NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 200,000 Max Cl/Cd: 72.25 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m18-il-200000-n5.txt Download as CSV file: xf-m18-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3897 0.08994 0.08635 -0.0231 0.8465 0.0437
-8.250 -0.3872 0.08684 0.08319 -0.0245 0.8285 0.0446
-8.000 -0.3879 0.08311 0.07940 -0.0273 0.8124 0.0453
-7.500 -0.3994 0.07112 0.06713 -0.0362 0.7873 0.0409
-7.250 -0.3912 0.06835 0.06428 -0.0359 0.7755 0.0395
-7.000 -0.3863 0.06364 0.05941 -0.0374 0.7658 0.0377
-6.750 -0.3820 0.05724 0.05275 -0.0395 0.7565 0.0363
-6.250 -0.3725 0.04082 0.03525 -0.0399 0.7416 0.0346
-6.000 -0.3597 0.03695 0.03097 -0.0388 0.7338 0.0346
-5.750 -0.3448 0.03336 0.02694 -0.0376 0.7252 0.0346
-5.250 -0.3069 0.02876 0.02173 -0.0357 0.7093 0.0354
-5.000 -0.2846 0.02743 0.02017 -0.0351 0.7018 0.0360
-4.750 -0.2614 0.02588 0.01836 -0.0345 0.6938 0.0364
-4.500 -0.2382 0.02409 0.01618 -0.0336 0.6869 0.0365
-4.250 -0.2134 0.02266 0.01445 -0.0331 0.6800 0.0368
-4.000 -0.1878 0.02148 0.01300 -0.0326 0.6730 0.0371
-3.750 -0.1616 0.02048 0.01175 -0.0322 0.6665 0.0375
-3.500 -0.1348 0.01958 0.01066 -0.0320 0.6593 0.0379
-3.250 -0.1079 0.01881 0.00969 -0.0317 0.6530 0.0384
-3.000 -0.0804 0.01811 0.00885 -0.0315 0.6462 0.0389
-2.750 -0.0531 0.01756 0.00817 -0.0313 0.6398 0.0399
-2.500 -0.0257 0.01708 0.00756 -0.0311 0.6340 0.0410
-2.250 0.0018 0.01661 0.00700 -0.0310 0.6271 0.0416
-2.000 0.0285 0.01604 0.00637 -0.0307 0.6210 0.0423
-1.750 0.0553 0.01558 0.00592 -0.0305 0.6144 0.0432
-1.500 0.0821 0.01523 0.00555 -0.0303 0.6077 0.0441
-1.250 0.1088 0.01495 0.00522 -0.0300 0.6021 0.0453
-1.000 0.1358 0.01468 0.00495 -0.0298 0.5954 0.0468
-0.750 0.1626 0.01447 0.00467 -0.0295 0.5893 0.0486
-0.500 0.1894 0.01425 0.00445 -0.0293 0.5831 0.0514
-0.250 0.2163 0.01408 0.00429 -0.0291 0.5761 0.0562
0.000 0.2429 0.01391 0.00411 -0.0288 0.5702 0.0634
0.250 0.2697 0.01371 0.00399 -0.0286 0.5630 0.0803
0.500 0.2959 0.01352 0.00389 -0.0283 0.5570 0.1139
0.750 0.3221 0.01334 0.00384 -0.0281 0.5510 0.1603
1.000 0.3467 0.01300 0.00382 -0.0276 0.5445 0.2565
1.500 0.4746 0.01205 0.00472 -0.0416 0.5291 0.9839
1.750 0.5462 0.01218 0.00469 -0.0510 0.5219 0.9988
2.000 0.5764 0.01223 0.00470 -0.0516 0.5156 1.0000
2.250 0.6022 0.01229 0.00468 -0.0513 0.5099 1.0000
2.500 0.6279 0.01236 0.00470 -0.0511 0.5044 1.0000
2.750 0.6536 0.01243 0.00474 -0.0508 0.4985 1.0000
3.000 0.6791 0.01253 0.00477 -0.0504 0.4935 1.0000
3.250 0.7044 0.01263 0.00484 -0.0501 0.4884 1.0000
3.500 0.7296 0.01273 0.00493 -0.0497 0.4828 1.0000
3.750 0.7545 0.01285 0.00499 -0.0493 0.4774 1.0000
4.000 0.7794 0.01296 0.00511 -0.0488 0.4705 1.0000
4.250 0.8040 0.01309 0.00520 -0.0483 0.4638 1.0000
4.500 0.8285 0.01324 0.00532 -0.0479 0.4585 1.0000
4.750 0.8532 0.01339 0.00550 -0.0474 0.4535 1.0000
5.000 0.8777 0.01355 0.00567 -0.0469 0.4490 1.0000
5.250 0.9019 0.01374 0.00582 -0.0464 0.4449 1.0000
5.500 0.9262 0.01391 0.00606 -0.0459 0.4400 1.0000
5.750 0.9502 0.01409 0.00628 -0.0453 0.4350 1.0000
6.000 0.9740 0.01429 0.00647 -0.0447 0.4305 1.0000
6.250 0.9977 0.01450 0.00673 -0.0441 0.4254 1.0000
6.500 1.0212 0.01469 0.00699 -0.0434 0.4197 1.0000
6.750 1.0444 0.01492 0.00722 -0.0428 0.4146 1.0000
7.000 1.0675 0.01514 0.00751 -0.0421 0.4091 1.0000
7.250 1.0903 0.01536 0.00781 -0.0413 0.4026 1.0000
7.500 1.1127 0.01561 0.00805 -0.0405 0.3967 1.0000
7.750 1.1351 0.01583 0.00841 -0.0397 0.3900 1.0000
8.000 1.1573 0.01609 0.00874 -0.0389 0.3843 1.0000
8.250 1.1791 0.01636 0.00908 -0.0380 0.3781 1.0000
8.500 1.1993 0.01660 0.00936 -0.0368 0.3667 1.0000
8.750 1.2175 0.01687 0.00965 -0.0354 0.3483 1.0000
9.000 1.2342 0.01722 0.01000 -0.0337 0.3242 1.0000
9.250 1.2494 0.01769 0.01042 -0.0319 0.2993 1.0000
9.500 1.2615 0.01833 0.01096 -0.0297 0.2740 1.0000
9.750 1.2699 0.01915 0.01166 -0.0270 0.2477 1.0000
10.000 1.2764 0.02006 0.01247 -0.0241 0.2240 1.0000
10.250 1.2788 0.02112 0.01345 -0.0207 0.2008 1.0000
10.500 1.2764 0.02227 0.01451 -0.0167 0.1741 1.0000
10.750 1.2672 0.02394 0.01601 -0.0125 0.1435 1.0000
11.000 1.2592 0.02601 0.01795 -0.0095 0.1205 1.0000
11.250 1.2548 0.02819 0.02006 -0.0074 0.1032 1.0000
11.500 1.2518 0.03048 0.02231 -0.0058 0.0819 1.0000
11.750 1.2441 0.03336 0.02508 -0.0045 0.0617 1.0000
12.000 1.2386 0.03622 0.02790 -0.0035 0.0506 1.0000
12.250 1.2355 0.03899 0.03069 -0.0029 0.0436 1.0000
12.500 1.2325 0.04183 0.03359 -0.0023 0.0387 1.0000
12.750 1.2300 0.04469 0.03651 -0.0019 0.0351 1.0000
13.000 1.2272 0.04764 0.03954 -0.0016 0.0325 1.0000
13.250 1.2254 0.05052 0.04251 -0.0014 0.0304 1.0000
13.500 1.2221 0.05364 0.04569 -0.0013 0.0287 1.0000
13.750 1.2172 0.05706 0.04918 -0.0014 0.0275 1.0000
14.000 1.2157 0.06017 0.05241 -0.0015 0.0264 1.0000
14.250 1.2135 0.06346 0.05581 -0.0018 0.0254 1.0000
14.500 1.2110 0.06685 0.05930 -0.0022 0.0245 1.0000
14.750 1.2077 0.07039 0.06293 -0.0026 0.0237 1.0000
15.000 1.2031 0.07418 0.06679 -0.0032 0.0230 1.0000
15.250 1.1987 0.07800 0.07069 -0.0039 0.0223 1.0000
15.500 1.1973 0.08143 0.07423 -0.0045 0.0217 1.0000
15.750 1.1957 0.08495 0.07785 -0.0051 0.0210 1.0000
16.000 1.1941 0.08848 0.08148 -0.0059 0.0204 1.0000
16.250 1.1923 0.09208 0.08516 -0.0066 0.0198 1.0000
16.500 1.1905 0.09566 0.08881 -0.0074 0.0194 1.0000
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Polar data table (+)
Polar graphs
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