MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 50,000 Max Cl/Cd: 14.87 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh106-il-50000.txt Download as CSV file: xf-mh106-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 106 13.07%
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6387 0.10008 0.09365 -0.0076 1.0000 0.1053
-10.500 -0.6228 0.09812 0.09173 -0.0053 1.0000 0.1088
-10.250 -0.7104 0.07965 0.07319 -0.0227 1.0000 0.0916
-10.000 -0.7225 0.07463 0.06814 -0.0239 1.0000 0.0905
-9.750 -0.7411 0.07006 0.06351 -0.0240 1.0000 0.0894
-9.500 -0.7595 0.06569 0.05899 -0.0232 1.0000 0.0880
-9.250 -0.7738 0.06127 0.05432 -0.0221 1.0000 0.0867
-9.000 -0.7835 0.05695 0.04968 -0.0207 1.0000 0.0861
-8.750 -0.7866 0.05295 0.04530 -0.0190 1.0000 0.0862
-8.500 -0.7843 0.04923 0.04118 -0.0172 1.0000 0.0870
-8.250 -0.7775 0.04580 0.03729 -0.0153 1.0000 0.0887
-8.000 -0.7666 0.04253 0.03351 -0.0134 1.0000 0.0906
-7.750 -0.7505 0.03929 0.02979 -0.0117 1.0000 0.0930
-7.500 -0.7271 0.03633 0.02687 -0.0109 1.0000 0.0989
-7.250 -0.7055 0.03377 0.02416 -0.0097 1.0000 0.1087
-7.000 -0.6827 0.03133 0.02178 -0.0085 1.0000 0.1234
-6.750 -0.6638 0.02912 0.01970 -0.0067 1.0000 0.1490
-6.500 -0.6528 0.02698 0.01807 -0.0038 1.0000 0.2019
-6.250 -0.6552 0.02567 0.01768 0.0016 1.0000 0.3059
-6.000 -0.6496 0.02596 0.01833 0.0067 1.0000 0.3821
-5.750 -0.6362 0.02636 0.01888 0.0106 1.0000 0.4331
-5.500 -0.6192 0.02670 0.01938 0.0142 1.0000 0.4759
-5.250 -0.6036 0.02647 0.01914 0.0174 1.0000 0.5105
-5.000 -0.5844 0.02612 0.01880 0.0200 1.0000 0.5382
-4.750 -0.5661 0.02561 0.01832 0.0223 1.0000 0.5619
-4.500 -0.5536 0.02490 0.01754 0.0248 1.0000 0.5850
-4.250 -0.5389 0.02446 0.01715 0.0273 1.0000 0.6055
-4.000 -0.5314 0.02396 0.01662 0.0303 1.0000 0.6267
-3.750 -0.5242 0.02361 0.01628 0.0331 1.0000 0.6473
-3.500 -0.5169 0.02335 0.01600 0.0357 1.0000 0.6696
-3.250 -0.5083 0.02319 0.01584 0.0379 1.0000 0.6934
-3.000 -0.4764 0.02330 0.01592 0.0364 0.9909 0.7256
-2.750 -0.4045 0.02378 0.01629 0.0289 0.9679 0.7690
-2.500 -0.3248 0.02443 0.01675 0.0208 0.9460 0.8111
-2.250 -0.2158 0.02523 0.01725 0.0080 0.9286 0.8517
-2.000 -0.0776 0.02567 0.01732 -0.0099 0.9118 0.8834
-1.750 0.0270 0.02548 0.01685 -0.0231 0.8883 0.9135
-1.500 0.1075 0.02506 0.01618 -0.0327 0.8634 0.9429
-1.250 0.1783 0.02447 0.01537 -0.0412 0.8387 0.9724
-1.000 0.2458 0.02363 0.01435 -0.0503 0.8154 1.0000
-0.750 0.2582 0.02365 0.01427 -0.0495 0.7981 1.0000
-0.500 0.2714 0.02376 0.01429 -0.0488 0.7827 1.0000
-0.250 0.2853 0.02395 0.01441 -0.0480 0.7686 1.0000
0.000 0.3004 0.02423 0.01462 -0.0473 0.7554 1.0000
0.250 0.3163 0.02459 0.01492 -0.0466 0.7436 1.0000
0.500 0.3321 0.02495 0.01520 -0.0454 0.7329 1.0000
0.750 0.3483 0.02545 0.01569 -0.0447 0.7217 1.0000
1.000 0.3643 0.02610 0.01632 -0.0440 0.7111 1.0000
1.250 0.3806 0.02668 0.01686 -0.0428 0.7019 1.0000
1.500 0.3966 0.02739 0.01755 -0.0418 0.6921 1.0000
1.750 0.4119 0.02830 0.01850 -0.0411 0.6827 1.0000
2.000 0.4293 0.02888 0.01902 -0.0394 0.6747 1.0000
2.250 0.4427 0.03007 0.02026 -0.0389 0.6646 1.0000
2.500 0.4574 0.03107 0.02127 -0.0377 0.6560 1.0000
2.750 0.4733 0.03196 0.02217 -0.0363 0.6473 1.0000
3.000 0.4839 0.03341 0.02368 -0.0353 0.6380 1.0000
3.250 0.5043 0.03400 0.02424 -0.0336 0.6302 1.0000
3.500 0.5100 0.03585 0.02617 -0.0326 0.6201 1.0000
3.750 0.5214 0.03723 0.02759 -0.0312 0.6109 1.0000
4.000 0.5391 0.03817 0.02856 -0.0296 0.6021 1.0000
4.250 0.5409 0.04029 0.03074 -0.0282 0.5917 1.0000
4.500 0.5536 0.04168 0.03216 -0.0267 0.5823 1.0000
4.750 0.5729 0.04255 0.03308 -0.0250 0.5722 1.0000
5.000 0.5671 0.04525 0.03581 -0.0235 0.5613 1.0000
5.250 0.5731 0.04714 0.03774 -0.0219 0.5506 1.0000
5.500 0.5946 0.04799 0.03868 -0.0202 0.5397 1.0000
5.750 0.6108 0.04913 0.03990 -0.0185 0.5276 1.0000
6.000 0.5957 0.05260 0.04337 -0.0171 0.5161 1.0000
6.250 0.5939 0.05512 0.04591 -0.0156 0.5042 1.0000
6.500 0.6011 0.05707 0.04790 -0.0141 0.4916 1.0000
6.750 0.6128 0.05874 0.04965 -0.0127 0.4787 1.0000
7.000 0.6248 0.06033 0.05133 -0.0111 0.4649 1.0000
7.250 0.6387 0.06182 0.05291 -0.0095 0.4513 1.0000
7.500 0.6498 0.06341 0.05457 -0.0078 0.4371 1.0000
7.750 0.6621 0.06495 0.05620 -0.0061 0.4230 1.0000
8.000 0.6196 0.07081 0.06191 -0.0062 0.4147 1.0000
8.250 0.6229 0.07334 0.06449 -0.0053 0.4013 1.0000
8.500 0.6274 0.07589 0.06709 -0.0046 0.3884 1.0000
8.750 0.6341 0.07824 0.06950 -0.0038 0.3747 1.0000
9.000 0.6435 0.08053 0.07189 -0.0030 0.3619 1.0000
9.250 0.6536 0.08270 0.07415 -0.0021 0.3484 1.0000
9.500 0.6638 0.08475 0.07628 -0.0012 0.3346 1.0000
9.750 0.6379 0.09095 0.08241 -0.0034 0.3298 1.0000
10.000 0.6474 0.09364 0.08518 -0.0030 0.3188 1.0000
10.250 0.6576 0.09588 0.08749 -0.0023 0.3055 1.0000
10.500 0.6390 0.10164 0.09322 -0.0045 0.3015 1.0000
10.750 0.6295 0.10709 0.09867 -0.0065 0.3008 1.0000
11.000 0.6219 0.11248 0.10408 -0.0084 0.3023 1.0000
11.250 0.6170 0.11757 0.10919 -0.0102 0.3033 1.0000
11.500 0.6264 0.12291 0.11461 -0.0115 0.3070 1.0000
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Polar data table (+)
Polar graphs
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