MH 42 8.94% (mh42-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 42 8.94% (mh42-il) Reynolds number: 100,000 Max Cl/Cd: 49.92 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh42-il-100000.txt Download as CSV file: xf-mh42-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 42 8.94%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4083 0.10082 0.09643 -0.0059 1.0000 0.0945
-9.000 -0.4166 0.09706 0.09272 -0.0090 1.0000 0.0982
-8.750 -0.4334 0.09331 0.08905 -0.0138 1.0000 0.0993
-8.500 -0.4077 0.08856 0.08429 -0.0101 1.0000 0.1050
-8.250 -0.4123 0.08469 0.08048 -0.0123 1.0000 0.1106
-8.000 -0.4314 0.08069 0.07657 -0.0174 1.0000 0.1124
-7.750 -0.4156 0.07594 0.07185 -0.0152 1.0000 0.1168
-7.500 -0.4142 0.07210 0.06805 -0.0160 1.0000 0.1217
-7.250 -0.4367 0.06784 0.06388 -0.0217 1.0000 0.1252
-7.000 -0.4634 0.06206 0.05797 -0.0307 1.0000 0.1266
-6.750 -0.5057 0.06778 0.06320 -0.0328 1.0000 0.1268
-6.500 -0.4813 0.06455 0.06028 -0.0269 1.0000 0.1335
-6.250 -0.4308 0.04925 0.04535 -0.0276 1.0000 0.1458
-6.000 -0.4321 0.04429 0.04030 -0.0302 1.0000 0.1563
-5.750 -0.4568 0.04006 0.03424 -0.0363 1.0000 0.0566
-5.500 -0.4418 0.03598 0.02911 -0.0341 1.0000 0.0478
-5.250 -0.4284 0.03195 0.02485 -0.0326 1.0000 0.0465
-5.000 -0.4139 0.02880 0.02134 -0.0306 1.0000 0.0455
-4.750 -0.3982 0.02629 0.01843 -0.0284 1.0000 0.0452
-4.500 -0.3813 0.02417 0.01593 -0.0262 1.0000 0.0458
-4.250 -0.3634 0.02258 0.01395 -0.0240 1.0000 0.0476
-4.000 -0.3471 0.02068 0.01211 -0.0225 1.0000 0.0540
-3.750 -0.3294 0.01923 0.01060 -0.0207 1.0000 0.0639
-3.500 -0.3119 0.01813 0.00943 -0.0189 1.0000 0.0861
-3.250 -0.2950 0.01690 0.00848 -0.0174 1.0000 0.1249
-3.000 -0.2788 0.01531 0.00764 -0.0159 1.0000 0.2402
-2.750 -0.2547 0.01436 0.00744 -0.0162 0.9965 0.3930
-2.500 -0.2211 0.01332 0.00755 -0.0170 0.9870 0.6482
-2.250 -0.1688 0.01299 0.00777 -0.0189 0.9834 0.9124
-2.000 -0.0792 0.01303 0.00731 -0.0309 0.9840 1.0000
-1.750 -0.0278 0.01313 0.00709 -0.0364 0.9727 1.0000
-1.500 0.0234 0.01321 0.00690 -0.0416 0.9621 1.0000
-1.250 0.0795 0.01323 0.00667 -0.0475 0.9533 1.0000
-1.000 0.1289 0.01321 0.00648 -0.0520 0.9424 1.0000
-0.750 0.1722 0.01319 0.00632 -0.0552 0.9297 1.0000
-0.500 0.2106 0.01320 0.00619 -0.0573 0.9161 1.0000
-0.250 0.2432 0.01323 0.00613 -0.0581 0.9019 1.0000
0.000 0.2710 0.01331 0.00612 -0.0579 0.8874 1.0000
0.250 0.2951 0.01342 0.00615 -0.0568 0.8726 1.0000
0.500 0.3168 0.01358 0.00623 -0.0553 0.8573 1.0000
0.750 0.3383 0.01373 0.00632 -0.0538 0.8424 1.0000
1.000 0.3597 0.01389 0.00642 -0.0521 0.8278 1.0000
1.250 0.3812 0.01404 0.00653 -0.0505 0.8134 1.0000
1.500 0.4029 0.01419 0.00665 -0.0489 0.7991 1.0000
1.750 0.4250 0.01435 0.00676 -0.0473 0.7848 1.0000
2.000 0.4473 0.01449 0.00688 -0.0458 0.7703 1.0000
2.250 0.4700 0.01464 0.00699 -0.0443 0.7558 1.0000
2.500 0.4930 0.01477 0.00715 -0.0429 0.7410 1.0000
2.750 0.5163 0.01490 0.00727 -0.0415 0.7260 1.0000
3.000 0.5398 0.01502 0.00737 -0.0401 0.7108 1.0000
3.250 0.5636 0.01512 0.00746 -0.0388 0.6954 1.0000
3.500 0.5873 0.01526 0.00762 -0.0375 0.6781 1.0000
3.750 0.6112 0.01539 0.00781 -0.0363 0.6600 1.0000
4.000 0.6355 0.01547 0.00789 -0.0350 0.6422 1.0000
4.250 0.6596 0.01557 0.00802 -0.0338 0.6227 1.0000
4.500 0.6838 0.01566 0.00813 -0.0326 0.6020 1.0000
4.750 0.7079 0.01575 0.00831 -0.0313 0.5796 1.0000
5.000 0.7321 0.01583 0.00837 -0.0301 0.5565 1.0000
5.250 0.7559 0.01593 0.00849 -0.0288 0.5306 1.0000
5.500 0.7793 0.01608 0.00867 -0.0276 0.5010 1.0000
5.750 0.8021 0.01627 0.00889 -0.0263 0.4678 1.0000
6.000 0.8244 0.01654 0.00914 -0.0250 0.4314 1.0000
6.250 0.8457 0.01694 0.00948 -0.0237 0.3891 1.0000
6.500 0.8657 0.01752 0.01001 -0.0223 0.3419 1.0000
6.750 0.8843 0.01835 0.01066 -0.0209 0.2898 1.0000
7.000 0.9013 0.01945 0.01152 -0.0194 0.2369 1.0000
7.250 0.9168 0.02084 0.01259 -0.0180 0.1902 1.0000
7.500 0.9320 0.02241 0.01392 -0.0164 0.1501 1.0000
7.750 0.9475 0.02402 0.01543 -0.0149 0.1172 1.0000
8.000 0.9634 0.02605 0.01728 -0.0134 0.0957 1.0000
8.250 0.9811 0.02794 0.01923 -0.0119 0.0792 1.0000
8.500 0.9999 0.03014 0.02145 -0.0107 0.0677 1.0000
8.750 1.0211 0.03321 0.02444 -0.0099 0.0594 1.0000
9.000 1.0366 0.03479 0.02651 -0.0082 0.0516 1.0000
9.250 1.0538 0.03892 0.03079 -0.0072 0.0469 1.0000
9.500 1.0641 0.04126 0.03366 -0.0052 0.0422 1.0000
9.750 1.0750 0.04379 0.03635 -0.0038 0.0384 1.0000
10.000 1.0805 0.04877 0.04161 -0.0025 0.0368 1.0000
10.250 1.0781 0.05384 0.04711 -0.0007 0.0365 1.0000
10.500 1.0714 0.05827 0.05192 0.0011 0.0364 1.0000
10.750 1.0584 0.06209 0.05604 0.0031 0.0362 1.0000
11.000 1.0435 0.06593 0.06010 0.0049 0.0363 1.0000
11.500 0.9179 0.06621 0.06137 0.0076 0.0392 1.0000
11.750 0.8781 0.07430 0.06973 0.0038 0.0409 1.0000
12.000 0.8451 0.08285 0.07845 -0.0009 0.0425 1.0000
12.250 0.8171 0.09172 0.08742 -0.0056 0.0448 1.0000
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Polar data table (+)
Polar graphs
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