MH 26 10.99% (mh26-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 26 10.99% (mh26-il) Reynolds number: 100,000 Max Cl/Cd: 51.18 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh26-il-100000.txt Download as CSV file: xf-mh26-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5186 0.10599 0.10138 -0.0362 1.0000 0.0864
-9.250 -0.5440 0.10220 0.09766 -0.0394 1.0000 0.0867
-9.000 -0.5687 0.09941 0.09490 -0.0392 1.0000 0.0868
-8.750 -0.5230 0.09541 0.09088 -0.0322 1.0000 0.0921
-8.500 -0.5348 0.09209 0.08761 -0.0322 1.0000 0.0939
-8.250 -0.5540 0.08879 0.08436 -0.0322 1.0000 0.0951
-8.000 -0.5807 0.08615 0.08175 -0.0299 1.0000 0.0965
-7.750 -0.6014 0.08365 0.07925 -0.0273 1.0000 0.0972
-7.500 -0.6421 0.08141 0.07689 -0.0244 1.0000 0.0999
-7.250 -0.6718 0.08032 0.07546 -0.0203 1.0000 0.1006
-7.000 -0.6433 0.07375 0.06923 -0.0198 1.0000 0.1043
-6.750 -0.6457 0.07094 0.06639 -0.0172 1.0000 0.1083
-6.500 -0.6708 0.06854 0.06364 -0.0137 1.0000 0.1150
-6.250 -0.6583 0.06454 0.05977 -0.0118 1.0000 0.1187
-5.500 -0.6585 0.05600 0.05085 -0.0035 1.0000 0.1449
-5.250 -0.6559 0.05352 0.04820 -0.0007 1.0000 0.1576
-5.000 -0.6350 0.04311 0.03613 0.0041 1.0000 0.0629
-4.750 -0.6162 0.03892 0.03129 0.0078 1.0000 0.0461
-4.500 -0.6015 0.03618 0.02818 0.0103 1.0000 0.0453
-4.250 -0.5847 0.03377 0.02535 0.0128 1.0000 0.0452
-4.000 -0.5658 0.03154 0.02271 0.0150 1.0000 0.0451
-3.750 -0.5447 0.02936 0.02016 0.0169 1.0000 0.0444
-3.500 -0.5212 0.02729 0.01775 0.0187 1.0000 0.0444
-3.250 -0.4978 0.02576 0.01601 0.0201 1.0000 0.0448
-3.000 -0.4745 0.02446 0.01450 0.0217 1.0000 0.0475
-2.750 -0.1599 0.02206 0.01551 -0.0266 1.0000 1.0000
-2.500 -0.1513 0.02184 0.01509 -0.0239 1.0000 1.0000
-2.250 -0.1421 0.02168 0.01472 -0.0214 1.0000 1.0000
-2.000 -0.1323 0.02157 0.01446 -0.0188 1.0000 1.0000
-1.750 -0.1220 0.02151 0.01425 -0.0163 1.0000 1.0000
-1.500 -0.1115 0.02148 0.01409 -0.0138 1.0000 1.0000
-1.250 -0.1007 0.02150 0.01399 -0.0114 1.0000 1.0000
-1.000 -0.0898 0.02155 0.01392 -0.0090 1.0000 1.0000
-0.750 -0.0789 0.02163 0.01389 -0.0066 1.0000 1.0000
-0.500 -0.0679 0.02175 0.01392 -0.0042 1.0000 1.0000
-0.250 -0.0569 0.02190 0.01398 -0.0019 1.0000 1.0000
0.000 -0.0459 0.02209 0.01410 0.0004 1.0000 1.0000
0.250 -0.0350 0.02231 0.01426 0.0026 1.0000 1.0000
0.500 -0.0241 0.02257 0.01446 0.0048 1.0000 1.0000
0.750 0.0000 0.02299 0.01482 0.0043 0.9969 1.0000
1.000 0.0537 0.02374 0.01553 -0.0022 0.9855 1.0000
1.250 0.1035 0.02435 0.01611 -0.0076 0.9734 1.0000
1.500 0.1495 0.02482 0.01657 -0.0121 0.9608 1.0000
1.750 0.1930 0.02517 0.01695 -0.0160 0.9482 1.0000
2.000 0.2362 0.02543 0.01724 -0.0197 0.9353 1.0000
2.250 0.2793 0.02558 0.01745 -0.0231 0.9223 1.0000
2.500 0.3222 0.02560 0.01754 -0.0264 0.9093 1.0000
2.750 0.3650 0.02549 0.01752 -0.0294 0.8963 1.0000
3.000 0.4082 0.02524 0.01741 -0.0323 0.8831 1.0000
3.250 0.4516 0.02482 0.01712 -0.0350 0.8695 1.0000
3.500 0.4952 0.02423 0.01668 -0.0375 0.8557 1.0000
3.750 0.5404 0.02343 0.01610 -0.0400 0.8415 1.0000
4.000 0.5875 0.02237 0.01525 -0.0426 0.8269 1.0000
4.250 0.6367 0.02102 0.01413 -0.0451 0.8121 1.0000
4.500 0.6729 0.01981 0.01312 -0.0450 0.7913 1.0000
4.750 0.7238 0.01839 0.01200 -0.0475 0.7642 1.0000
5.000 0.7916 0.01698 0.01074 -0.0532 0.7107 1.0000
5.250 0.8460 0.01653 0.01007 -0.0568 0.6182 1.0000
5.500 0.8648 0.01702 0.01017 -0.0543 0.5345 1.0000
5.750 0.8732 0.01774 0.01061 -0.0501 0.4610 1.0000
6.000 0.8773 0.01857 0.01108 -0.0455 0.3939 1.0000
6.250 0.8799 0.01947 0.01164 -0.0406 0.3321 1.0000
6.500 0.8814 0.02046 0.01228 -0.0358 0.2751 1.0000
6.750 0.8832 0.02152 0.01304 -0.0311 0.2235 1.0000
7.000 0.8844 0.02270 0.01389 -0.0263 0.1791 1.0000
7.250 0.8882 0.02399 0.01495 -0.0220 0.1427 1.0000
7.500 0.8930 0.02525 0.01604 -0.0180 0.1153 1.0000
7.750 0.9046 0.02691 0.01754 -0.0152 0.0962 1.0000
8.000 0.9245 0.02873 0.01936 -0.0137 0.0817 1.0000
8.250 0.9435 0.03049 0.02112 -0.0124 0.0703 1.0000
8.500 0.9698 0.03268 0.02345 -0.0120 0.0625 1.0000
8.750 0.9939 0.03561 0.02678 -0.0111 0.0564 1.0000
9.000 1.0040 0.03721 0.02855 -0.0082 0.0509 1.0000
9.250 1.0201 0.04166 0.03328 -0.0066 0.0475 1.0000
9.500 1.0171 0.04333 0.03543 -0.0011 0.0456 1.0000
9.750 1.0124 0.04522 0.03770 0.0043 0.0425 1.0000
10.000 1.0104 0.04749 0.04018 0.0088 0.0400 1.0000
10.250 1.0021 0.05031 0.04333 0.0140 0.0397 1.0000
10.500 0.9857 0.05294 0.04630 0.0203 0.0401 1.0000
10.750 0.9647 0.05557 0.04923 0.0268 0.0405 1.0000
11.000 0.9437 0.05830 0.05220 0.0325 0.0406 1.0000
11.250 0.9201 0.06140 0.05556 0.0373 0.0413 1.0000
11.500 0.8964 0.06485 0.05924 0.0411 0.0422 1.0000
11.750 0.8720 0.06860 0.06318 0.0437 0.0426 1.0000
12.000 0.8486 0.07270 0.06745 0.0449 0.0433 1.0000
12.250 0.8224 0.07763 0.07253 0.0448 0.0439 1.0000
12.500 0.8001 0.08288 0.07787 0.0433 0.0446 1.0000
12.750 0.7761 0.08933 0.08441 0.0402 0.0453 1.0000
13.000 0.7584 0.09588 0.09099 0.0369 0.0463 1.0000
13.250 0.7409 0.10339 0.09851 0.0331 0.0471 1.0000
13.500 0.7282 0.11148 0.10664 0.0289 0.0491 1.0000
13.750 0.7054 0.12551 0.12052 0.0228 0.0599 1.0000
14.000 0.6540 0.14861 0.14342 0.0064 0.1162 1.0000
14.250 0.6821 0.15323 0.14812 0.0104 0.1111 1.0000
14.500 0.6641 0.15757 0.15237 0.0054 0.1101 1.0000
14.750 0.6543 0.16133 0.15607 0.0019 0.1053 1.0000
15.000 0.5399 0.15233 0.14763 0.0125 0.1113 1.0000
15.250 0.5170 0.15321 0.14847 0.0088 0.1105 1.0000
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Polar data table (+)
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