MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 200,000 Max Cl/Cd: 76.32 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh120-il-200000.txt Download as CSV file: xf-mh120-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 120 11.57%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4104 0.09031 0.08695 -0.0428 1.0000 0.0512
-9.000 -0.4242 0.08542 0.08214 -0.0474 1.0000 0.0521
-8.750 -0.4481 0.07977 0.07655 -0.0529 1.0000 0.0523
-8.500 -0.4675 0.07701 0.07382 -0.0512 1.0000 0.0523
-8.250 -0.4951 0.07472 0.07152 -0.0479 1.0000 0.0524
-8.000 -0.5166 0.07265 0.06942 -0.0445 1.0000 0.0525
-7.750 -0.5376 0.07105 0.06773 -0.0405 1.0000 0.0527
-7.500 -0.4651 0.05609 0.05338 -0.0395 0.9983 0.0565
-7.250 -0.5609 0.06182 0.05841 -0.0373 0.9979 0.0542
-7.000 -0.5340 0.05850 0.05522 -0.0394 0.9947 0.0564
-6.750 -0.5111 0.05467 0.05125 -0.0426 0.9884 0.0602
-6.250 -0.4690 0.04550 0.04150 -0.0486 0.9746 0.0716
-6.000 -0.4521 0.04199 0.03741 -0.0494 0.9650 0.0815
-5.750 -0.4232 0.03994 0.03493 -0.0513 0.9602 0.0942
-5.500 -0.3990 0.03674 0.03202 -0.0521 0.9529 0.1011
-5.250 -0.3697 0.03431 0.02937 -0.0537 0.9480 0.1164
-5.000 -0.3409 0.02524 0.01826 -0.0477 0.9406 0.0421
-4.750 -0.3037 0.02365 0.01641 -0.0489 0.9360 0.0401
-4.500 -0.2647 0.02119 0.01370 -0.0508 0.9335 0.0392
-4.250 -0.2318 0.02026 0.01255 -0.0515 0.9270 0.0405
-4.000 -0.1940 0.01858 0.01076 -0.0532 0.9226 0.0409
-3.750 -0.1530 0.01696 0.00913 -0.0558 0.9198 0.0414
-3.500 -0.1232 0.01575 0.00792 -0.0561 0.9127 0.0433
-3.250 -0.0887 0.01490 0.00701 -0.0573 0.9066 0.0464
-3.000 -0.0550 0.01433 0.00634 -0.0584 0.8999 0.0519
-2.750 -0.0234 0.01364 0.00563 -0.0589 0.8920 0.0669
-2.500 -0.0147 0.01172 0.00520 -0.0556 0.8812 0.4039
-2.250 0.0063 0.01087 0.00503 -0.0539 0.8736 0.5886
-2.000 0.0261 0.01034 0.00500 -0.0515 0.8635 0.7222
-1.750 0.1191 0.00998 0.00502 -0.0642 0.8624 0.8843
-1.500 0.1958 0.01021 0.00510 -0.0736 0.8575 0.9256
-1.250 0.2456 0.01038 0.00513 -0.0778 0.8486 0.9411
-1.000 0.2942 0.01055 0.00514 -0.0819 0.8388 0.9541
-0.750 0.3434 0.01064 0.00509 -0.0863 0.8294 0.9654
-0.500 0.3916 0.01070 0.00502 -0.0906 0.8190 0.9766
-0.250 0.4400 0.01071 0.00493 -0.0951 0.8079 0.9870
0.000 0.4898 0.01063 0.00475 -0.1000 0.7972 0.9959
0.250 0.5259 0.01054 0.00456 -0.1021 0.7862 1.0000
0.500 0.5459 0.01054 0.00446 -0.1008 0.7749 1.0000
0.750 0.5637 0.01057 0.00444 -0.0989 0.7628 1.0000
1.000 0.5825 0.01062 0.00442 -0.0973 0.7513 1.0000
1.250 0.6024 0.01067 0.00442 -0.0958 0.7401 1.0000
1.500 0.6236 0.01073 0.00441 -0.0945 0.7296 1.0000
1.750 0.6443 0.01080 0.00442 -0.0931 0.7186 1.0000
2.000 0.6638 0.01087 0.00447 -0.0914 0.7067 1.0000
2.250 0.6840 0.01095 0.00453 -0.0899 0.6950 1.0000
2.500 0.7050 0.01104 0.00458 -0.0884 0.6840 1.0000
2.750 0.7271 0.01114 0.00463 -0.0873 0.6737 1.0000
3.000 0.7476 0.01125 0.00474 -0.0857 0.6625 1.0000
3.250 0.7680 0.01137 0.00488 -0.0842 0.6514 1.0000
3.500 0.7891 0.01149 0.00500 -0.0828 0.6403 1.0000
3.750 0.8106 0.01161 0.00510 -0.0815 0.6290 1.0000
4.000 0.8323 0.01174 0.00521 -0.0801 0.6175 1.0000
4.250 0.8522 0.01187 0.00540 -0.0785 0.6053 1.0000
4.500 0.8724 0.01200 0.00556 -0.0769 0.5924 1.0000
4.750 0.8925 0.01214 0.00572 -0.0752 0.5790 1.0000
5.000 0.9123 0.01228 0.00589 -0.0735 0.5650 1.0000
5.250 0.9320 0.01244 0.00607 -0.0718 0.5504 1.0000
5.500 0.9514 0.01260 0.00628 -0.0700 0.5353 1.0000
5.750 0.9704 0.01278 0.00647 -0.0681 0.5190 1.0000
6.000 0.9885 0.01298 0.00670 -0.0661 0.5011 1.0000
6.250 1.0059 0.01318 0.00695 -0.0640 0.4813 1.0000
6.500 1.0219 0.01343 0.00719 -0.0615 0.4581 1.0000
6.750 1.0345 0.01373 0.00745 -0.0584 0.4246 1.0000
7.000 1.0448 0.01415 0.00773 -0.0550 0.3845 1.0000
7.250 1.0534 0.01472 0.00812 -0.0514 0.3402 1.0000
7.500 1.0601 0.01545 0.00862 -0.0476 0.2947 1.0000
7.750 1.0670 0.01623 0.00921 -0.0439 0.2539 1.0000
8.000 1.0730 0.01711 0.00988 -0.0402 0.2135 1.0000
8.250 1.0774 0.01809 0.01063 -0.0363 0.1705 1.0000
8.500 1.0762 0.01922 0.01149 -0.0315 0.1230 1.0000
8.750 1.0642 0.02105 0.01276 -0.0253 0.0550 1.0000
9.000 1.0569 0.02284 0.01431 -0.0200 0.0311 1.0000
9.250 1.0601 0.02413 0.01570 -0.0164 0.0264 1.0000
9.500 1.0651 0.02534 0.01702 -0.0134 0.0242 1.0000
9.750 1.0651 0.02696 0.01873 -0.0100 0.0225 1.0000
10.000 1.0610 0.02897 0.02086 -0.0067 0.0215 1.0000
10.250 1.0648 0.03059 0.02257 -0.0043 0.0209 1.0000
10.500 1.0689 0.03232 0.02442 -0.0021 0.0204 1.0000
10.750 1.0746 0.03404 0.02624 -0.0002 0.0199 1.0000
11.000 1.0813 0.03588 0.02818 0.0017 0.0197 1.0000
11.250 1.0903 0.03764 0.03007 0.0033 0.0191 1.0000
11.500 1.1018 0.03953 0.03207 0.0049 0.0190 1.0000
11.750 1.1119 0.04132 0.03398 0.0063 0.0183 1.0000
12.000 1.1192 0.04310 0.03588 0.0074 0.0174 1.0000
12.250 1.1317 0.04538 0.03835 0.0088 0.0176 1.0000
12.500 1.1359 0.04758 0.04067 0.0100 0.0167 1.0000
12.750 1.1413 0.05028 0.04360 0.0113 0.0167 1.0000
13.000 1.1427 0.05324 0.04672 0.0124 0.0162 1.0000
13.250 1.1411 0.05645 0.05022 0.0134 0.0165 1.0000
13.500 1.1345 0.06030 0.05436 0.0143 0.0166 1.0000
13.750 1.1224 0.06474 0.05914 0.0147 0.0172 1.0000
14.000 1.1060 0.06972 0.06441 0.0145 0.0173 1.0000
14.250 1.0865 0.07523 0.07020 0.0136 0.0178 1.0000
14.500 1.0671 0.08095 0.07617 0.0120 0.0180 1.0000
14.750 1.0459 0.08734 0.08279 0.0096 0.0181 1.0000
15.000 1.0267 0.09384 0.08949 0.0068 0.0188 1.0000
15.250 1.0046 0.10133 0.09716 0.0029 0.0188 1.0000
15.500 0.9802 0.10994 0.10595 -0.0019 0.0191 1.0000
15.750 0.9597 0.11837 0.11452 -0.0069 0.0194 1.0000
16.000 0.9343 0.12888 0.12518 -0.0135 0.0194 1.0000
16.250 0.9048 0.14176 0.13818 -0.0213 0.0197 1.0000
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Polar data table (+)
Polar graphs
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