MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 100,000 Max Cl/Cd: 53.31 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh18-il-100000.txt Download as CSV file: xf-mh18-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3028 0.11119 0.10716 -0.0266 1.0000 0.0858
-10.250 -0.3116 0.10806 0.10408 -0.0306 1.0000 0.0889
-10.000 -0.3266 0.10510 0.10119 -0.0357 1.0000 0.0897
-9.750 -0.3040 0.09923 0.09533 -0.0343 1.0000 0.0920
-9.500 -0.2916 0.09553 0.09164 -0.0347 1.0000 0.0952
-9.250 -0.2906 0.09197 0.08812 -0.0365 1.0000 0.0992
-9.000 -0.3076 0.08939 0.08563 -0.0393 1.0000 0.1023
-8.750 -0.3331 0.08919 0.08554 -0.0369 1.0000 0.1027
-8.500 -0.3622 0.08802 0.08448 -0.0371 0.9984 0.1031
-8.250 -0.3361 0.08214 0.07858 -0.0367 0.9950 0.1061
-8.000 -0.3218 0.07750 0.07394 -0.0391 0.9898 0.1105
-7.750 -0.3357 0.07174 0.06820 -0.0493 0.9825 0.1160
-6.750 -0.3907 0.06572 0.06178 -0.0557 0.9666 0.1237
-6.000 -0.3673 0.04278 0.03665 -0.0620 0.9430 0.0500
-5.750 -0.3605 0.03945 0.03316 -0.0598 0.9350 0.0481
-5.500 -0.3382 0.03575 0.02896 -0.0597 0.9305 0.0460
-5.250 -0.3289 0.03352 0.02629 -0.0566 0.9233 0.0453
-5.000 -0.3044 0.03128 0.02350 -0.0559 0.9185 0.0475
-4.750 -0.2824 0.02981 0.02145 -0.0543 0.9133 0.0508
-4.500 -0.2615 0.02750 0.01900 -0.0532 0.9080 0.0539
-4.250 -0.2288 0.02608 0.01726 -0.0535 0.9042 0.0636
-4.000 -0.2085 0.02465 0.01594 -0.0523 0.8991 0.0811
-3.750 -0.1892 0.02371 0.01504 -0.0507 0.8937 0.1105
-3.500 -0.1617 0.02260 0.01417 -0.0506 0.8899 0.1647
-3.250 -0.1522 0.02208 0.01394 -0.0476 0.8836 0.2222
-3.000 -0.1340 0.02116 0.01362 -0.0461 0.8786 0.3310
-2.750 0.0497 0.01918 0.01334 -0.0709 0.8874 0.9406
-2.500 0.1734 0.01892 0.01252 -0.0882 0.8895 0.9898
-2.250 0.2167 0.01879 0.01213 -0.0925 0.8841 1.0000
-2.000 0.2343 0.01896 0.01214 -0.0914 0.8775 1.0000
-1.750 0.2490 0.01928 0.01232 -0.0899 0.8702 1.0000
-1.500 0.2677 0.01948 0.01239 -0.0888 0.8637 1.0000
-1.250 0.2827 0.01986 0.01265 -0.0873 0.8565 1.0000
-1.000 0.3021 0.02009 0.01275 -0.0861 0.8501 1.0000
-0.750 0.3172 0.02050 0.01307 -0.0844 0.8426 1.0000
-0.500 0.3377 0.02072 0.01319 -0.0832 0.8362 1.0000
-0.250 0.3526 0.02118 0.01358 -0.0815 0.8284 1.0000
0.000 0.3747 0.02135 0.01366 -0.0804 0.8221 1.0000
0.250 0.3890 0.02186 0.01412 -0.0786 0.8137 1.0000
0.500 0.4131 0.02196 0.01415 -0.0775 0.8078 1.0000
0.750 0.4267 0.02252 0.01467 -0.0756 0.7986 1.0000
1.000 0.4529 0.02251 0.01462 -0.0747 0.7934 1.0000
1.500 0.4886 0.02328 0.01534 -0.0715 0.7765 1.0000
1.750 0.5083 0.02354 0.01559 -0.0700 0.7681 1.0000
2.000 0.5255 0.02397 0.01601 -0.0683 0.7588 1.0000
2.250 0.5522 0.02382 0.01588 -0.0672 0.7528 1.0000
2.500 0.5685 0.02428 0.01636 -0.0654 0.7423 1.0000
2.750 0.5915 0.02433 0.01641 -0.0640 0.7346 1.0000
3.000 0.6144 0.02434 0.01645 -0.0626 0.7262 1.0000
3.250 0.6329 0.02465 0.01679 -0.0609 0.7158 1.0000
3.500 0.6627 0.02412 0.01632 -0.0597 0.7107 1.0000
3.750 0.6808 0.02442 0.01668 -0.0580 0.6992 1.0000
4.000 0.7010 0.02457 0.01689 -0.0564 0.6885 1.0000
4.250 0.7318 0.02385 0.01621 -0.0552 0.6832 1.0000
4.500 0.7518 0.02397 0.01645 -0.0535 0.6714 1.0000
4.750 0.7733 0.02393 0.01650 -0.0519 0.6600 1.0000
5.000 0.7973 0.02368 0.01634 -0.0503 0.6495 1.0000
5.250 0.8277 0.02285 0.01556 -0.0490 0.6421 1.0000
5.500 0.8507 0.02260 0.01547 -0.0474 0.6294 1.0000
5.750 0.8746 0.02226 0.01524 -0.0459 0.6165 1.0000
6.000 0.8994 0.02181 0.01489 -0.0443 0.6030 1.0000
6.250 0.9248 0.02130 0.01448 -0.0428 0.5888 1.0000
6.500 0.9508 0.02072 0.01399 -0.0413 0.5735 1.0000
6.750 0.9719 0.02053 0.01394 -0.0396 0.5538 1.0000
7.000 0.9966 0.02002 0.01350 -0.0379 0.5337 1.0000
7.250 1.0177 0.01980 0.01343 -0.0361 0.5088 1.0000
7.500 1.0381 0.01964 0.01328 -0.0340 0.4800 1.0000
7.750 1.0550 0.01979 0.01338 -0.0317 0.4458 1.0000
8.000 1.0684 0.02020 0.01368 -0.0291 0.4074 1.0000
8.250 1.0769 0.02089 0.01426 -0.0260 0.3655 1.0000
8.500 1.0817 0.02177 0.01504 -0.0227 0.3230 1.0000
8.750 1.0814 0.02288 0.01601 -0.0187 0.2766 1.0000
9.000 1.0734 0.02435 0.01721 -0.0141 0.2247 1.0000
9.250 1.0558 0.02625 0.01869 -0.0085 0.1742 1.0000
9.500 1.0375 0.02885 0.02079 -0.0038 0.1263 1.0000
9.750 1.0236 0.03163 0.02317 0.0000 0.0974 1.0000
10.000 1.0169 0.03418 0.02557 0.0029 0.0752 1.0000
10.250 1.0152 0.03650 0.02779 0.0054 0.0627 1.0000
10.500 1.0166 0.03882 0.03006 0.0076 0.0516 1.0000
10.750 1.0261 0.04110 0.03240 0.0098 0.0433 1.0000
11.000 1.0527 0.04380 0.03494 0.0112 0.0369 1.0000
11.250 1.0591 0.04568 0.03713 0.0128 0.0335 1.0000
11.500 1.0750 0.04820 0.03987 0.0142 0.0308 1.0000
11.750 1.0890 0.05121 0.04310 0.0155 0.0295 1.0000
12.000 1.0970 0.05445 0.04661 0.0168 0.0289 1.0000
12.250 1.0978 0.05803 0.05048 0.0183 0.0286 1.0000
12.500 1.0925 0.06172 0.05447 0.0196 0.0286 1.0000
12.750 1.0828 0.06554 0.05861 0.0207 0.0289 1.0000
13.000 1.0686 0.06978 0.06315 0.0214 0.0292 1.0000
13.250 1.0481 0.07454 0.06823 0.0214 0.0296 1.0000
13.500 1.0260 0.07965 0.07363 0.0206 0.0301 1.0000
13.750 1.0026 0.08537 0.07960 0.0189 0.0307 1.0000
14.000 0.9781 0.09178 0.08624 0.0164 0.0311 1.0000
14.250 0.9540 0.09874 0.09339 0.0129 0.0316 1.0000
14.500 0.9299 0.10652 0.10133 0.0085 0.0322 1.0000
14.750 0.9027 0.11599 0.11093 0.0027 0.0327 1.0000
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Polar data table (+)
Polar graphs
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