NACA M18 (nacam18-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 200,000 Max Cl/Cd: 72.34 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam18-il-200000-n5.txt Download as CSV file: xf-nacam18-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4035 0.09381 0.09031 -0.0241 0.8726 0.0424
-8.500 -0.3943 0.09181 0.08825 -0.0225 0.8541 0.0431
-8.250 -0.3893 0.08913 0.08551 -0.0229 0.8376 0.0439
-8.000 -0.3872 0.08585 0.08218 -0.0247 0.8223 0.0448
-7.750 -0.3883 0.08206 0.07833 -0.0277 0.8082 0.0455
-7.500 -0.3897 0.07837 0.07455 -0.0298 0.7957 0.0459
-7.250 -0.3869 0.07433 0.07042 -0.0323 0.7843 0.0463
-7.000 -0.3822 0.07014 0.06611 -0.0346 0.7734 0.0461
-6.000 -0.3676 0.04019 0.03456 -0.0401 0.7408 0.0346
-5.750 -0.3545 0.03630 0.03026 -0.0390 0.7329 0.0345
-5.500 -0.3392 0.03278 0.02629 -0.0378 0.7245 0.0346
-5.250 -0.3220 0.02991 0.02297 -0.0365 0.7171 0.0349
-5.000 -0.3007 0.02825 0.02112 -0.0359 0.7087 0.0355
-4.500 -0.2549 0.02526 0.01760 -0.0345 0.6940 0.0363
-4.250 -0.2312 0.02362 0.01560 -0.0337 0.6872 0.0365
-4.000 -0.2061 0.02229 0.01399 -0.0332 0.6805 0.0367
-3.750 -0.1802 0.02118 0.01261 -0.0327 0.6737 0.0370
-3.500 -0.1539 0.02023 0.01143 -0.0323 0.6678 0.0374
-3.250 -0.1269 0.01937 0.01040 -0.0321 0.6611 0.0379
-3.000 -0.0998 0.01863 0.00947 -0.0318 0.6551 0.0384
-2.750 -0.0725 0.01796 0.00866 -0.0316 0.6492 0.0390
-2.500 -0.0450 0.01742 0.00802 -0.0314 0.6430 0.0400
-2.250 -0.0177 0.01696 0.00742 -0.0312 0.6375 0.0410
-2.000 0.0098 0.01651 0.00689 -0.0310 0.6315 0.0417
-1.750 0.0366 0.01593 0.00630 -0.0308 0.6256 0.0424
-1.500 0.0632 0.01552 0.00584 -0.0305 0.6206 0.0433
-1.250 0.0901 0.01518 0.00551 -0.0303 0.6146 0.0443
-1.000 0.1170 0.01489 0.00520 -0.0301 0.6087 0.0456
-0.750 0.1437 0.01466 0.00490 -0.0298 0.6038 0.0471
-0.500 0.1708 0.01444 0.00467 -0.0297 0.5979 0.0490
-0.250 0.1975 0.01423 0.00447 -0.0294 0.5920 0.0522
0.250 0.2513 0.01388 0.00416 -0.0291 0.5809 0.0667
0.500 0.2778 0.01369 0.00403 -0.0288 0.5752 0.0881
0.750 0.3040 0.01351 0.00394 -0.0286 0.5702 0.1268
1.000 0.3303 0.01331 0.00392 -0.0284 0.5638 0.1774
1.250 0.3522 0.01269 0.00387 -0.0276 0.5583 0.3548
1.500 0.4314 0.01185 0.00465 -0.0371 0.5512 0.9682
1.750 0.4954 0.01209 0.00479 -0.0447 0.5434 0.9875
2.000 0.5585 0.01218 0.00476 -0.0524 0.5365 1.0000
2.250 0.5844 0.01222 0.00475 -0.0523 0.5298 1.0000
2.500 0.6101 0.01227 0.00472 -0.0520 0.5240 1.0000
2.750 0.6359 0.01232 0.00475 -0.0519 0.5175 1.0000
3.000 0.6615 0.01238 0.00477 -0.0516 0.5109 1.0000
3.250 0.6869 0.01246 0.00479 -0.0514 0.5049 1.0000
3.500 0.7122 0.01254 0.00486 -0.0511 0.4979 1.0000
3.750 0.7372 0.01264 0.00489 -0.0508 0.4919 1.0000
4.000 0.7623 0.01273 0.00500 -0.0505 0.4849 1.0000
4.250 0.7871 0.01285 0.00509 -0.0502 0.4785 1.0000
4.500 0.8119 0.01297 0.00520 -0.0498 0.4723 1.0000
4.750 0.8365 0.01310 0.00533 -0.0495 0.4657 1.0000
5.000 0.8608 0.01325 0.00545 -0.0491 0.4600 1.0000
5.250 0.8853 0.01340 0.00564 -0.0487 0.4533 1.0000
5.500 0.9095 0.01356 0.00580 -0.0483 0.4475 1.0000
5.750 0.9335 0.01374 0.00600 -0.0479 0.4419 1.0000
6.000 0.9574 0.01392 0.00622 -0.0475 0.4355 1.0000
6.250 0.9809 0.01413 0.00640 -0.0469 0.4294 1.0000
6.500 1.0044 0.01432 0.00667 -0.0465 0.4218 1.0000
6.750 1.0274 0.01454 0.00688 -0.0459 0.4150 1.0000
7.000 1.0505 0.01476 0.00716 -0.0453 0.4082 1.0000
7.250 1.0732 0.01500 0.00745 -0.0447 0.4015 1.0000
7.500 1.0956 0.01525 0.00773 -0.0441 0.3944 1.0000
7.750 1.1175 0.01550 0.00803 -0.0434 0.3859 1.0000
8.000 1.1393 0.01577 0.00835 -0.0427 0.3786 1.0000
8.250 1.1611 0.01605 0.00871 -0.0420 0.3718 1.0000
8.500 1.1820 0.01635 0.00905 -0.0411 0.3639 1.0000
8.750 1.2010 0.01667 0.00939 -0.0400 0.3500 1.0000
9.000 1.2181 0.01705 0.00975 -0.0386 0.3290 1.0000
9.250 1.2328 0.01756 0.01019 -0.0369 0.3064 1.0000
9.500 1.2477 0.01809 0.01070 -0.0352 0.2862 1.0000
9.750 1.2602 0.01872 0.01128 -0.0332 0.2651 1.0000
10.000 1.2697 0.01948 0.01196 -0.0308 0.2433 1.0000
10.250 1.2768 0.02033 0.01274 -0.0282 0.2198 1.0000
10.500 1.2788 0.02139 0.01370 -0.0249 0.1930 1.0000
10.750 1.2719 0.02271 0.01488 -0.0204 0.1629 1.0000
11.000 1.2619 0.02461 0.01659 -0.0166 0.1336 1.0000
11.250 1.2560 0.02668 0.01856 -0.0141 0.1130 1.0000
11.500 1.2528 0.02884 0.02067 -0.0123 0.0943 1.0000
11.750 1.2473 0.03139 0.02314 -0.0108 0.0707 1.0000
12.000 1.2408 0.03423 0.02589 -0.0096 0.0554 1.0000
12.250 1.2368 0.03698 0.02863 -0.0088 0.0465 1.0000
12.500 1.2333 0.03980 0.03148 -0.0082 0.0405 1.0000
12.750 1.2323 0.04245 0.03421 -0.0077 0.0363 1.0000
13.000 1.2288 0.04542 0.03723 -0.0074 0.0334 1.0000
13.250 1.2282 0.04814 0.04005 -0.0072 0.0310 1.0000
13.500 1.2255 0.05112 0.04311 -0.0070 0.0292 1.0000
13.750 1.2209 0.05441 0.04647 -0.0070 0.0278 1.0000
14.000 1.2188 0.05752 0.04968 -0.0071 0.0267 1.0000
14.250 1.2167 0.06072 0.05299 -0.0073 0.0257 1.0000
14.500 1.2141 0.06407 0.05644 -0.0077 0.0247 1.0000
14.750 1.2108 0.06756 0.06004 -0.0081 0.0239 1.0000
15.000 1.2064 0.07128 0.06383 -0.0087 0.0232 1.0000
15.250 1.2004 0.07528 0.06790 -0.0093 0.0226 1.0000
15.500 1.1990 0.07871 0.07144 -0.0099 0.0219 1.0000
15.750 1.1970 0.08225 0.07509 -0.0106 0.0212 1.0000
16.000 1.1949 0.08586 0.07880 -0.0114 0.0206 1.0000
16.250 1.1929 0.08947 0.08250 -0.0122 0.0200 1.0000
16.500 1.1908 0.09313 0.08623 -0.0130 0.0195 1.0000
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Polar data table (+)
Polar graphs
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