MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 100,000 Max Cl/Cd: 44.97 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh62-il-100000.txt Download as CSV file: xf-mh62-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5351 0.09690 0.09259 0.0064 1.0000 0.1083
-8.250 -0.5342 0.09331 0.08906 0.0040 1.0000 0.1130
-8.000 -0.5717 0.08890 0.08479 -0.0095 1.0000 0.1164
-7.750 -0.5387 0.08498 0.08088 -0.0015 1.0000 0.1203
-7.500 -0.5372 0.08125 0.07721 -0.0035 1.0000 0.1257
-7.250 -0.5498 0.07544 0.07143 -0.0126 1.0000 0.1319
-7.000 -0.5333 0.07228 0.06827 -0.0106 1.0000 0.1364
-6.750 -0.5353 0.06700 0.06293 -0.0167 1.0000 0.1462
-6.500 -0.5211 0.06341 0.05935 -0.0168 1.0000 0.1512
-6.250 -0.5240 0.04322 0.03768 -0.0291 1.0000 0.0611
-6.000 -0.5072 0.03738 0.03097 -0.0285 1.0000 0.0497
-5.750 -0.4891 0.03317 0.02643 -0.0280 1.0000 0.0472
-5.500 -0.4696 0.02973 0.02251 -0.0271 1.0000 0.0452
-5.250 -0.4506 0.02697 0.01924 -0.0255 1.0000 0.0442
-5.000 -0.4342 0.02489 0.01682 -0.0234 1.0000 0.0442
-4.750 -0.4188 0.02318 0.01488 -0.0212 1.0000 0.0453
-4.500 -0.4032 0.02199 0.01347 -0.0190 1.0000 0.0491
-4.250 -0.3878 0.02039 0.01183 -0.0170 1.0000 0.0540
-4.000 -0.3715 0.01918 0.01059 -0.0150 1.0000 0.0611
-3.750 -0.3560 0.01787 0.00933 -0.0130 1.0000 0.0775
-3.500 -0.3414 0.01614 0.00810 -0.0110 1.0000 0.1417
-3.250 -0.3281 0.01469 0.00770 -0.0092 1.0000 0.3333
-3.000 -0.2910 0.01427 0.00761 -0.0115 0.9909 0.4528
-2.750 -0.2513 0.01388 0.00759 -0.0139 0.9817 0.5631
-2.500 -0.2142 0.01345 0.00754 -0.0152 0.9720 0.6720
-2.250 -0.1725 0.01311 0.00757 -0.0165 0.9643 0.8041
-2.000 -0.0794 0.01309 0.00746 -0.0272 0.9657 0.9453
-1.750 0.0208 0.01297 0.00696 -0.0411 0.9676 1.0000
-1.500 0.0721 0.01288 0.00661 -0.0465 0.9559 1.0000
-1.250 0.1154 0.01285 0.00639 -0.0500 0.9422 1.0000
-1.000 0.1495 0.01290 0.00629 -0.0515 0.9267 1.0000
-0.750 0.1756 0.01303 0.00627 -0.0512 0.9101 1.0000
-0.500 0.1977 0.01320 0.00633 -0.0500 0.8939 1.0000
-0.250 0.2176 0.01338 0.00641 -0.0482 0.8780 1.0000
0.000 0.2364 0.01357 0.00650 -0.0461 0.8627 1.0000
0.250 0.2550 0.01375 0.00658 -0.0438 0.8477 1.0000
0.500 0.2737 0.01391 0.00666 -0.0415 0.8330 1.0000
0.750 0.2928 0.01405 0.00672 -0.0393 0.8184 1.0000
1.000 0.3128 0.01420 0.00680 -0.0373 0.8029 1.0000
1.250 0.3334 0.01433 0.00688 -0.0354 0.7872 1.0000
1.500 0.3543 0.01443 0.00694 -0.0335 0.7714 1.0000
1.750 0.3755 0.01451 0.00697 -0.0316 0.7556 1.0000
2.000 0.3972 0.01457 0.00697 -0.0298 0.7398 1.0000
2.250 0.4193 0.01460 0.00696 -0.0280 0.7239 1.0000
2.500 0.4418 0.01462 0.00694 -0.0262 0.7079 1.0000
2.750 0.4651 0.01467 0.00698 -0.0248 0.6895 1.0000
3.000 0.4886 0.01470 0.00698 -0.0234 0.6708 1.0000
3.250 0.5122 0.01469 0.00692 -0.0218 0.6529 1.0000
3.500 0.5365 0.01476 0.00700 -0.0207 0.6318 1.0000
3.750 0.5607 0.01478 0.00698 -0.0193 0.6116 1.0000
4.000 0.5853 0.01489 0.00707 -0.0183 0.5885 1.0000
4.250 0.6099 0.01499 0.00712 -0.0171 0.5658 1.0000
4.500 0.6345 0.01514 0.00725 -0.0161 0.5418 1.0000
4.750 0.6592 0.01537 0.00744 -0.0152 0.5158 1.0000
5.000 0.6838 0.01565 0.00768 -0.0143 0.4894 1.0000
5.250 0.7083 0.01598 0.00797 -0.0135 0.4623 1.0000
5.500 0.7327 0.01639 0.00833 -0.0127 0.4347 1.0000
5.750 0.7568 0.01684 0.00877 -0.0119 0.4066 1.0000
6.000 0.7807 0.01736 0.00924 -0.0112 0.3785 1.0000
6.250 0.8042 0.01793 0.00976 -0.0105 0.3501 1.0000
6.500 0.8275 0.01857 0.01035 -0.0097 0.3219 1.0000
6.750 0.8504 0.01926 0.01101 -0.0090 0.2943 1.0000
7.000 0.8728 0.02001 0.01173 -0.0083 0.2672 1.0000
7.250 0.8948 0.02084 0.01261 -0.0076 0.2412 1.0000
7.500 0.9162 0.02173 0.01350 -0.0068 0.2159 1.0000
7.750 0.9369 0.02273 0.01445 -0.0060 0.1922 1.0000
8.000 0.9567 0.02380 0.01542 -0.0052 0.1689 1.0000
8.250 0.9753 0.02493 0.01664 -0.0042 0.1448 1.0000
8.500 0.9927 0.02634 0.01809 -0.0032 0.1224 1.0000
8.750 1.0087 0.02793 0.01949 -0.0022 0.1023 1.0000
9.000 1.0248 0.02984 0.02159 -0.0008 0.0857 1.0000
9.250 1.0396 0.03170 0.02354 0.0004 0.0722 1.0000
9.500 1.0563 0.03436 0.02626 0.0016 0.0630 1.0000
9.750 1.0695 0.03620 0.02831 0.0029 0.0548 1.0000
10.000 1.0812 0.03956 0.03198 0.0043 0.0493 1.0000
10.250 1.0903 0.04197 0.03466 0.0058 0.0443 1.0000
10.500 1.0953 0.04568 0.03848 0.0069 0.0403 1.0000
10.750 1.0925 0.04892 0.04222 0.0089 0.0386 1.0000
11.000 1.0847 0.05248 0.04616 0.0107 0.0380 1.0000
11.250 1.0698 0.05608 0.05007 0.0124 0.0375 1.0000
11.500 1.0537 0.06000 0.05426 0.0129 0.0375 1.0000
11.750 1.0359 0.06446 0.05896 0.0121 0.0376 1.0000
12.000 1.0152 0.06969 0.06441 0.0102 0.0379 1.0000
12.250 0.9950 0.07544 0.07035 0.0072 0.0383 1.0000
12.500 0.9749 0.08186 0.07692 0.0033 0.0389 1.0000
12.750 0.9517 0.08953 0.08472 -0.0018 0.0394 1.0000
13.000 0.9298 0.09785 0.09312 -0.0073 0.0401 1.0000
13.250 0.9149 0.10547 0.10077 -0.0115 0.0408 1.0000
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Polar data table (+)
Polar graphs
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