NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M26 AIRFOIL (m26-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.71 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m26-il-1000000-n5.txt Download as CSV file: xf-m26-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA M26 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3094 0.10918 0.10604 0.0138 0.4967 0.0040
-8.250 -0.3036 0.10565 0.10251 0.0120 0.4957 0.0040
-8.000 -0.2988 0.10177 0.09865 0.0099 0.4947 0.0042
-7.750 -0.2926 0.09863 0.09551 0.0077 0.4938 0.0044
-7.500 -0.2849 0.09617 0.09304 0.0058 0.4928 0.0045
-7.250 -0.2725 0.09344 0.09031 0.0032 0.4917 0.0046
-7.000 -0.2597 0.09017 0.08703 0.0003 0.4908 0.0047
-6.750 -0.2454 0.08681 0.08365 -0.0029 0.4898 0.0048
-6.500 -0.2296 0.08345 0.08026 -0.0060 0.4888 0.0049
-6.250 -0.2124 0.07995 0.07674 -0.0093 0.4878 0.0052
-6.000 -0.1938 0.07609 0.07284 -0.0129 0.4868 0.0055
-5.750 -0.1734 0.07088 0.06758 -0.0175 0.4860 0.0061
-5.500 -0.1516 0.06777 0.06444 -0.0204 0.4854 0.0064
-5.250 -0.1291 0.06554 0.06218 -0.0227 0.4846 0.0067
-5.000 -0.1056 0.06294 0.05953 -0.0252 0.4839 0.0071
-4.750 -0.0805 0.05941 0.05595 -0.0282 0.4830 0.0077
-4.500 -0.0526 0.05440 0.05083 -0.0320 0.4821 0.0086
-4.250 -0.0273 0.05252 0.04890 -0.0337 0.4810 0.0089
-4.000 -0.0016 0.05067 0.04701 -0.0353 0.4799 0.0094
-3.750 0.0256 0.04812 0.04438 -0.0373 0.4788 0.0103
-3.500 0.0563 0.04371 0.03983 -0.0398 0.4780 0.0115
-3.250 0.0827 0.04226 0.03832 -0.0410 0.4770 0.0118
-3.000 0.1096 0.04080 0.03679 -0.0421 0.4760 0.0124
-2.750 0.1378 0.03874 0.03465 -0.0433 0.4750 0.0134
-2.500 0.1708 0.03462 0.03032 -0.0447 0.4741 0.0150
-2.250 0.1971 0.03369 0.02934 -0.0454 0.4730 0.0153
-2.000 0.2241 0.03264 0.02821 -0.0461 0.4716 0.0158
-1.750 0.2524 0.03110 0.02660 -0.0468 0.4708 0.0165
-1.500 0.2815 0.02931 0.02470 -0.0474 0.4701 0.0172
-1.250 0.3113 0.02732 0.02258 -0.0478 0.4693 0.0178
-1.000 0.3436 0.02454 0.01959 -0.0479 0.4686 0.0196
-0.750 0.3706 0.02377 0.01877 -0.0483 0.4677 0.0199
-0.500 0.3985 0.02278 0.01772 -0.0487 0.4666 0.0203
-0.250 0.4269 0.02170 0.01655 -0.0490 0.4655 0.0207
0.000 0.4560 0.02035 0.01508 -0.0491 0.4641 0.0208
0.250 0.4849 0.01918 0.01379 -0.0492 0.4624 0.0212
0.500 0.5141 0.01775 0.01219 -0.0492 0.4603 0.0212
0.750 0.5435 0.01607 0.01030 -0.0490 0.4583 0.0212
1.000 0.5725 0.01459 0.00863 -0.0488 0.4566 0.0220
1.250 0.6013 0.01309 0.00694 -0.0487 0.4557 0.0230
1.500 0.6299 0.01221 0.00591 -0.0487 0.4545 0.0233
1.750 0.6584 0.01162 0.00522 -0.0489 0.4533 0.0234
2.000 0.6870 0.01119 0.00472 -0.0491 0.4520 0.0236
2.250 0.7155 0.01094 0.00443 -0.0494 0.4504 0.0240
2.500 0.7438 0.01056 0.00398 -0.0496 0.4488 0.0240
2.750 0.7719 0.01024 0.00362 -0.0498 0.4472 0.0240
3.000 0.7998 0.00999 0.00334 -0.0499 0.4458 0.0240
3.250 0.8276 0.00982 0.00314 -0.0501 0.4442 0.0241
3.500 0.8554 0.00970 0.00301 -0.0503 0.4423 0.0243
3.750 0.8834 0.00961 0.00293 -0.0506 0.4409 0.0246
4.000 0.9116 0.00955 0.00291 -0.0509 0.4394 0.0249
4.250 0.9388 0.00934 0.00270 -0.0509 0.4378 0.0267
4.500 0.9670 0.00930 0.00268 -0.0513 0.4351 0.0277
4.750 0.9951 0.00931 0.00266 -0.0516 0.4282 0.0284
5.000 1.0233 0.00930 0.00267 -0.0520 0.4191 0.0290
5.250 1.0513 0.00936 0.00271 -0.0524 0.4089 0.0300
5.500 1.0791 0.00949 0.00279 -0.0528 0.3921 0.0310
5.750 1.1059 0.00987 0.00302 -0.0533 0.3614 0.0313
6.000 1.1306 0.01074 0.00360 -0.0538 0.3097 0.0317
6.250 1.1544 0.01168 0.00427 -0.0542 0.2602 0.0324
6.500 1.1609 0.01532 0.00693 -0.0542 0.0732 0.0331
6.750 1.1799 0.01645 0.00791 -0.0541 0.0183 0.0440
7.000 1.2036 0.01681 0.00842 -0.0541 0.0141 0.1347
7.500 1.2528 0.01652 0.00965 -0.0549 0.0115 0.9895
7.750 1.3215 0.01761 0.01079 -0.0655 0.0089 1.0000
8.000 1.3375 0.01820 0.01141 -0.0644 0.0085 1.0000
8.250 1.3512 0.01888 0.01213 -0.0630 0.0079 1.0000
8.500 1.3619 0.01976 0.01304 -0.0615 0.0073 1.0000
8.750 1.3628 0.02117 0.01451 -0.0594 0.0069 1.0000
9.000 1.3607 0.02283 0.01622 -0.0569 0.0066 1.0000
9.250 1.3636 0.02480 0.01824 -0.0559 0.0062 1.0000
9.500 1.3671 0.02696 0.02048 -0.0553 0.0059 1.0000
9.750 1.3730 0.02895 0.02253 -0.0548 0.0057 1.0000
10.000 1.3774 0.03112 0.02477 -0.0544 0.0055 1.0000
10.250 1.3806 0.03343 0.02714 -0.0539 0.0053 1.0000
10.500 1.3830 0.03582 0.02960 -0.0534 0.0051 1.0000
10.750 1.3845 0.03830 0.03214 -0.0530 0.0049 1.0000
11.000 1.3857 0.04081 0.03472 -0.0525 0.0047 1.0000
11.250 1.3873 0.04327 0.03723 -0.0520 0.0046 1.0000
11.500 1.3886 0.04576 0.03977 -0.0516 0.0044 1.0000
11.750 1.3880 0.04849 0.04255 -0.0511 0.0042 1.0000
12.000 1.3851 0.05157 0.04570 -0.0507 0.0040 1.0000
12.250 1.3819 0.05473 0.04893 -0.0504 0.0039 1.0000
12.500 1.3816 0.05764 0.05191 -0.0501 0.0038 1.0000
12.750 1.3816 0.06052 0.05486 -0.0499 0.0037 1.0000
13.000 1.3803 0.06361 0.05803 -0.0497 0.0036 1.0000
13.250 1.3793 0.06669 0.06118 -0.0496 0.0035 1.0000
13.500 1.3775 0.06993 0.06450 -0.0495 0.0034 1.0000
13.750 1.3761 0.07310 0.06775 -0.0494 0.0033 1.0000
14.000 1.3739 0.07644 0.07115 -0.0494 0.0032 1.0000
14.250 1.3731 0.07962 0.07440 -0.0494 0.0032 1.0000
14.500 1.3713 0.08300 0.07785 -0.0495 0.0031 1.0000
14.750 1.3710 0.08612 0.08104 -0.0496 0.0030 1.0000
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Polar data table (+)
Polar graphs
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