128 0.01933 -0.0499 0.5576 1.0000
4.750 0.7943 0.03191 0.01997 -0.0488 0.5518 1.0000
5.000 0.8090 0.03288 0.02102 -0.0474 0.5443 1.0000
5.250 0.8336 0.03303 0.02117 -0.0464 0.5398 1.0000
5.500 0.8426 0.03441 0.02266 -0.0447 0.5312 1.0000
5.750 0.8644 0.03475 0.02303 -0.0436 0.5257 1.0000
6.000 0.8781 0.03573 0.02410 -0.0420 0.5187 1.0000
6.250 0.8930 0.03658 0.02503 -0.0405 0.5116 1.0000
6.500 0.9213 0.03646 0.02493 -0.0398 0.5076 1.0000
6.750 0.9193 0.03856 0.02717 -0.0372 0.4977 1.0000
7.000 0.9458 0.03858 0.02727 -0.0364 0.4932 1.0000
7.250 0.9431 0.04076 0.02958 -0.0339 0.4840 1.0000
7.500 0.9658 0.04105 0.02996 -0.0329 0.4788 1.0000
7.750 0.9661 0.04304 0.03205 -0.0306 0.4704 1.0000
8.000 0.9814 0.04388 0.03300 -0.0292 0.4640 1.0000
8.250 1.0163 0.04332 0.03256 -0.0289 0.4606 1.0000
8.500 0.9909 0.04722 0.03656 -0.0254 0.4486 1.0000
8.750 1.0269 0.04652 0.03601 -0.0251 0.4452 1.0000
9.000 0.9904 0.05129 0.04082 -0.0213 0.4324 1.0000
9.250 1.0055 0.05222 0.04186 -0.0201 0.4264 1.0000
9.500 0.9915 0.05591 0.04562 -0.0186 0.4156 1.0000
9.750 1.0269 0.05479 0.04469 -0.0175 0.4121 1.0000
10.000 1.0032 0.05960 0.04956 -0.0163 0.3987 1.0000
10.500 1.0157 0.06278 0.05295 -0.0140 0.3794 1.0000
10.750 1.0124 0.06558 0.05585 -0.0133 0.3677 1.0000
11.250 1.0150 0.07047 0.06097 -0.0119 0.3480 1.0000
11.500 1.0137 0.07340 0.06404 -0.0115 0.3376 1.0000
12.000 1.0346 0.07586 0.06682 -0.0098 0.3212 1.0000
12.250 1.0182 0.08109 0.07212 -0.0103 0.3083 1.0000
12.500 1.0092 0.08524 0.07637 -0.0106 0.2962 1.0000
12.750 1.0180 0.08626 0.07755 -0.0097 0.2849 1.0000
13.000 1.0435 0.08365 0.07513 -0.0075 0.2711 1.0000
13.250 1.0642 0.08161 0.07326 -0.0056 0.2523 1.0000
13.500 1.0915 0.07869 0.07037 -0.0034 0.2303 1.0000
13.750 1.0845 0.08222 0.07397 -0.0037 0.2114 1.0000
14.000 1.0844 0.08461 0.07636 -0.0036 0.1889 1.0000
14.250 1.0798 0.08797 0.07969 -0.0039 0.1658 1.0000
14.500 1.0781 0.09071 0.08222 -0.0039 0.1416 1.0000
14.750 1.0723 0.09429 0.08553 -0.0043 0.1229 1.0000
15.000 1.0651 0.09833 0.08938 -0.0049 0.1086 1.0000
15.250 1.0590 0.10243 0.09336 -0.0055 0.0970 1.0000
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Polar data table (+)
Polar graphs
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