MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 200,000 Max Cl/Cd: 72.32 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh32-il-200000.txt Download as CSV file: xf-mh32-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4131 0.09781 0.09428 -0.0256 1.0000 0.0343
-8.750 -0.4150 0.09415 0.09068 -0.0296 1.0000 0.0357
-8.500 -0.4154 0.09068 0.08726 -0.0326 1.0000 0.0361
-8.250 -0.3513 0.07511 0.07200 -0.0352 1.0000 0.0379
-8.000 -0.3471 0.07188 0.06879 -0.0345 1.0000 0.0388
-7.750 -0.3472 0.06850 0.06546 -0.0346 1.0000 0.0397
-7.500 -0.3518 0.06510 0.06211 -0.0349 1.0000 0.0404
-7.250 -0.4378 0.07053 0.06725 -0.0456 1.0000 0.0367
-7.000 -0.4466 0.06576 0.06257 -0.0437 1.0000 0.0377
-6.750 -0.4488 0.06356 0.06042 -0.0411 1.0000 0.0385
-6.500 -0.4512 0.06118 0.05804 -0.0394 1.0000 0.0392
-6.250 -0.4526 0.05854 0.05538 -0.0381 1.0000 0.0400
-6.000 -0.4521 0.05568 0.05246 -0.0372 1.0000 0.0413
-5.750 -0.4491 0.05244 0.04911 -0.0367 1.0000 0.0429
-5.500 -0.4426 0.04879 0.04527 -0.0368 1.0000 0.0456
-5.250 -0.4356 0.04383 0.03969 -0.0375 1.0000 0.0502
-5.000 -0.4166 0.04049 0.03641 -0.0382 0.9985 0.0521
-4.750 -0.3826 0.03701 0.03271 -0.0415 0.9945 0.0558
-4.500 -0.3442 0.02713 0.02151 -0.0418 0.9914 0.0226
-4.250 -0.3102 0.02293 0.01664 -0.0430 0.9876 0.0196
-4.000 -0.2734 0.02000 0.01307 -0.0441 0.9845 0.0183
-3.750 -0.2346 0.01816 0.01094 -0.0459 0.9817 0.0194
-3.500 -0.2012 0.01728 0.00991 -0.0469 0.9758 0.0233
-3.250 -0.1646 0.01567 0.00823 -0.0485 0.9717 0.0300
-3.000 -0.1250 0.01439 0.00693 -0.0507 0.9682 0.0512
-2.750 -0.0956 0.01275 0.00605 -0.0515 0.9614 0.1994
-2.500 -0.0586 0.01177 0.00585 -0.0539 0.9569 0.4044
-2.250 -0.0290 0.01108 0.00577 -0.0543 0.9501 0.5778
-2.000 0.0032 0.01054 0.00574 -0.0546 0.9446 0.7331
-1.750 0.0427 0.01019 0.00570 -0.0556 0.9419 0.8673
-1.500 0.1109 0.01003 0.00548 -0.0631 0.9424 0.9620
-1.250 0.1814 0.00987 0.00513 -0.0717 0.9428 1.0000
-1.000 0.2136 0.00976 0.00489 -0.0727 0.9332 1.0000
-0.750 0.2506 0.00962 0.00462 -0.0744 0.9261 1.0000
-0.500 0.2805 0.00950 0.00441 -0.0746 0.9163 1.0000
-0.250 0.3062 0.00942 0.00425 -0.0739 0.9049 1.0000
0.000 0.3312 0.00933 0.00409 -0.0730 0.8932 1.0000
0.250 0.3554 0.00924 0.00393 -0.0718 0.8810 1.0000
0.500 0.3790 0.00917 0.00378 -0.0705 0.8684 1.0000
0.750 0.4026 0.00911 0.00366 -0.0692 0.8553 1.0000
1.000 0.4263 0.00906 0.00355 -0.0679 0.8415 1.0000
1.250 0.4502 0.00902 0.00346 -0.0667 0.8268 1.0000
1.500 0.4745 0.00899 0.00339 -0.0656 0.8113 1.0000
1.750 0.4992 0.00898 0.00332 -0.0645 0.7950 1.0000
2.000 0.5241 0.00898 0.00325 -0.0635 0.7779 1.0000
2.250 0.5487 0.00902 0.00325 -0.0626 0.7577 1.0000
2.500 0.5739 0.00907 0.00325 -0.0617 0.7379 1.0000
2.750 0.5987 0.00916 0.00329 -0.0608 0.7150 1.0000
3.000 0.6236 0.00928 0.00333 -0.0599 0.6915 1.0000
3.250 0.6484 0.00943 0.00340 -0.0591 0.6670 1.0000
3.500 0.6730 0.00962 0.00351 -0.0582 0.6414 1.0000
3.750 0.6975 0.00985 0.00368 -0.0574 0.6150 1.0000
4.000 0.7217 0.01010 0.00385 -0.0565 0.5875 1.0000
4.250 0.7458 0.01037 0.00405 -0.0557 0.5591 1.0000
4.500 0.7697 0.01066 0.00428 -0.0549 0.5294 1.0000
4.750 0.7933 0.01097 0.00456 -0.0540 0.4984 1.0000
5.000 0.8165 0.01133 0.00483 -0.0531 0.4665 1.0000
5.250 0.8395 0.01171 0.00514 -0.0522 0.4332 1.0000
5.500 0.8619 0.01215 0.00548 -0.0513 0.3988 1.0000
5.750 0.8843 0.01261 0.00587 -0.0504 0.3635 1.0000
6.000 0.9059 0.01314 0.00629 -0.0494 0.3286 1.0000
6.250 0.9276 0.01368 0.00675 -0.0485 0.2919 1.0000
6.500 0.9485 0.01431 0.00731 -0.0475 0.2548 1.0000
6.750 0.9688 0.01499 0.00787 -0.0464 0.2168 1.0000
7.000 0.9889 0.01573 0.00848 -0.0454 0.1808 1.0000
7.250 1.0088 0.01652 0.00919 -0.0443 0.1483 1.0000
7.500 1.0271 0.01750 0.01003 -0.0431 0.1160 1.0000
7.750 1.0437 0.01869 0.01108 -0.0416 0.0829 1.0000
8.000 1.0582 0.02012 0.01240 -0.0397 0.0592 1.0000
8.250 1.0738 0.02138 0.01363 -0.0381 0.0426 1.0000
8.500 1.0858 0.02301 0.01528 -0.0359 0.0306 1.0000
8.750 1.0980 0.02459 0.01698 -0.0338 0.0213 1.0000
9.000 1.1042 0.02723 0.01974 -0.0308 0.0181 1.0000
9.250 1.1180 0.02919 0.02189 -0.0288 0.0163 1.0000
9.500 1.1318 0.03137 0.02426 -0.0269 0.0150 1.0000
9.750 1.1447 0.03376 0.02686 -0.0251 0.0142 1.0000
10.000 1.1555 0.03641 0.02976 -0.0231 0.0137 1.0000
10.250 1.1614 0.03883 0.03238 -0.0209 0.0129 1.0000
10.500 1.1618 0.04205 0.03583 -0.0184 0.0123 1.0000
10.750 1.1558 0.04573 0.03984 -0.0155 0.0121 1.0000
11.250 1.1303 0.05193 0.04664 -0.0104 0.0111 1.0000
11.500 1.1242 0.05424 0.04919 -0.0092 0.0105 1.0000
11.750 1.1112 0.05812 0.05332 -0.0087 0.0104 1.0000
12.000 1.0970 0.06243 0.05787 -0.0091 0.0102 1.0000
12.250 1.0811 0.06748 0.06314 -0.0105 0.0103 1.0000
12.500 1.0638 0.07322 0.06909 -0.0131 0.0103 1.0000
13.750 0.8204 0.12176 0.11889 -0.0396 0.0166 1.0000
14.000 0.7903 0.13144 0.12864 -0.0457 0.0174 1.0000
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Polar data table (+)
Polar graphs
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