MH 120 11.57% (mh120-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 120 11.57% (mh120-il) Reynolds number: 200,000 Max Cl/Cd: 73.15 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh120-il-200000-n5.txt Download as CSV file: xf-mh120-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4185 0.08958 0.08611 -0.0422 1.0000 0.0186
-9.500 -0.4228 0.08554 0.08212 -0.0434 1.0000 0.0182
-9.250 -0.4313 0.08065 0.07730 -0.0451 1.0000 0.0178
-9.000 -0.4411 0.07581 0.07252 -0.0472 1.0000 0.0174
-8.750 -0.4549 0.07052 0.06731 -0.0502 1.0000 0.0169
-8.500 -0.4813 0.06529 0.06210 -0.0521 1.0000 0.0168
-8.250 -0.5103 0.06241 0.05921 -0.0483 1.0000 0.0168
-8.000 -0.5116 0.05487 0.05142 -0.0532 0.9912 0.0163
-7.750 -0.5078 0.04823 0.04442 -0.0561 0.9809 0.0160
-7.500 -0.4980 0.04254 0.03830 -0.0576 0.9724 0.0159
-7.250 -0.4875 0.03793 0.03324 -0.0573 0.9627 0.0158
-7.000 -0.4707 0.03409 0.02894 -0.0572 0.9556 0.0160
-6.750 -0.4500 0.03142 0.02587 -0.0571 0.9485 0.0171
-6.500 -0.4256 0.02894 0.02293 -0.0572 0.9426 0.0181
-6.250 -0.4021 0.02661 0.02018 -0.0568 0.9352 0.0185
-6.000 -0.3714 0.02427 0.01741 -0.0578 0.9311 0.0187
-5.750 -0.3459 0.02264 0.01548 -0.0575 0.9226 0.0189
-5.500 -0.3117 0.02109 0.01363 -0.0588 0.9179 0.0193
-5.250 -0.2828 0.01993 0.01226 -0.0590 0.9096 0.0197
-5.000 -0.2500 0.01813 0.01029 -0.0603 0.9040 0.0209
-4.750 -0.2222 0.01714 0.00925 -0.0606 0.8950 0.0222
-4.500 -0.1895 0.01618 0.00820 -0.0617 0.8880 0.0227
-4.250 -0.1626 0.01544 0.00738 -0.0615 0.8781 0.0230
-4.000 -0.1355 0.01479 0.00664 -0.0614 0.8684 0.0235
-3.750 -0.1069 0.01424 0.00597 -0.0616 0.8593 0.0241
-3.500 -0.0808 0.01380 0.00538 -0.0612 0.8486 0.0252
-3.250 -0.0549 0.01344 0.00489 -0.0607 0.8378 0.0264
-3.000 -0.0282 0.01316 0.00447 -0.0604 0.8272 0.0276
-2.750 -0.0014 0.01286 0.00408 -0.0601 0.8169 0.0312
-2.500 0.0234 0.01252 0.00376 -0.0594 0.8060 0.0489
-2.250 0.0369 0.01130 0.00343 -0.0571 0.7948 0.2700
-2.000 0.0530 0.01061 0.00332 -0.0548 0.7841 0.4310
-1.750 0.0738 0.01029 0.00322 -0.0533 0.7742 0.5134
-1.500 0.0943 0.01001 0.00314 -0.0516 0.7641 0.5874
-1.250 0.1139 0.00966 0.00312 -0.0495 0.7541 0.6878
-1.000 0.1449 0.00943 0.00309 -0.0499 0.7451 0.7672
-0.750 0.2362 0.00934 0.00319 -0.0633 0.7368 0.8820
-0.500 0.2860 0.00943 0.00317 -0.0680 0.7274 0.9040
-0.250 0.3289 0.00955 0.00318 -0.0711 0.7179 0.9210
0.000 0.3670 0.00968 0.00322 -0.0733 0.7083 0.9356
0.250 0.4021 0.00980 0.00327 -0.0748 0.6986 0.9489
0.500 0.4363 0.00994 0.00332 -0.0761 0.6893 0.9608
0.750 0.4710 0.01008 0.00338 -0.0777 0.6797 0.9715
1.000 0.5083 0.01018 0.00343 -0.0798 0.6697 0.9803
1.250 0.5454 0.01029 0.00348 -0.0819 0.6602 0.9885
1.500 0.5835 0.01040 0.00353 -0.0843 0.6500 0.9956
1.750 0.6181 0.01045 0.00355 -0.0861 0.6389 1.0000
2.000 0.6383 0.01052 0.00358 -0.0846 0.6278 1.0000
2.250 0.6587 0.01060 0.00363 -0.0831 0.6163 1.0000
2.500 0.6793 0.01069 0.00368 -0.0817 0.6051 1.0000
2.750 0.7000 0.01079 0.00375 -0.0803 0.5941 1.0000
3.000 0.7209 0.01089 0.00385 -0.0789 0.5832 1.0000
3.250 0.7419 0.01101 0.00396 -0.0776 0.5726 1.0000
3.500 0.7629 0.01114 0.00410 -0.0762 0.5618 1.0000
3.750 0.7836 0.01128 0.00422 -0.0748 0.5498 1.0000
4.000 0.8042 0.01143 0.00437 -0.0733 0.5374 1.0000
4.250 0.8248 0.01158 0.00454 -0.0719 0.5247 1.0000
4.500 0.8450 0.01175 0.00471 -0.0704 0.5109 1.0000
4.750 0.8649 0.01194 0.00493 -0.0688 0.4961 1.0000
5.000 0.8844 0.01215 0.00513 -0.0671 0.4799 1.0000
5.250 0.9037 0.01236 0.00536 -0.0654 0.4620 1.0000
5.500 0.9224 0.01261 0.00560 -0.0637 0.4433 1.0000
5.750 0.9405 0.01289 0.00586 -0.0617 0.4237 1.0000
6.000 0.9581 0.01319 0.00618 -0.0598 0.4011 1.0000
6.250 0.9738 0.01357 0.00650 -0.0575 0.3733 1.0000
6.500 0.9829 0.01420 0.00688 -0.0540 0.3229 1.0000
6.750 0.9896 0.01501 0.00738 -0.0503 0.2692 1.0000
7.000 0.9972 0.01585 0.00795 -0.0468 0.2216 1.0000
7.250 1.0094 0.01649 0.00849 -0.0441 0.1935 1.0000
7.500 1.0187 0.01729 0.00912 -0.0410 0.1582 1.0000
7.750 1.0260 0.01821 0.00982 -0.0377 0.1213 1.0000
8.000 1.0317 0.01915 0.01061 -0.0341 0.0872 1.0000
8.250 1.0327 0.02025 0.01146 -0.0298 0.0512 1.0000
8.500 1.0306 0.02160 0.01257 -0.0251 0.0203 1.0000
8.750 1.0373 0.02257 0.01353 -0.0219 0.0142 1.0000
9.000 1.0464 0.02345 0.01448 -0.0192 0.0122 1.0000
9.250 1.0568 0.02429 0.01544 -0.0169 0.0117 1.0000
9.500 1.0652 0.02532 0.01658 -0.0144 0.0106 1.0000
9.750 1.0733 0.02641 0.01780 -0.0120 0.0100 1.0000
10.000 1.0788 0.02773 0.01925 -0.0096 0.0094 1.0000
10.250 1.0832 0.02919 0.02084 -0.0073 0.0090 1.0000
10.500 1.0843 0.03097 0.02280 -0.0049 0.0087 1.0000
10.750 1.0876 0.03266 0.02461 -0.0030 0.0086 1.0000
11.000 1.0906 0.03447 0.02656 -0.0012 0.0084 1.0000
11.250 1.0922 0.03650 0.02872 0.0004 0.0083 1.0000
11.500 1.0947 0.03854 0.03088 0.0017 0.0082 1.0000
11.750 1.0973 0.04065 0.03312 0.0029 0.0081 1.0000
12.000 1.0993 0.04291 0.03553 0.0040 0.0076 1.0000
12.250 1.1019 0.04518 0.03792 0.0049 0.0075 1.0000
12.500 1.1058 0.04733 0.04020 0.0055 0.0074 1.0000
12.750 1.1068 0.04989 0.04289 0.0060 0.0066 1.0000
13.000 1.1072 0.05258 0.04572 0.0065 0.0065 1.0000
13.250 1.1083 0.05527 0.04855 0.0072 0.0068 1.0000
13.500 1.1071 0.05830 0.05172 0.0073 0.0063 1.0000
13.750 1.1070 0.06124 0.05482 0.0074 0.0064 1.0000
14.000 1.1036 0.06472 0.05849 0.0072 0.0061 1.0000
14.250 1.1009 0.06824 0.06219 0.0070 0.0062 1.0000
14.500 1.0961 0.07212 0.06624 0.0064 0.0061 1.0000
14.750 1.0894 0.07643 0.07072 0.0055 0.0060 1.0000
15.000 1.0835 0.08074 0.07522 0.0044 0.0061 1.0000
15.250 1.0738 0.08581 0.08045 0.0027 0.0059 1.0000
15.500 1.0649 0.09092 0.08575 0.0008 0.0059 1.0000
15.750 1.0532 0.09674 0.09173 -0.0016 0.0058 1.0000
16.000 1.0417 0.10284 0.09803 -0.0043 0.0059 1.0000
16.250 1.0294 0.10929 0.10469 -0.0074 0.0060 1.0000
16.500 1.0143 0.11662 0.11220 -0.0111 0.0061 1.0000
16.750 0.9985 0.12448 0.12023 -0.0154 0.0060 1.0000
17.000 0.9846 0.13228 0.12819 -0.0197 0.0061 1.0000
17.250 0.9653 0.14185 0.13793 -0.0250 0.0062 1.0000
17.500 0.9480 0.15150 0.14773 -0.0305 0.0063 1.0000
17.750 0.9227 0.16446 0.16081 -0.0375 0.0066 1.0000
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Polar data table (+)
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