MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 50,000 Max Cl/Cd: 38.02 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh122-il-50000.txt Download as CSV file: xf-mh122-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.4489 0.10680 0.10070 -0.0208 1.0000 0.2489
-7.250 -0.4447 0.10377 0.09772 -0.0183 1.0000 0.2618
-7.000 -0.4425 0.10098 0.09499 -0.0158 1.0000 0.2743
-6.750 -0.4433 0.09852 0.09259 -0.0133 1.0000 0.2866
-6.500 -0.4507 0.09652 0.09068 -0.0102 1.0000 0.3001
-6.000 -0.4655 0.09280 0.08713 -0.0040 1.0000 0.3274
-5.750 -0.4820 0.09155 0.08601 -0.0013 1.0000 0.3433
-5.500 -0.4741 0.08822 0.08272 0.0018 1.0000 0.3608
-5.250 -0.4723 0.08575 0.08030 0.0047 1.0000 0.3794
-4.250 -0.3866 0.04766 0.04000 -0.0591 1.0000 0.1118
-4.000 -0.3517 0.04287 0.03452 -0.0619 1.0000 0.0971
-3.750 -0.3157 0.03882 0.02962 -0.0641 1.0000 0.0883
-3.500 -0.2833 0.03639 0.02642 -0.0648 1.0000 0.0861
-3.250 -0.2564 0.03368 0.02363 -0.0652 1.0000 0.0931
-3.000 -0.2266 0.03178 0.02121 -0.0651 1.0000 0.0982
-2.750 -0.1995 0.02984 0.01909 -0.0643 1.0000 0.1027
-2.500 -0.1742 0.02820 0.01736 -0.0632 1.0000 0.1218
-2.250 -0.1444 0.02632 0.01561 -0.0630 1.0000 0.1646
-2.000 -0.1293 0.02370 0.01591 -0.0569 1.0000 0.6907
-1.750 -0.1357 0.02369 0.01604 -0.0473 1.0000 0.7837
-1.500 -0.1427 0.02325 0.01570 -0.0382 1.0000 0.8593
-1.250 -0.1324 0.02210 0.01458 -0.0339 1.0000 1.0000
-1.000 -0.0915 0.02224 0.01409 -0.0393 1.0000 1.0000
-0.750 -0.0530 0.02252 0.01383 -0.0437 1.0000 1.0000
-0.500 -0.0185 0.02287 0.01373 -0.0468 1.0000 1.0000
-0.250 0.0125 0.02326 0.01368 -0.0490 1.0000 1.0000
0.000 0.0409 0.02369 0.01379 -0.0505 1.0000 1.0000
0.250 0.0676 0.02415 0.01396 -0.0516 1.0000 1.0000
0.500 0.0929 0.02464 0.01422 -0.0523 1.0000 1.0000
0.750 0.1174 0.02515 0.01449 -0.0528 1.0000 1.0000
1.000 0.1411 0.02570 0.01486 -0.0532 1.0000 1.0000
1.250 0.1641 0.02627 0.01530 -0.0535 1.0000 1.0000
1.500 0.1865 0.02688 0.01580 -0.0537 1.0000 1.0000
1.750 0.2085 0.02753 0.01636 -0.0538 1.0000 1.0000
2.000 0.2300 0.02821 0.01696 -0.0539 1.0000 1.0000
2.250 0.2510 0.02893 0.01763 -0.0540 1.0000 1.0000
2.500 0.2716 0.02969 0.01837 -0.0541 1.0000 1.0000
2.750 0.2916 0.03050 0.01917 -0.0541 1.0000 1.0000
3.000 0.3113 0.03136 0.02004 -0.0541 1.0000 1.0000
3.250 0.3303 0.03228 0.02099 -0.0542 1.0000 1.0000
3.500 0.3490 0.03326 0.02204 -0.0542 1.0000 1.0000
3.750 0.3670 0.03431 0.02314 -0.0543 1.0000 1.0000
4.000 0.3845 0.03543 0.02433 -0.0544 1.0000 1.0000
4.250 0.4014 0.03663 0.02562 -0.0546 1.0000 1.0000
4.500 0.4177 0.03792 0.02701 -0.0548 1.0000 1.0000
4.750 0.4871 0.04070 0.03015 -0.0647 0.9670 1.0000
5.000 0.5412 0.04237 0.03211 -0.0710 0.9365 1.0000
5.250 0.5998 0.04373 0.03381 -0.0771 0.9061 1.0000
5.500 0.6491 0.04438 0.03490 -0.0809 0.8726 1.0000
5.750 0.7149 0.04410 0.03512 -0.0856 0.8351 1.0000
6.000 0.7900 0.04178 0.03347 -0.0889 0.7905 1.0000
6.250 0.8759 0.03627 0.02899 -0.0896 0.7385 1.0000
6.500 0.9713 0.02555 0.01750 -0.0798 0.4043 1.0000
6.750 0.9733 0.02920 0.01952 -0.0753 0.2664 1.0000
7.000 1.0256 0.03319 0.02261 -0.0785 0.1779 1.0000
7.250 1.0845 0.03761 0.02690 -0.0823 0.1373 1.0000
7.500 1.1126 0.04079 0.03036 -0.0817 0.1163 1.0000
7.750 1.1426 0.04539 0.03548 -0.0809 0.1070 1.0000
8.000 1.1589 0.04899 0.03956 -0.0789 0.0956 1.0000
8.250 1.1727 0.05292 0.04397 -0.0764 0.0897 1.0000
8.500 1.1860 0.05784 0.04929 -0.0741 0.0878 1.0000
8.750 1.1856 0.06233 0.05448 -0.0701 0.0890 1.0000
9.000 1.1810 0.06693 0.05964 -0.0662 0.0901 1.0000
9.250 1.1710 0.07145 0.06463 -0.0625 0.0913 1.0000
9.500 1.1573 0.07603 0.06959 -0.0590 0.0930 1.0000
9.750 1.1424 0.08053 0.07436 -0.0560 0.0947 1.0000
10.000 1.1258 0.08484 0.07885 -0.0531 0.0960 1.0000
10.250 1.1110 0.08949 0.08364 -0.0510 0.0973 1.0000
10.500 1.1007 0.09473 0.08897 -0.0499 0.0984 1.0000
10.750 0.9285 0.09685 0.09168 -0.0438 0.1070 1.0000
11.000 0.9056 0.10384 0.09872 -0.0461 0.1098 1.0000
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Polar data table (+)
Polar graphs
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