NACA M18 (nacam18-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 500,000 Max Cl/Cd: 102.61 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nacam18-il-500000.txt Download as CSV file: xf-nacam18-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4115 0.10518 0.10307 -0.0101 1.0000 0.0293
-9.250 -0.4057 0.10195 0.09981 -0.0118 0.9339 0.0298
-9.000 -0.4065 0.09913 0.09687 -0.0118 0.8950 0.0304
-8.750 -0.3344 0.08140 0.07893 -0.0288 0.8164 0.0334
-8.500 -0.3300 0.07819 0.07567 -0.0279 0.8031 0.0337
-8.250 -0.3257 0.07524 0.07266 -0.0279 0.7908 0.0339
-8.000 -0.4379 0.07668 0.07405 -0.0326 0.8179 0.0334
-7.750 -0.4327 0.07379 0.07109 -0.0321 0.8042 0.0337
-7.500 -0.4245 0.07121 0.06843 -0.0322 0.7910 0.0340
-7.250 -0.4151 0.06858 0.06571 -0.0326 0.7785 0.0343
-7.000 -0.4046 0.06578 0.06283 -0.0333 0.7664 0.0347
-6.750 -0.3934 0.06281 0.05976 -0.0342 0.7556 0.0353
-6.500 -0.3814 0.05955 0.05636 -0.0353 0.7456 0.0361
-6.250 -0.3415 0.03665 0.03319 -0.0409 0.7212 0.0399
-6.000 -0.3280 0.03440 0.03086 -0.0403 0.7132 0.0403
-5.750 -0.3122 0.03247 0.02887 -0.0398 0.7053 0.0408
-5.500 -0.2962 0.03036 0.02666 -0.0393 0.6982 0.0415
-5.250 -0.2799 0.02787 0.02405 -0.0389 0.6918 0.0427
-5.000 -0.2741 0.02083 0.01634 -0.0372 0.6874 0.0475
-4.750 -0.2546 0.01923 0.01468 -0.0367 0.6811 0.0480
-4.500 -0.2341 0.01786 0.01324 -0.0362 0.6747 0.0487
-4.250 -0.2131 0.01651 0.01180 -0.0357 0.6686 0.0497
-4.000 -0.1922 0.01506 0.01016 -0.0349 0.6632 0.0516
-3.750 -0.1746 0.01235 0.00694 -0.0333 0.6584 0.0569
-3.500 -0.1662 0.01918 0.01230 -0.0292 0.6622 0.0396
-3.250 -0.1400 0.01751 0.01048 -0.0289 0.6562 0.0390
-3.000 -0.1132 0.01634 0.00912 -0.0286 0.6504 0.0388
-2.750 -0.0858 0.01549 0.00809 -0.0283 0.6451 0.0389
-2.500 -0.0579 0.01487 0.00737 -0.0282 0.6394 0.0391
-2.250 -0.0302 0.01419 0.00657 -0.0280 0.6337 0.0396
-2.000 -0.0029 0.01336 0.00565 -0.0278 0.6285 0.0401
-1.750 0.0245 0.01275 0.00503 -0.0276 0.6230 0.0406
-1.500 0.0517 0.01233 0.00458 -0.0274 0.6177 0.0414
-1.250 0.0788 0.01203 0.00424 -0.0272 0.6125 0.0422
-1.000 0.1063 0.01172 0.00395 -0.0271 0.6068 0.0431
-0.750 0.1335 0.01147 0.00367 -0.0269 0.6014 0.0442
-0.500 0.1608 0.01130 0.00344 -0.0267 0.5963 0.0454
-0.250 0.1884 0.01109 0.00324 -0.0266 0.5906 0.0470
0.000 0.2154 0.01083 0.00299 -0.0264 0.5850 0.0502
0.250 0.2429 0.01073 0.00285 -0.0263 0.5798 0.0537
0.500 0.2705 0.01054 0.00272 -0.0263 0.5739 0.0616
0.750 0.2970 0.01025 0.00261 -0.0260 0.5682 0.1129
1.000 0.3232 0.01000 0.00259 -0.0258 0.5628 0.1922
1.250 0.3417 0.00889 0.00251 -0.0245 0.5572 0.5324
1.500 0.3729 0.00804 0.00290 -0.0244 0.5513 0.9483
1.750 0.4189 0.00840 0.00320 -0.0279 0.5447 0.9713
2.000 0.4794 0.00874 0.00346 -0.0348 0.5370 0.9831
2.250 0.5545 0.00903 0.00365 -0.0450 0.5289 0.9941
2.500 0.6134 0.00905 0.00360 -0.0519 0.5205 1.0000
2.750 0.6397 0.00908 0.00358 -0.0519 0.5141 1.0000
3.000 0.6660 0.00909 0.00357 -0.0518 0.5072 1.0000
3.500 0.7184 0.00917 0.00359 -0.0516 0.4944 1.0000
3.750 0.7445 0.00923 0.00361 -0.0515 0.4880 1.0000
4.000 0.7706 0.00930 0.00366 -0.0514 0.4818 1.0000
4.250 0.7966 0.00935 0.00370 -0.0514 0.4755 1.0000
4.750 0.8484 0.00951 0.00384 -0.0512 0.4635 1.0000
5.000 0.8740 0.00961 0.00391 -0.0510 0.4567 1.0000
5.250 0.8996 0.00971 0.00400 -0.0509 0.4498 1.0000
5.500 0.9251 0.00980 0.00410 -0.0507 0.4429 1.0000
5.750 0.9501 0.00995 0.00422 -0.0505 0.4368 1.0000
6.000 0.9752 0.01004 0.00435 -0.0503 0.4301 1.0000
6.250 0.9996 0.01021 0.00448 -0.0500 0.4236 1.0000
6.500 1.0244 0.01031 0.00464 -0.0497 0.4169 1.0000
6.750 1.0486 0.01047 0.00480 -0.0494 0.4100 1.0000
7.000 1.0728 0.01062 0.00497 -0.0490 0.4030 1.0000
7.250 1.0965 0.01079 0.00514 -0.0486 0.3940 1.0000
7.500 1.1202 0.01094 0.00532 -0.0482 0.3842 1.0000
7.750 1.1431 0.01114 0.00550 -0.0477 0.3718 1.0000
8.000 1.1655 0.01137 0.00570 -0.0471 0.3583 1.0000
8.250 1.1874 0.01163 0.00594 -0.0464 0.3453 1.0000
8.500 1.2093 0.01188 0.00619 -0.0458 0.3316 1.0000
8.750 1.2304 0.01218 0.00647 -0.0450 0.3166 1.0000
9.000 1.2503 0.01255 0.00681 -0.0440 0.2993 1.0000
9.250 1.2694 0.01297 0.00717 -0.0430 0.2799 1.0000
9.500 1.2860 0.01352 0.00763 -0.0415 0.2568 1.0000
9.750 1.3006 0.01417 0.00817 -0.0398 0.2306 1.0000
10.000 1.3102 0.01508 0.00889 -0.0374 0.1960 1.0000
10.250 1.3079 0.01657 0.01002 -0.0332 0.1382 1.0000
10.500 1.3020 0.01805 0.01126 -0.0284 0.1030 1.0000
10.750 1.2883 0.01950 0.01252 -0.0224 0.0691 1.0000
11.000 1.2761 0.02134 0.01421 -0.0177 0.0469 1.0000
11.250 1.2747 0.02308 0.01593 -0.0153 0.0373 1.0000
11.500 1.2770 0.02482 0.01769 -0.0137 0.0328 1.0000
11.750 1.2813 0.02655 0.01947 -0.0126 0.0301 1.0000
12.000 1.2820 0.02875 0.02172 -0.0115 0.0281 1.0000
12.250 1.2882 0.03054 0.02361 -0.0109 0.0268 1.0000
12.500 1.2923 0.03260 0.02574 -0.0104 0.0256 1.0000
12.750 1.2936 0.03499 0.02819 -0.0099 0.0245 1.0000
13.000 1.2894 0.03800 0.03128 -0.0095 0.0236 1.0000
13.250 1.2892 0.04066 0.03402 -0.0092 0.0230 1.0000
13.500 1.2911 0.04312 0.03658 -0.0090 0.0223 1.0000
13.750 1.2911 0.04582 0.03937 -0.0088 0.0217 1.0000
14.000 1.2898 0.04867 0.04230 -0.0087 0.0212 1.0000
14.250 1.2878 0.05169 0.04538 -0.0087 0.0207 1.0000
14.500 1.2849 0.05490 0.04867 -0.0088 0.0203 1.0000
14.750 1.2799 0.05841 0.05224 -0.0090 0.0199 1.0000
15.000 1.2724 0.06226 0.05616 -0.0092 0.0195 1.0000
15.250 1.2662 0.06598 0.05995 -0.0094 0.0191 1.0000
15.500 1.2671 0.06894 0.06300 -0.0097 0.0189 1.0000
15.750 1.2674 0.07202 0.06616 -0.0101 0.0185 1.0000
16.000 1.2679 0.07508 0.06931 -0.0106 0.0182 1.0000
16.250 1.2683 0.07820 0.07251 -0.0111 0.0178 1.0000
16.500 1.2686 0.08132 0.07569 -0.0116 0.0174 1.0000
16.750 1.2692 0.08442 0.07886 -0.0122 0.0170 1.0000
17.000 1.2696 0.08758 0.08206 -0.0128 0.0167 1.0000
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