MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 1,000,000 Max Cl/Cd: 69.64 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh25-il-1000000-n5.txt Download as CSV file: xf-mh25-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 25 9.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3956 0.06625 0.06456 -0.0810 0.9768 0.0050
-9.000 -0.4013 0.05929 0.05752 -0.0883 0.9724 0.0050
-8.750 -0.4119 0.05480 0.05292 -0.0892 0.9666 0.0048
-8.500 -0.4271 0.05094 0.04894 -0.0867 0.9602 0.0047
-8.250 -0.4302 0.04736 0.04522 -0.0850 0.9561 0.0048
-8.000 -0.4359 0.04367 0.04138 -0.0822 0.9521 0.0048
-7.750 -0.4318 0.04056 0.03811 -0.0798 0.9491 0.0051
-7.500 -0.4341 0.03665 0.03397 -0.0764 0.9456 0.0049
-7.250 -0.4298 0.03339 0.03048 -0.0734 0.9430 0.0049
-7.000 -0.4440 0.02458 0.02092 -0.0653 0.9387 0.0031
-6.500 -0.4192 0.02007 0.01588 -0.0603 0.9343 0.0027
-6.250 -0.4031 0.01784 0.01333 -0.0581 0.9324 0.0026
-6.000 -0.3834 0.01609 0.01131 -0.0565 0.9308 0.0025
-5.750 -0.3621 0.01448 0.00945 -0.0551 0.9292 0.0024
-5.500 -0.3399 0.01327 0.00807 -0.0539 0.9274 0.0023
-5.250 -0.3177 0.01229 0.00696 -0.0528 0.9254 0.0023
-5.000 -0.2951 0.01154 0.00612 -0.0518 0.9234 0.0023
-4.750 -0.2730 0.01080 0.00525 -0.0505 0.9213 0.0022
-4.500 -0.2501 0.01022 0.00457 -0.0495 0.9191 0.0022
-4.250 -0.2266 0.00974 0.00400 -0.0486 0.9170 0.0022
-4.000 -0.2028 0.00936 0.00356 -0.0477 0.9145 0.0022
-3.750 -0.1788 0.00903 0.00317 -0.0469 0.9116 0.0023
-3.500 -0.1539 0.00876 0.00286 -0.0463 0.9087 0.0023
-3.250 -0.1284 0.00852 0.00255 -0.0458 0.9060 0.0025
-3.000 -0.1022 0.00832 0.00229 -0.0455 0.9035 0.0028
-2.750 -0.0768 0.00815 0.00211 -0.0450 0.9001 0.0039
-2.500 -0.0527 0.00786 0.00193 -0.0443 0.8962 0.0272
-2.250 -0.0292 0.00748 0.00175 -0.0435 0.8925 0.0843
-2.000 -0.0064 0.00701 0.00158 -0.0427 0.8890 0.1742
-1.750 0.0102 0.00624 0.00145 -0.0408 0.8834 0.3521
-1.500 0.0300 0.00571 0.00130 -0.0394 0.8781 0.4738
-1.250 0.0510 0.00535 0.00121 -0.0381 0.8722 0.5587
-1.000 0.0695 0.00490 0.00110 -0.0362 0.8649 0.6623
-0.750 0.0875 0.00449 0.00103 -0.0340 0.8560 0.7583
-0.500 0.1089 0.00428 0.00105 -0.0324 0.8453 0.8371
-0.250 0.1346 0.00427 0.00105 -0.0318 0.8304 0.8659
0.000 0.1597 0.00431 0.00104 -0.0311 0.8090 0.8850
0.250 0.1841 0.00442 0.00105 -0.0302 0.7813 0.8965
0.500 0.2072 0.00457 0.00107 -0.0291 0.7492 0.9039
0.750 0.2294 0.00477 0.00113 -0.0279 0.7143 0.9094
1.000 0.2503 0.00497 0.00117 -0.0264 0.6778 0.9152
1.250 0.2725 0.00519 0.00127 -0.0251 0.6423 0.9197
1.500 0.2926 0.00543 0.00137 -0.0235 0.6055 0.9267
1.750 0.3135 0.00569 0.00150 -0.0220 0.5692 0.9327
2.000 0.3343 0.00594 0.00162 -0.0205 0.5324 0.9381
2.250 0.3546 0.00616 0.00170 -0.0190 0.4967 0.9421
2.500 0.3774 0.00638 0.00179 -0.0181 0.4617 0.9442
2.750 0.4000 0.00662 0.00189 -0.0172 0.4249 0.9461
3.000 0.4230 0.00684 0.00201 -0.0163 0.3916 0.9480
3.250 0.4457 0.00707 0.00211 -0.0155 0.3580 0.9500
3.500 0.4680 0.00730 0.00222 -0.0145 0.3251 0.9523
3.750 0.4894 0.00755 0.00234 -0.0134 0.2918 0.9548
4.000 0.5120 0.00779 0.00246 -0.0126 0.2614 0.9566
4.250 0.5359 0.00803 0.00262 -0.0120 0.2346 0.9581
4.500 0.5591 0.00832 0.00279 -0.0113 0.2029 0.9599
4.750 0.5828 0.00857 0.00296 -0.0107 0.1795 0.9619
5.000 0.6055 0.00886 0.00315 -0.0100 0.1521 0.9641
5.250 0.6274 0.00917 0.00335 -0.0090 0.1257 0.9665
5.500 0.6464 0.00956 0.00360 -0.0075 0.0923 0.9693
5.750 0.6718 0.00986 0.00384 -0.0074 0.0754 0.9707
6.000 0.6975 0.01015 0.00409 -0.0073 0.0616 0.9721
6.250 0.7229 0.01046 0.00436 -0.0072 0.0490 0.9737
6.500 0.7481 0.01079 0.00465 -0.0070 0.0376 0.9755
6.750 0.7730 0.01113 0.00496 -0.0068 0.0285 0.9775
7.000 0.7967 0.01149 0.00529 -0.0064 0.0207 0.9796
7.250 0.8187 0.01181 0.00560 -0.0055 0.0159 0.9822
7.500 0.8462 0.01220 0.00602 -0.0060 0.0115 0.9831
7.750 0.8740 0.01255 0.00639 -0.0065 0.0100 0.9839
8.000 0.9009 0.01299 0.00682 -0.0069 0.0072 0.9849
8.250 0.9280 0.01337 0.00724 -0.0072 0.0061 0.9858
8.500 0.9546 0.01377 0.00768 -0.0075 0.0049 0.9869
8.750 0.9787 0.01440 0.00830 -0.0075 0.0022 0.9884
9.000 1.0029 0.01497 0.00891 -0.0073 0.0014 0.9901
9.250 1.0257 0.01558 0.00961 -0.0069 0.0013 0.9921
9.500 1.0485 0.01604 0.01012 -0.0065 0.0011 0.9940
9.750 1.0727 0.01659 0.01077 -0.0065 0.0010 0.9958
10.000 1.0956 0.01725 0.01152 -0.0063 0.0010 0.9978
10.250 1.1172 0.01803 0.01241 -0.0059 0.0009 0.9996
10.500 1.1264 0.01849 0.01293 -0.0028 0.0009 1.0000
10.750 1.1326 0.01902 0.01354 0.0009 0.0008 1.0000
11.000 1.1411 0.01963 0.01422 0.0040 0.0008 1.0000
11.250 1.1490 0.02040 0.01510 0.0071 0.0008 1.0000
11.500 1.1591 0.02109 0.01587 0.0097 0.0007 1.0000
11.750 1.1681 0.02191 0.01678 0.0123 0.0007 1.0000
12.000 1.1740 0.02298 0.01799 0.0153 0.0007 1.0000
12.250 1.1790 0.02416 0.01932 0.0182 0.0006 1.0000
12.500 1.1861 0.02519 0.02046 0.0207 0.0006 1.0000
12.750 1.1886 0.02657 0.02199 0.0236 0.0006 1.0000
13.000 1.1891 0.02813 0.02370 0.0265 0.0005 1.0000
13.250 1.1871 0.02992 0.02566 0.0294 0.0005 1.0000
13.500 1.1831 0.03194 0.02785 0.0322 0.0005 1.0000
13.750 1.1858 0.03350 0.02952 0.0340 0.0005 1.0000
14.000 1.1797 0.03589 0.03207 0.0361 0.0005 1.0000
14.250 1.1691 0.03887 0.03524 0.0380 0.0005 1.0000
14.500 1.1767 0.04028 0.03670 0.0385 0.0005 1.0000
14.750 1.1496 0.04553 0.04222 0.0393 0.0005 1.0000
15.000 1.1334 0.05022 0.04709 0.0387 0.0005 1.0000
15.250 1.1325 0.05332 0.05029 0.0378 0.0005 1.0000
15.500 1.1375 0.05576 0.05278 0.0370 0.0005 1.0000
15.750 1.1070 0.06413 0.06137 0.0330 0.0005 1.0000
16.000 1.0869 0.07165 0.06905 0.0289 0.0005 1.0000
16.250 1.1073 0.07175 0.06913 0.0290 0.0004 1.0000
16.500 1.0658 0.08411 0.08170 0.0220 0.0004 1.0000
16.750 1.0325 0.09531 0.09306 0.0159 0.0004 1.0000
17.000 0.9847 0.10996 0.10787 0.0086 0.0005 1.0000
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Polar data table (+)
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