MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 500,000 Max Cl/Cd: 58.37 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh26-il-500000-n5.txt Download as CSV file: xf-mh26-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 26 10.99%
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3892 0.08276 0.08036 -0.0734 0.9834 0.0045
-10.000 -0.3926 0.07726 0.07488 -0.0773 0.9818 0.0045
-9.750 -0.3980 0.07118 0.06881 -0.0823 0.9793 0.0045
-9.500 -0.4109 0.06274 0.06031 -0.0911 0.9765 0.0044
-9.250 -0.4235 0.05677 0.05421 -0.0945 0.9742 0.0043
-9.000 -0.4305 0.05179 0.04907 -0.0957 0.9721 0.0042
-8.750 -0.4435 0.04814 0.04526 -0.0928 0.9684 0.0041
-8.500 -0.4547 0.04495 0.04190 -0.0889 0.9640 0.0040
-8.250 -0.4582 0.04090 0.03762 -0.0862 0.9610 0.0039
-8.000 -0.4631 0.03565 0.03199 -0.0827 0.9586 0.0035
-7.750 -0.4645 0.03227 0.02829 -0.0783 0.9558 0.0034
-7.500 -0.4842 0.02613 0.02143 -0.0692 0.9499 0.0030
-7.250 -0.4720 0.02360 0.01848 -0.0665 0.9480 0.0028
-7.000 -0.4536 0.02162 0.01616 -0.0649 0.9466 0.0028
-6.750 -0.4322 0.02010 0.01436 -0.0639 0.9456 0.0027
-6.500 -0.4089 0.01879 0.01283 -0.0632 0.9448 0.0027
-6.250 -0.3871 0.01747 0.01128 -0.0621 0.9436 0.0028
-6.000 -0.3819 0.01685 0.01054 -0.0575 0.9388 0.0028
-5.750 -0.3625 0.01602 0.00959 -0.0559 0.9367 0.0028
-5.500 -0.3409 0.01519 0.00865 -0.0547 0.9350 0.0029
-5.250 -0.3175 0.01451 0.00788 -0.0540 0.9337 0.0029
-5.000 -0.2932 0.01387 0.00716 -0.0534 0.9326 0.0031
-4.750 -0.2676 0.01335 0.00656 -0.0531 0.9316 0.0033
-4.500 -0.2409 0.01292 0.00606 -0.0530 0.9308 0.0036
-4.250 -0.2356 0.01280 0.00587 -0.0482 0.9249 0.0039
-4.000 -0.2121 0.01249 0.00549 -0.0474 0.9227 0.0045
-3.750 -0.1858 0.01212 0.00507 -0.0471 0.9210 0.0063
-3.500 -0.1592 0.01165 0.00470 -0.0470 0.9196 0.0253
-3.250 -0.1337 0.01102 0.00438 -0.0468 0.9183 0.0896
-3.000 -0.1226 0.01051 0.00424 -0.0436 0.9137 0.1796
-2.750 -0.1043 0.01013 0.00406 -0.0417 0.9098 0.2416
-2.500 -0.0839 0.00944 0.00378 -0.0405 0.9072 0.3624
-2.250 -0.0671 0.00858 0.00350 -0.0385 0.9051 0.5179
-2.000 -0.0608 0.00817 0.00341 -0.0339 0.8992 0.6061
-1.750 -0.0478 0.00764 0.00325 -0.0305 0.8949 0.7037
-1.500 -0.0170 0.00726 0.00332 -0.0307 0.8932 0.8239
-1.250 0.0216 0.00725 0.00334 -0.0328 0.8919 0.8644
-1.000 0.0494 0.00730 0.00338 -0.0326 0.8883 0.8834
-0.750 0.0708 0.00738 0.00346 -0.0310 0.8826 0.8993
-0.500 0.1061 0.00743 0.00348 -0.0323 0.8796 0.9091
-0.250 0.1270 0.00742 0.00344 -0.0306 0.8741 0.9168
0.000 0.1569 0.00748 0.00349 -0.0310 0.8681 0.9203
0.250 0.1889 0.00745 0.00343 -0.0318 0.8629 0.9242
0.500 0.2054 0.00745 0.00342 -0.0292 0.8530 0.9305
0.750 0.2406 0.00753 0.00349 -0.0307 0.8440 0.9331
1.000 0.2795 0.00756 0.00350 -0.0331 0.8335 0.9358
1.250 0.3154 0.00752 0.00342 -0.0347 0.8177 0.9387
1.500 0.3418 0.00744 0.00326 -0.0343 0.7970 0.9431
1.750 0.3798 0.00748 0.00316 -0.0365 0.7650 0.9436
2.000 0.4119 0.00765 0.00314 -0.0375 0.7258 0.9444
2.250 0.4385 0.00791 0.00320 -0.0373 0.6812 0.9456
2.500 0.4615 0.00821 0.00332 -0.0364 0.6367 0.9475
2.750 0.4806 0.00851 0.00345 -0.0347 0.5938 0.9504
3.000 0.4841 0.00872 0.00352 -0.0294 0.5605 0.9567
3.250 0.5089 0.00905 0.00368 -0.0291 0.5160 0.9579
3.500 0.5332 0.00938 0.00384 -0.0287 0.4739 0.9593
3.750 0.5564 0.00971 0.00403 -0.0281 0.4328 0.9610
4.000 0.5775 0.01004 0.00420 -0.0270 0.3915 0.9631
4.250 0.5954 0.01037 0.00438 -0.0253 0.3528 0.9661
4.500 0.6059 0.01061 0.00451 -0.0218 0.3219 0.9701
4.750 0.6321 0.01099 0.00473 -0.0220 0.2815 0.9711
5.000 0.6579 0.01135 0.00498 -0.0220 0.2468 0.9721
5.250 0.6823 0.01171 0.00522 -0.0218 0.2124 0.9734
5.500 0.7057 0.01209 0.00547 -0.0214 0.1805 0.9749
5.750 0.7272 0.01251 0.00575 -0.0206 0.1463 0.9767
6.000 0.7473 0.01294 0.00605 -0.0195 0.1161 0.9792
6.250 0.7615 0.01328 0.00632 -0.0170 0.0973 0.9825
6.500 0.7871 0.01369 0.00668 -0.0171 0.0765 0.9833
6.750 0.8121 0.01413 0.00705 -0.0172 0.0583 0.9843
7.000 0.8368 0.01455 0.00744 -0.0171 0.0448 0.9855
7.250 0.8607 0.01497 0.00785 -0.0168 0.0347 0.9868
7.500 0.8840 0.01546 0.00832 -0.0165 0.0260 0.9884
7.750 0.9072 0.01586 0.00877 -0.0161 0.0221 0.9901
8.000 0.9277 0.01641 0.00933 -0.0152 0.0174 0.9919
8.250 0.9486 0.01681 0.00980 -0.0143 0.0153 0.9936
8.500 0.9712 0.01731 0.01034 -0.0140 0.0121 0.9948
8.750 0.9933 0.01790 0.01098 -0.0135 0.0098 0.9962
9.000 1.0163 0.01836 0.01153 -0.0133 0.0083 0.9976
9.250 1.0375 0.01899 0.01218 -0.0128 0.0064 0.9989
9.500 1.0564 0.01967 0.01295 -0.0117 0.0053 1.0000
9.750 1.0636 0.02011 0.01343 -0.0082 0.0040 1.0000
10.000 1.0647 0.02098 0.01437 -0.0036 0.0030 1.0000
10.250 1.0727 0.02142 0.01487 -0.0004 0.0027 1.0000
10.500 1.0811 0.02184 0.01534 0.0027 0.0023 1.0000
10.750 1.0867 0.02251 0.01610 0.0063 0.0020 1.0000
11.000 1.0911 0.02330 0.01702 0.0099 0.0018 1.0000
11.250 1.0962 0.02411 0.01792 0.0133 0.0017 1.0000
11.500 1.1009 0.02501 0.01893 0.0166 0.0016 1.0000
11.750 1.1017 0.02624 0.02030 0.0203 0.0014 1.0000
12.000 1.1064 0.02726 0.02144 0.0233 0.0014 1.0000
12.250 1.1097 0.02843 0.02275 0.0263 0.0013 1.0000
12.500 1.1128 0.02966 0.02411 0.0291 0.0013 1.0000
12.750 1.1140 0.03110 0.02569 0.0320 0.0013 1.0000
13.000 1.1174 0.03240 0.02712 0.0343 0.0012 1.0000
13.250 1.1158 0.03420 0.02908 0.0370 0.0011 1.0000
13.500 1.1111 0.03634 0.03139 0.0395 0.0012 1.0000
13.750 1.1137 0.03795 0.03312 0.0411 0.0010 1.0000
14.000 1.1046 0.04073 0.03610 0.0432 0.0011 1.0000
14.250 1.0993 0.04336 0.03889 0.0445 0.0010 1.0000
14.500 1.0911 0.04650 0.04220 0.0453 0.0010 1.0000
14.750 1.0820 0.05001 0.04587 0.0456 0.0010 1.0000
15.000 1.0720 0.05398 0.05002 0.0452 0.0010 1.0000
15.250 1.0633 0.05813 0.05434 0.0442 0.0009 1.0000
15.500 1.0482 0.06360 0.05998 0.0423 0.0009 1.0000
15.750 1.0326 0.06965 0.06620 0.0396 0.0008 1.0000
16.000 1.0095 0.07750 0.07421 0.0357 0.0009 1.0000
16.250 0.9905 0.08505 0.08192 0.0317 0.0009 1.0000
16.500 0.9696 0.09334 0.09035 0.0275 0.0009 1.0000
16.750 0.9427 0.10311 0.10027 0.0226 0.0010 1.0000
17.000 0.9135 0.11364 0.11093 0.0175 0.0010 1.0000
17.250 0.8846 0.12443 0.12182 0.0124 0.0011 1.0000
17.500 0.8595 0.13457 0.13204 0.0077 0.0013 1.0000
17.750 0.8294 0.14676 0.14432 0.0022 0.0012 1.0000
18.000 0.8125 0.15583 0.15343 -0.0019 0.0013 1.0000
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Polar data table (+)
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