MH 27 11.99% (mh27-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 27 11.99% (mh27-il) Reynolds number: 100,000 Max Cl/Cd: 49.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh27-il-100000.txt Download as CSV file: xf-mh27-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 27 11.99%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4586 0.09834 0.09415 -0.0337 1.0000 0.1063
-9.000 -0.4448 0.09516 0.09098 -0.0301 1.0000 0.1120
-8.750 -0.5657 0.09390 0.08950 -0.0348 1.0000 0.0968
-8.500 -0.5735 0.09092 0.08654 -0.0332 1.0000 0.0995
-8.250 -0.5963 0.08794 0.08358 -0.0313 1.0000 0.1013
-8.000 -0.6212 0.08551 0.08116 -0.0278 1.0000 0.1011
-7.750 -0.6436 0.08284 0.07847 -0.0244 1.0000 0.1027
-7.500 -0.6897 0.08099 0.07636 -0.0196 1.0000 0.1065
-7.000 -0.6880 0.07323 0.06870 -0.0149 1.0000 0.1115
-6.750 -0.6937 0.07058 0.06595 -0.0117 1.0000 0.1168
-5.000 -0.6801 0.04198 0.03434 0.0151 1.0000 0.0527
-4.750 -0.6676 0.03879 0.03082 0.0181 1.0000 0.0517
-4.500 -0.6519 0.03568 0.02737 0.0207 1.0000 0.0478
-4.250 -0.6330 0.03287 0.02392 0.0236 1.0000 0.0446
-4.000 -0.6110 0.03055 0.02111 0.0259 1.0000 0.0435
-3.750 -0.5878 0.02867 0.01892 0.0274 1.0000 0.0437
-3.500 -0.5647 0.02713 0.01725 0.0287 1.0000 0.0447
-3.250 -0.5425 0.02579 0.01584 0.0301 1.0000 0.0483
-3.000 -0.5226 0.02458 0.01460 0.0318 1.0000 0.0569
-2.750 -0.1576 0.02538 0.01853 -0.0262 1.0000 1.0000
-2.500 -0.1491 0.02513 0.01813 -0.0237 1.0000 1.0000
-2.250 -0.1399 0.02496 0.01779 -0.0212 1.0000 1.0000
-2.000 -0.1302 0.02484 0.01751 -0.0188 1.0000 1.0000
-1.750 -0.1200 0.02477 0.01731 -0.0163 1.0000 1.0000
-1.500 -0.1096 0.02475 0.01718 -0.0139 1.0000 1.0000
-1.250 -0.0988 0.02477 0.01709 -0.0116 1.0000 1.0000
-1.000 -0.0880 0.02484 0.01705 -0.0093 1.0000 1.0000
-0.750 -0.0771 0.02493 0.01706 -0.0070 1.0000 1.0000
-0.500 -0.0661 0.02507 0.01710 -0.0047 1.0000 1.0000
-0.250 -0.0552 0.02525 0.01720 -0.0024 1.0000 1.0000
0.000 -0.0442 0.02546 0.01735 -0.0002 1.0000 1.0000
0.250 -0.0334 0.02571 0.01755 0.0020 1.0000 1.0000
0.500 -0.0227 0.02600 0.01779 0.0041 1.0000 1.0000
0.750 0.0100 0.02653 0.01826 0.0017 0.9949 1.0000
1.000 0.0658 0.02729 0.01898 -0.0052 0.9832 1.0000
1.250 0.1156 0.02785 0.01953 -0.0107 0.9711 1.0000
1.500 0.1607 0.02819 0.01987 -0.0151 0.9584 1.0000
1.750 0.2024 0.02843 0.02012 -0.0186 0.9457 1.0000
2.000 0.2430 0.02858 0.02031 -0.0219 0.9329 1.0000
2.250 0.2827 0.02866 0.02044 -0.0247 0.9202 1.0000
2.500 0.3226 0.02863 0.02048 -0.0275 0.9075 1.0000
2.750 0.3631 0.02848 0.02041 -0.0302 0.8947 1.0000
3.000 0.4033 0.02822 0.02027 -0.0327 0.8820 1.0000
3.250 0.4438 0.02782 0.01998 -0.0350 0.8691 1.0000
3.500 0.4847 0.02727 0.01955 -0.0372 0.8560 1.0000
3.750 0.5262 0.02654 0.01901 -0.0393 0.8426 1.0000
4.000 0.5687 0.02562 0.01827 -0.0413 0.8289 1.0000
4.250 0.6122 0.02451 0.01735 -0.0432 0.8147 1.0000
4.500 0.6572 0.02312 0.01621 -0.0449 0.8003 1.0000
4.750 0.7051 0.02144 0.01476 -0.0468 0.7845 1.0000
5.000 0.7456 0.02010 0.01363 -0.0476 0.7589 1.0000
5.250 0.8146 0.01851 0.01228 -0.0535 0.7118 1.0000
5.500 0.8869 0.01779 0.01136 -0.0607 0.6150 1.0000
5.750 0.9079 0.01827 0.01145 -0.0587 0.5316 1.0000
6.000 0.9148 0.01898 0.01180 -0.0543 0.4620 1.0000
6.250 0.9169 0.01978 0.01228 -0.0492 0.3994 1.0000
6.500 0.9169 0.02065 0.01283 -0.0438 0.3420 1.0000
6.750 0.9162 0.02156 0.01344 -0.0385 0.2896 1.0000
7.000 0.9148 0.02253 0.01412 -0.0331 0.2431 1.0000
7.250 0.9129 0.02357 0.01488 -0.0277 0.2020 1.0000
7.500 0.9122 0.02467 0.01581 -0.0226 0.1664 1.0000
7.750 0.9130 0.02588 0.01682 -0.0178 0.1361 1.0000
8.000 0.9178 0.02721 0.01800 -0.0138 0.1130 1.0000
8.250 0.9255 0.02852 0.01922 -0.0103 0.0953 1.0000
8.500 0.9489 0.03054 0.02115 -0.0098 0.0810 1.0000
8.750 0.9747 0.03254 0.02326 -0.0096 0.0697 1.0000
9.000 1.0110 0.03549 0.02642 -0.0112 0.0606 1.0000
9.250 1.0404 0.03888 0.02985 -0.0122 0.0536 1.0000
9.500 1.0411 0.04024 0.03166 -0.0071 0.0502 1.0000
9.750 1.0490 0.04288 0.03468 -0.0035 0.0472 1.0000
10.000 1.0548 0.04499 0.03685 -0.0005 0.0438 1.0000
10.250 1.0510 0.04882 0.04103 0.0038 0.0418 1.0000
10.500 1.0352 0.05011 0.04269 0.0110 0.0407 1.0000
10.750 1.0191 0.05198 0.04486 0.0178 0.0401 1.0000
11.000 1.0023 0.05429 0.04745 0.0241 0.0400 1.0000
11.250 0.9859 0.05672 0.05012 0.0298 0.0401 1.0000
11.500 0.9647 0.05944 0.05310 0.0355 0.0400 1.0000
11.750 0.9464 0.06222 0.05608 0.0400 0.0403 1.0000
12.000 0.9242 0.06523 0.05931 0.0442 0.0403 1.0000
12.250 0.9012 0.06874 0.06300 0.0475 0.0405 1.0000
12.500 0.8775 0.07245 0.06688 0.0499 0.0407 1.0000
12.750 0.8562 0.07655 0.07111 0.0512 0.0411 1.0000
13.000 0.8331 0.08119 0.07588 0.0515 0.0413 1.0000
13.250 0.8153 0.08621 0.08097 0.0510 0.0418 1.0000
13.500 0.7392 0.10085 0.09597 0.0407 0.0493 1.0000
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Polar data table (+)
Polar graphs
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