NACA M18 AIRFOIL (m18-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M18 AIRFOIL (m18-il) Reynolds number: 100,000 Max Cl/Cd: 50.37 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m18-il-100000-n5.txt Download as CSV file: xf-m18-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3981 0.11395 0.10920 -0.0205 1.0000 0.0696
-9.500 -0.4032 0.11052 0.10583 -0.0256 1.0000 0.0699
-9.250 -0.4060 0.10664 0.10201 -0.0304 1.0000 0.0701
-9.000 -0.4050 0.10214 0.09758 -0.0336 1.0000 0.0703
-8.750 -0.3839 0.09774 0.09318 -0.0297 1.0000 0.0712
-8.500 -0.3728 0.09426 0.08974 -0.0298 1.0000 0.0720
-8.250 -0.3650 0.09083 0.08635 -0.0316 0.9830 0.0728
-8.000 -0.3519 0.08704 0.08254 -0.0351 0.9416 0.0744
-7.750 -0.3458 0.08360 0.07903 -0.0378 0.9132 0.0766
-7.500 -0.3449 0.08034 0.07568 -0.0400 0.8901 0.0790
-7.250 -0.3535 0.07695 0.07194 -0.0471 0.8687 0.0829
-7.000 -0.3514 0.06700 0.06170 -0.0489 0.8563 0.0589
-6.750 -0.3421 0.06442 0.05913 -0.0476 0.8424 0.0603
-6.250 -0.3294 0.05225 0.04608 -0.0484 0.8192 0.0498
-6.000 -0.3154 0.04987 0.04361 -0.0477 0.8074 0.0503
-5.750 -0.2992 0.04840 0.04206 -0.0468 0.7968 0.0513
-5.500 -0.2828 0.04607 0.03953 -0.0462 0.7863 0.0520
-5.250 -0.2674 0.04233 0.03538 -0.0453 0.7772 0.0516
-4.750 -0.2331 0.03491 0.02673 -0.0425 0.7602 0.0497
-4.500 -0.2125 0.03273 0.02416 -0.0414 0.7521 0.0497
-4.250 -0.1901 0.03074 0.02178 -0.0405 0.7435 0.0498
-4.000 -0.1672 0.02901 0.01974 -0.0397 0.7357 0.0501
-3.750 -0.1429 0.02777 0.01835 -0.0393 0.7272 0.0510
-3.500 -0.1182 0.02684 0.01726 -0.0388 0.7196 0.0524
-3.250 -0.0925 0.02582 0.01601 -0.0384 0.7115 0.0537
-3.000 -0.0662 0.02467 0.01459 -0.0378 0.7041 0.0545
-2.750 -0.0392 0.02360 0.01328 -0.0374 0.6966 0.0552
-2.500 -0.0120 0.02267 0.01213 -0.0371 0.6891 0.0560
-2.250 0.0154 0.02185 0.01113 -0.0368 0.6821 0.0570
-2.000 0.0428 0.02114 0.01028 -0.0365 0.6742 0.0582
-1.750 0.0697 0.02049 0.00951 -0.0361 0.6678 0.0597
-1.500 0.0963 0.02003 0.00911 -0.0359 0.6597 0.0626
-1.250 0.1228 0.01963 0.00864 -0.0355 0.6535 0.0663
-1.000 0.1494 0.01924 0.00817 -0.0352 0.6459 0.0697
-0.750 0.1752 0.01879 0.00773 -0.0346 0.6390 0.0737
-0.500 0.2016 0.01848 0.00739 -0.0342 0.6321 0.0804
-0.250 0.2283 0.01817 0.00709 -0.0339 0.6248 0.0928
0.000 0.2552 0.01785 0.00685 -0.0335 0.6191 0.1242
0.250 0.2820 0.01755 0.00679 -0.0335 0.6115 0.1861
0.750 0.4518 0.01614 0.00728 -0.0556 0.5948 1.0000
1.000 0.4768 0.01622 0.00720 -0.0551 0.5888 1.0000
1.250 0.5020 0.01633 0.00721 -0.0547 0.5823 1.0000
1.500 0.5270 0.01645 0.00724 -0.0543 0.5758 1.0000
1.750 0.5518 0.01655 0.00719 -0.0537 0.5707 1.0000
2.000 0.5766 0.01671 0.00734 -0.0534 0.5635 1.0000
2.250 0.6013 0.01684 0.00738 -0.0529 0.5577 1.0000
2.500 0.6260 0.01699 0.00746 -0.0524 0.5525 1.0000
2.750 0.6505 0.01718 0.00765 -0.0519 0.5462 1.0000
3.000 0.6750 0.01733 0.00772 -0.0513 0.5410 1.0000
3.250 0.6993 0.01752 0.00790 -0.0508 0.5355 1.0000
3.500 0.7233 0.01774 0.00812 -0.0503 0.5296 1.0000
3.750 0.7476 0.01791 0.00824 -0.0497 0.5248 1.0000
4.000 0.7715 0.01814 0.00849 -0.0491 0.5193 1.0000
4.250 0.7951 0.01838 0.00875 -0.0485 0.5134 1.0000
4.500 0.8192 0.01854 0.00886 -0.0479 0.5085 1.0000
4.750 0.8423 0.01881 0.00920 -0.0472 0.5019 1.0000
5.000 0.8657 0.01902 0.00941 -0.0465 0.4958 1.0000
5.250 0.8894 0.01920 0.00956 -0.0458 0.4906 1.0000
5.500 0.9117 0.01952 0.01000 -0.0450 0.4839 1.0000
5.750 0.9352 0.01975 0.01023 -0.0443 0.4788 1.0000
6.000 0.9583 0.02003 0.01054 -0.0436 0.4739 1.0000
6.250 0.9802 0.02040 0.01102 -0.0428 0.4681 1.0000
6.500 1.0034 0.02067 0.01133 -0.0420 0.4631 1.0000
6.750 1.0261 0.02099 0.01170 -0.0413 0.4581 1.0000
7.000 1.0472 0.02140 0.01224 -0.0403 0.4519 1.0000
7.250 1.0701 0.02168 0.01258 -0.0396 0.4469 1.0000
7.500 1.0917 0.02207 0.01306 -0.0387 0.4414 1.0000
7.750 1.1122 0.02246 0.01357 -0.0376 0.4344 1.0000
8.000 1.1359 0.02265 0.01375 -0.0369 0.4286 1.0000
8.250 1.1534 0.02316 0.01448 -0.0355 0.4201 1.0000
8.500 1.1759 0.02338 0.01473 -0.0346 0.4135 1.0000
8.750 1.1928 0.02389 0.01543 -0.0331 0.4050 1.0000
9.000 1.2143 0.02411 0.01569 -0.0320 0.3974 1.0000
9.250 1.2295 0.02465 0.01645 -0.0303 0.3880 1.0000
9.500 1.2474 0.02494 0.01683 -0.0288 0.3784 1.0000
9.750 1.2605 0.02524 0.01722 -0.0266 0.3637 1.0000
10.000 1.2684 0.02570 0.01778 -0.0239 0.3442 1.0000
10.250 1.2740 0.02623 0.01834 -0.0209 0.3220 1.0000
10.500 1.2768 0.02704 0.01916 -0.0178 0.2992 1.0000
10.750 1.2750 0.02803 0.02010 -0.0141 0.2785 1.0000
11.000 1.2708 0.02936 0.02138 -0.0107 0.2592 1.0000
11.250 1.2659 0.03111 0.02308 -0.0080 0.2392 1.0000
11.500 1.2596 0.03328 0.02521 -0.0059 0.2195 1.0000
11.750 1.2517 0.03589 0.02777 -0.0042 0.1992 1.0000
12.000 1.2423 0.03892 0.03076 -0.0030 0.1748 1.0000
12.250 1.2290 0.04255 0.03431 -0.0022 0.1496 1.0000
12.500 1.2128 0.04670 0.03834 -0.0017 0.1307 1.0000
12.750 1.1978 0.05093 0.04250 -0.0014 0.1154 1.0000
13.000 1.1841 0.05517 0.04673 -0.0014 0.1014 1.0000
13.250 1.1721 0.05934 0.05090 -0.0014 0.0864 1.0000
13.500 1.1599 0.06369 0.05523 -0.0017 0.0737 1.0000
13.750 1.1482 0.06817 0.05969 -0.0022 0.0652 1.0000
14.000 1.1370 0.07271 0.06421 -0.0028 0.0592 1.0000
14.250 1.1288 0.07699 0.06854 -0.0034 0.0543 1.0000
14.500 1.1203 0.08138 0.07295 -0.0041 0.0506 1.0000
14.750 1.1129 0.08567 0.07728 -0.0049 0.0476 1.0000
15.000 1.1090 0.08951 0.08123 -0.0056 0.0447 1.0000
15.250 1.1048 0.09344 0.08522 -0.0063 0.0426 1.0000
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Polar data table (+)
Polar graphs
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