NACA M26 AIRFOIL (m26-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA M26 AIRFOIL (m26-il) Reynolds number: 500,000 Max Cl/Cd: 98.75 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-m26-il-500000-n5.txt Download as CSV file: xf-m26-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1750 0.09175 0.08816 -0.0036 0.5126 0.0112
-7.750 -0.1756 0.08695 0.08337 -0.0048 0.5118 0.0084
-7.250 -0.2602 0.09617 0.09244 0.0030 0.5128 0.0083
-7.000 -0.2488 0.09305 0.08932 0.0003 0.5116 0.0081
-6.750 -0.2360 0.08971 0.08597 -0.0026 0.5104 0.0080
-6.500 -0.2216 0.08623 0.08247 -0.0058 0.5093 0.0080
-6.250 -0.2057 0.08262 0.07883 -0.0091 0.5082 0.0081
-6.000 -0.1879 0.07863 0.07480 -0.0128 0.5072 0.0083
-5.750 -0.1687 0.07549 0.07163 -0.0158 0.5061 0.0088
-5.500 -0.1488 0.07335 0.06945 -0.0180 0.5049 0.0094
-5.250 -0.1272 0.07033 0.06636 -0.0209 0.5038 0.0101
-5.000 -0.1043 0.06687 0.06284 -0.0240 0.5028 0.0103
-4.750 -0.0799 0.06334 0.05922 -0.0272 0.5017 0.0106
-4.500 -0.0512 0.05856 0.05433 -0.0313 0.5009 0.0114
-4.250 -0.0287 0.05709 0.05284 -0.0326 0.4999 0.0119
-4.000 -0.0034 0.05500 0.05069 -0.0345 0.4987 0.0131
-3.750 0.0244 0.05192 0.04753 -0.0369 0.4975 0.0137
-3.500 0.0582 0.04764 0.04308 -0.0400 0.4963 0.0149
-3.250 0.0809 0.04644 0.04185 -0.0408 0.4951 0.0155
-3.000 0.1077 0.04475 0.04009 -0.0421 0.4940 0.0171
-2.750 0.1373 0.04216 0.03738 -0.0437 0.4929 0.0178
-2.500 0.1717 0.03916 0.03419 -0.0454 0.4919 0.0195
-2.250 0.1939 0.03820 0.03320 -0.0460 0.4908 0.0208
-2.000 0.2312 0.03744 0.03227 -0.0472 0.4898 0.0244
-1.750 0.2604 0.03533 0.03001 -0.0479 0.4887 0.0245
-1.500 0.2891 0.03339 0.02792 -0.0484 0.4875 0.0246
-1.250 0.3187 0.03179 0.02616 -0.0489 0.4863 0.0248
-1.000 0.3476 0.02999 0.02424 -0.0492 0.4854 0.0248
-0.750 0.3739 0.02689 0.02097 -0.0496 0.4845 0.0256
-0.500 0.4000 0.02575 0.01977 -0.0500 0.4835 0.0262
-0.250 0.4271 0.02476 0.01873 -0.0504 0.4824 0.0271
0.250 0.4877 0.02373 0.01750 -0.0508 0.4797 0.0333
0.500 0.5166 0.02256 0.01621 -0.0509 0.4785 0.0334
0.750 0.5452 0.02133 0.01485 -0.0510 0.4772 0.0334
1.000 0.5728 0.01852 0.01176 -0.0509 0.4756 0.0276
1.250 0.6019 0.01727 0.01032 -0.0508 0.4736 0.0278
1.500 0.6307 0.01620 0.00905 -0.0507 0.4717 0.0281
1.750 0.6596 0.01516 0.00785 -0.0507 0.4701 0.0282
2.000 0.6882 0.01456 0.00717 -0.0509 0.4687 0.0292
2.250 0.7169 0.01390 0.00641 -0.0510 0.4672 0.0293
2.500 0.7454 0.01327 0.00567 -0.0511 0.4655 0.0288
2.750 0.7736 0.01283 0.00516 -0.0513 0.4639 0.0285
3.000 0.8014 0.01250 0.00478 -0.0514 0.4623 0.0285
3.250 0.8290 0.01226 0.00451 -0.0515 0.4607 0.0286
3.500 0.8563 0.01207 0.00430 -0.0515 0.4590 0.0290
3.750 0.8836 0.01196 0.00416 -0.0516 0.4574 0.0297
4.000 0.9110 0.01187 0.00409 -0.0518 0.4559 0.0307
4.250 0.9386 0.01181 0.00408 -0.0520 0.4543 0.0317
4.500 0.9664 0.01177 0.00409 -0.0522 0.4522 0.0325
4.750 0.9942 0.01177 0.00413 -0.0525 0.4500 0.0333
5.000 1.0219 0.01175 0.00415 -0.0528 0.4479 0.0353
5.250 1.0496 0.01173 0.00411 -0.0530 0.4437 0.0360
5.500 1.0776 0.01169 0.00412 -0.0534 0.4364 0.0368
5.750 1.1054 0.01169 0.00412 -0.0537 0.4289 0.0386
6.000 1.1332 0.01169 0.00416 -0.0541 0.4162 0.0438
6.250 1.1603 0.01175 0.00429 -0.0544 0.3989 0.1095
6.750 1.2273 0.01294 0.00619 -0.0605 0.2724 0.9941
7.250 1.2533 0.01971 0.01172 -0.0642 0.0180 1.0000
7.500 1.2667 0.02053 0.01260 -0.0629 0.0154 1.0000
7.750 1.2760 0.02166 0.01385 -0.0615 0.0136 1.0000
8.000 1.2784 0.02309 0.01535 -0.0596 0.0131 1.0000
8.250 1.2778 0.02471 0.01703 -0.0574 0.0124 1.0000
8.500 1.2816 0.02648 0.01888 -0.0562 0.0116 1.0000
8.750 1.2857 0.02846 0.02094 -0.0553 0.0110 1.0000
9.000 1.2893 0.03061 0.02316 -0.0546 0.0104 1.0000
9.250 1.2913 0.03297 0.02560 -0.0540 0.0099 1.0000
9.500 1.2906 0.03566 0.02838 -0.0533 0.0095 1.0000
9.750 1.2850 0.03886 0.03170 -0.0526 0.0090 1.0000
10.000 1.2856 0.04142 0.03433 -0.0520 0.0087 1.0000
10.250 1.2881 0.04380 0.03678 -0.0515 0.0084 1.0000
10.500 1.2892 0.04633 0.03937 -0.0510 0.0079 1.0000
10.750 1.2881 0.04909 0.04221 -0.0504 0.0076 1.0000
11.000 1.2868 0.05198 0.04517 -0.0500 0.0074 1.0000
11.250 1.2859 0.05488 0.04814 -0.0496 0.0071 1.0000
11.500 1.2845 0.05792 0.05125 -0.0493 0.0069 1.0000
11.750 1.2837 0.06092 0.05432 -0.0491 0.0067 1.0000
12.000 1.2819 0.06409 0.05757 -0.0489 0.0065 1.0000
12.250 1.2794 0.06739 0.06093 -0.0487 0.0063 1.0000
12.500 1.2749 0.07097 0.06458 -0.0486 0.0062 1.0000
12.750 1.2677 0.07491 0.06861 -0.0484 0.0060 1.0000
13.000 1.2653 0.07829 0.07205 -0.0483 0.0059 1.0000
13.250 1.2656 0.08136 0.07520 -0.0483 0.0058 1.0000
13.500 1.2666 0.08433 0.07824 -0.0482 0.0056 1.0000
13.750 1.2686 0.08715 0.08112 -0.0481 0.0053 1.0000
14.000 1.2705 0.09002 0.08406 -0.0481 0.0051 1.0000
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Polar data table (+)
Polar graphs
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