NACA M18 (nacam18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 50,000 Max Cl/Cd: 26.18 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam18-il-50000-n5.txt Download as CSV file: xf-nacam18-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M18
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3519 0.10127 0.09481 -0.0244 1.0000 0.1362
-8.000 -0.3504 0.09819 0.09181 -0.0264 1.0000 0.1393
-7.750 -0.3672 0.09605 0.08983 -0.0306 1.0000 0.1435
-7.500 -0.3940 0.09516 0.08906 -0.0333 1.0000 0.1448
-7.000 -0.3650 0.08684 0.08085 -0.0336 0.9832 0.1489
-6.750 -0.3441 0.08291 0.07685 -0.0373 0.9657 0.1548
-6.250 -0.3182 0.06756 0.06045 -0.0552 0.9293 0.0834
-6.000 -0.2967 0.06409 0.05695 -0.0560 0.9165 0.0819
-5.750 -0.2787 0.06074 0.05345 -0.0570 0.9034 0.0803
-5.500 -0.2618 0.05746 0.04994 -0.0577 0.8909 0.0787
-5.250 -0.2446 0.05423 0.04642 -0.0581 0.8796 0.0772
-5.000 -0.2288 0.05133 0.04322 -0.0578 0.8671 0.0762
-4.750 -0.2119 0.04882 0.04040 -0.0573 0.8555 0.0767
-4.500 -0.1933 0.04644 0.03766 -0.0567 0.8456 0.0776
-4.250 -0.1746 0.04419 0.03505 -0.0558 0.8351 0.0781
-4.000 -0.1552 0.04204 0.03253 -0.0548 0.8249 0.0779
-3.750 -0.1334 0.03993 0.03001 -0.0539 0.8166 0.0776
-3.500 -0.1122 0.03814 0.02786 -0.0529 0.8062 0.0777
-3.250 -0.0883 0.03638 0.02570 -0.0521 0.7986 0.0780
-3.000 -0.0649 0.03491 0.02389 -0.0513 0.7887 0.0786
-2.750 -0.0391 0.03355 0.02214 -0.0505 0.7812 0.0804
-2.500 -0.0131 0.03249 0.02065 -0.0499 0.7720 0.0830
-2.250 0.0136 0.03139 0.01943 -0.0496 0.7647 0.0857
-2.000 0.0403 0.03053 0.01844 -0.0494 0.7557 0.0880
-1.750 0.0711 0.02962 0.01731 -0.0494 0.7490 0.0908
-1.500 0.1043 0.02890 0.01640 -0.0501 0.7400 0.0946
-1.250 0.1390 0.02812 0.01546 -0.0508 0.7340 0.1007
-1.000 0.1672 0.02779 0.01508 -0.0510 0.7247 0.1099
-0.750 0.1951 0.02720 0.01446 -0.0506 0.7185 0.1209
-0.500 0.2190 0.02688 0.01417 -0.0500 0.7095 0.1375
-0.250 0.2431 0.02633 0.01372 -0.0491 0.7032 0.1725
0.000 0.2623 0.02568 0.01359 -0.0480 0.6951 0.2574
0.250 0.3968 0.02376 0.01319 -0.0669 0.6883 1.0000
0.500 0.4197 0.02403 0.01324 -0.0661 0.6807 1.0000
0.750 0.4425 0.02428 0.01330 -0.0653 0.6730 1.0000
1.000 0.4653 0.02452 0.01335 -0.0644 0.6661 1.0000
1.250 0.4874 0.02487 0.01358 -0.0637 0.6579 1.0000
1.500 0.5110 0.02500 0.01352 -0.0627 0.6524 1.0000
1.750 0.5316 0.02554 0.01402 -0.0620 0.6431 1.0000
2.000 0.5549 0.02571 0.01404 -0.0611 0.6373 1.0000
2.250 0.5752 0.02628 0.01458 -0.0603 0.6287 1.0000
2.500 0.5979 0.02653 0.01473 -0.0594 0.6223 1.0000
2.750 0.6184 0.02703 0.01519 -0.0585 0.6147 1.0000
3.000 0.6398 0.02744 0.01556 -0.0576 0.6076 1.0000
3.250 0.6622 0.02774 0.01578 -0.0566 0.6015 1.0000
3.500 0.6807 0.02841 0.01648 -0.0557 0.5929 1.0000
3.750 0.7047 0.02857 0.01657 -0.0547 0.5878 1.0000
4.000 0.7207 0.02945 0.01751 -0.0536 0.5786 1.0000
4.250 0.7437 0.02969 0.01771 -0.0527 0.5728 1.0000
4.500 0.7602 0.03052 0.01860 -0.0515 0.5646 1.0000
4.750 0.7812 0.03091 0.01900 -0.0505 0.5580 1.0000
5.000 0.8000 0.03152 0.01963 -0.0494 0.5510 1.0000
5.250 0.8172 0.03223 0.02041 -0.0481 0.5433 1.0000
5.500 0.8436 0.03222 0.02037 -0.0474 0.5388 1.0000
5.750 0.8516 0.03364 0.02192 -0.0456 0.5288 1.0000
6.000 0.8771 0.03370 0.02199 -0.0449 0.5239 1.0000
6.250 0.8842 0.03514 0.02356 -0.0430 0.5144 1.0000
6.500 0.9081 0.03533 0.02379 -0.0421 0.5091 1.0000
6.750 0.9151 0.03677 0.02535 -0.0402 0.5003 1.0000
7.000 0.9364 0.03714 0.02578 -0.0392 0.4944 1.0000
7.250 0.9456 0.03844 0.02719 -0.0374 0.4866 1.0000
7.500 0.9610 0.03926 0.02811 -0.0361 0.4797 1.0000
7.750 0.9925 0.03895 0.02787 -0.0358 0.4759 1.0000
8.000 0.9810 0.04173 0.03079 -0.0327 0.4649 1.0000
8.250 1.0124 0.04143 0.03060 -0.0325 0.4610 1.0000
8.500 0.9951 0.04468 0.03397 -0.0292 0.4499 1.0000
8.750 1.0267 0.04435 0.03376 -0.0290 0.4459 1.0000
9.000 0.9980 0.04850 0.03797 -0.0253 0.4343 1.0000
9.250 1.0322 0.04794 0.03757 -0.0251 0.4305 1.0000
9.500 0.9940 0.05327 0.04292 -0.0220 0.4178 1.0000
9.750 1.0296 0.05231 0.04215 -0.0214 0.4145 1.0000
10.000 0.9955 0.05822 0.04810 -0.0199 0.4011 1.0000
10.250 1.0312 0.05660 0.04664 -0.0187 0.3965 1.0000
10.500 1.0180 0.06039 0.05051 -0.0178 0.3843 1.0000
11.000 1.0135 0.06587 0.05618 -0.0163 0.3630 1.0000
11.250 1.0221 0.06735 0.05779 -0.0155 0.3541 1.0000
11.750 1.0386 0.07055 0.06131 -0.0140 0.3376 1.0000
12.250 1.0494 0.07448 0.06552 -0.0128 0.3199 1.0000
12.750 1.0297 0.08267 0.07392 -0.0130 0.2949 1.0000
13.000 1.0384 0.08329 0.07468 -0.0121 0.2815 1.0000
13.250 1.0980 0.07408 0.06568 -0.0081 0.2602 1.0000
13.500 1.0890 0.07764 0.06933 -0.0083 0.2433 1.0000
13.750 1.0816 0.08112 0.07288 -0.0085 0.2256 1.0000
14.000 1.0809 0.08353 0.07535 -0.0085 0.2048 1.0000
14.250 1.0797 0.08620 0.07802 -0.0087 0.1819 1.0000
14.500 1.0797 0.08861 0.08028 -0.0087 0.1560 1.0000
14.750 1.0771 0.09141 0.08276 -0.0087 0.1328 1.0000
15.000 1.0695 0.09541 0.08651 -0.0092 0.1166 1.0000
15.250 1.0618 0.09959 0.09050 -0.0098 0.1040 1.0000
15.500 1.0556 0.10381 0.09469 -0.0106 0.0931 1.0000
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Polar data table (+)
Polar graphs
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