NACA M18 (nacam18-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 (nacam18-il) Reynolds number: 100,000 Max Cl/Cd: 50.81 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nacam18-il-100000-n5.txt Download as CSV file: xf-nacam18-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3990 0.11301 0.10827 -0.0212 1.0000 0.0698
-9.250 -0.4033 0.10946 0.10478 -0.0263 1.0000 0.0700
-9.000 -0.4061 0.10551 0.10089 -0.0312 1.0000 0.0702
-8.750 -0.3998 0.10069 0.09614 -0.0325 1.0000 0.0705
-8.500 -0.3816 0.09668 0.09214 -0.0297 1.0000 0.0714
-8.250 -0.3713 0.09323 0.08872 -0.0301 1.0000 0.0722
-8.000 -0.3593 0.08951 0.08500 -0.0329 0.9540 0.0732
-7.750 -0.3489 0.08596 0.08140 -0.0357 0.9235 0.0750
-7.500 -0.3463 0.08279 0.07816 -0.0374 0.8984 0.0770
-7.250 -0.3455 0.07950 0.07478 -0.0397 0.8784 0.0795
-7.000 -0.3529 0.07614 0.07104 -0.0467 0.8593 0.0830
-6.750 -0.3515 0.06596 0.06062 -0.0483 0.8487 0.0596
-6.500 -0.3375 0.06395 0.05863 -0.0466 0.8358 0.0574
-6.000 -0.3253 0.05173 0.04551 -0.0481 0.8152 0.0497
-5.750 -0.3124 0.04830 0.04183 -0.0476 0.8044 0.0500
-5.500 -0.2948 0.04730 0.04085 -0.0468 0.7942 0.0512
-5.250 -0.2783 0.04489 0.03822 -0.0460 0.7850 0.0518
-4.750 -0.2466 0.03675 0.02884 -0.0435 0.7684 0.0497
-4.500 -0.2266 0.03443 0.02618 -0.0425 0.7596 0.0497
-4.250 -0.2055 0.03227 0.02363 -0.0415 0.7520 0.0497
-4.000 -0.1829 0.03034 0.02130 -0.0406 0.7437 0.0498
-3.750 -0.1596 0.02864 0.01928 -0.0398 0.7363 0.0501
-3.500 -0.1351 0.02746 0.01795 -0.0394 0.7286 0.0511
-3.250 -0.1101 0.02656 0.01691 -0.0389 0.7210 0.0525
-3.000 -0.0843 0.02555 0.01567 -0.0384 0.7141 0.0538
-2.750 -0.0577 0.02443 0.01430 -0.0380 0.7066 0.0546
-2.500 -0.0308 0.02341 0.01301 -0.0375 0.7006 0.0553
-2.250 -0.0032 0.02252 0.01195 -0.0373 0.6928 0.0561
-2.000 0.0241 0.02173 0.01097 -0.0370 0.6867 0.0572
-1.750 0.0516 0.02106 0.01018 -0.0367 0.6797 0.0585
-1.500 0.0784 0.02043 0.00950 -0.0364 0.6730 0.0602
-1.250 0.1048 0.02000 0.00907 -0.0361 0.6671 0.0633
-1.000 0.1316 0.01962 0.00868 -0.0359 0.6599 0.0672
-0.750 0.1579 0.01921 0.00815 -0.0354 0.6541 0.0705
-0.500 0.1839 0.01881 0.00780 -0.0350 0.6474 0.0751
-0.250 0.2104 0.01852 0.00744 -0.0346 0.6409 0.0829
0.000 0.2372 0.01819 0.00713 -0.0342 0.6356 0.0991
0.250 0.2641 0.01789 0.00705 -0.0342 0.6283 0.1393
0.500 0.2906 0.01753 0.00690 -0.0340 0.6225 0.2163
1.000 0.4602 0.01625 0.00740 -0.0561 0.6069 1.0000
1.250 0.4852 0.01633 0.00735 -0.0557 0.6011 1.0000
1.500 0.5103 0.01644 0.00738 -0.0554 0.5940 1.0000
1.750 0.5351 0.01653 0.00733 -0.0549 0.5884 1.0000
2.000 0.5600 0.01667 0.00742 -0.0546 0.5815 1.0000
2.250 0.5847 0.01678 0.00746 -0.0541 0.5751 1.0000
2.500 0.6093 0.01689 0.00747 -0.0536 0.5696 1.0000
2.750 0.6337 0.01707 0.00765 -0.0533 0.5622 1.0000
3.000 0.6582 0.01718 0.00768 -0.0528 0.5565 1.0000
3.250 0.6824 0.01736 0.00785 -0.0523 0.5497 1.0000
3.500 0.7065 0.01752 0.00799 -0.0518 0.5432 1.0000
3.750 0.7308 0.01765 0.00806 -0.0513 0.5377 1.0000
4.000 0.7544 0.01788 0.00833 -0.0508 0.5301 1.0000
4.250 0.7785 0.01802 0.00842 -0.0503 0.5244 1.0000
4.500 0.8019 0.01825 0.00869 -0.0497 0.5174 1.0000
4.750 0.8255 0.01844 0.00888 -0.0492 0.5109 1.0000
5.000 0.8491 0.01863 0.00907 -0.0486 0.5050 1.0000
5.250 0.8720 0.01889 0.00939 -0.0480 0.4977 1.0000
5.500 0.8958 0.01905 0.00952 -0.0474 0.4923 1.0000
5.750 0.9181 0.01937 0.00994 -0.0468 0.4850 1.0000
6.000 0.9412 0.01959 0.01018 -0.0461 0.4789 1.0000
6.250 0.9639 0.01986 0.01049 -0.0455 0.4727 1.0000
6.500 0.9860 0.02018 0.01090 -0.0448 0.4658 1.0000
6.750 1.0096 0.02039 0.01110 -0.0442 0.4607 1.0000
7.000 1.0304 0.02081 0.01166 -0.0434 0.4535 1.0000
7.250 1.0529 0.02109 0.01198 -0.0427 0.4474 1.0000
7.500 1.0744 0.02145 0.01243 -0.0420 0.4410 1.0000
7.750 1.0954 0.02181 0.01289 -0.0411 0.4338 1.0000
8.000 1.1177 0.02210 0.01321 -0.0404 0.4276 1.0000
8.250 1.1369 0.02254 0.01379 -0.0394 0.4192 1.0000
8.500 1.1584 0.02280 0.01410 -0.0385 0.4119 1.0000
8.750 1.1765 0.02325 0.01471 -0.0373 0.4030 1.0000
9.000 1.1967 0.02359 0.01510 -0.0363 0.3954 1.0000
9.250 1.2140 0.02404 0.01571 -0.0350 0.3862 1.0000
9.500 1.2317 0.02446 0.01624 -0.0338 0.3775 1.0000
9.750 1.2486 0.02476 0.01658 -0.0323 0.3662 1.0000
10.000 1.2594 0.02520 0.01709 -0.0300 0.3499 1.0000
10.250 1.2661 0.02577 0.01774 -0.0273 0.3297 1.0000
10.500 1.2703 0.02647 0.01843 -0.0244 0.3087 1.0000
10.750 1.2722 0.02737 0.01932 -0.0213 0.2892 1.0000
11.000 1.2702 0.02846 0.02042 -0.0178 0.2717 1.0000
11.250 1.2677 0.02986 0.02182 -0.0150 0.2535 1.0000
11.500 1.2641 0.03161 0.02356 -0.0127 0.2342 1.0000
11.750 1.2588 0.03378 0.02569 -0.0108 0.2133 1.0000
12.000 1.2511 0.03642 0.02828 -0.0093 0.1886 1.0000
12.250 1.2395 0.03966 0.03141 -0.0082 0.1608 1.0000
12.500 1.2244 0.04351 0.03512 -0.0073 0.1374 1.0000
12.750 1.2091 0.04760 0.03912 -0.0068 0.1202 1.0000
13.000 1.1950 0.05176 0.04322 -0.0065 0.1056 1.0000
13.250 1.1824 0.05590 0.04738 -0.0064 0.0907 1.0000
13.500 1.1701 0.06014 0.05162 -0.0065 0.0767 1.0000
13.750 1.1571 0.06466 0.05612 -0.0068 0.0674 1.0000
14.000 1.1454 0.06919 0.06066 -0.0074 0.0607 1.0000
14.250 1.1348 0.07372 0.06521 -0.0080 0.0559 1.0000
14.500 1.1258 0.07817 0.06971 -0.0087 0.0518 1.0000
14.750 1.1155 0.08286 0.07442 -0.0095 0.0490 1.0000
15.000 1.1109 0.08682 0.07848 -0.0102 0.0459 1.0000
15.250 1.1060 0.09085 0.08260 -0.0110 0.0435 1.0000
15.500 1.1009 0.09492 0.08672 -0.0118 0.0417 1.0000
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Polar data table (+)
Polar graphs
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