MH 200 12.97% (mh200-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 200 12.97% (mh200-il) Reynolds number: 200,000 Max Cl/Cd: 76.08 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh200-il-200000.txt Download as CSV file: xf-mh200-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 200 12.97%
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3457 0.09147 0.08846 -0.0486 1.0000 0.0557
-10.000 -0.3687 0.09123 0.08833 -0.0437 1.0000 0.0559
-9.750 -0.3681 0.08797 0.08508 -0.0443 0.9984 0.0574
-9.500 -0.3647 0.08241 0.07953 -0.0481 0.9958 0.0595
-9.250 -0.3695 0.07526 0.07239 -0.0537 0.9931 0.0618
-9.000 -0.3893 0.06528 0.06240 -0.0628 0.9888 0.0627
-8.750 -0.4141 0.05651 0.05353 -0.0713 0.9838 0.0628
-8.500 -0.4374 0.05119 0.04804 -0.0753 0.9739 0.0634
-7.000 -0.4535 0.03305 0.02711 -0.0768 0.9444 0.0344
-6.750 -0.4207 0.02864 0.02203 -0.0775 0.9427 0.0266
-6.500 -0.4046 0.02629 0.01911 -0.0747 0.9356 0.0240
-6.250 -0.3719 0.02475 0.01729 -0.0756 0.9330 0.0233
-6.000 -0.3370 0.02304 0.01541 -0.0770 0.9312 0.0232
-5.750 -0.3034 0.02099 0.01331 -0.0782 0.9296 0.0237
-5.500 -0.2829 0.01980 0.01213 -0.0772 0.9245 0.0251
-5.250 -0.2600 0.01892 0.01121 -0.0766 0.9199 0.0269
-5.000 -0.2299 0.01809 0.01032 -0.0773 0.9171 0.0316
-4.750 -0.2005 0.01680 0.00900 -0.0781 0.9147 0.0449
-4.500 -0.1976 0.01482 0.00816 -0.0750 0.9071 0.2404
-4.250 -0.1765 0.01356 0.00778 -0.0749 0.9033 0.4362
-4.000 -0.1516 0.01294 0.00792 -0.0741 0.9008 0.6056
-3.750 -0.1318 0.01326 0.00835 -0.0720 0.8960 0.6725
-3.500 -0.1089 0.01364 0.00869 -0.0705 0.8913 0.7082
-3.250 -0.0799 0.01392 0.00888 -0.0701 0.8884 0.7317
-3.000 -0.0489 0.01416 0.00903 -0.0700 0.8862 0.7490
-2.750 -0.0301 0.01453 0.00934 -0.0680 0.8810 0.7631
-2.500 -0.0068 0.01479 0.00953 -0.0667 0.8765 0.7762
-2.250 0.0218 0.01494 0.00960 -0.0663 0.8735 0.7887
-2.000 0.0525 0.01504 0.00961 -0.0664 0.8712 0.8002
-1.750 0.0660 0.01540 0.00996 -0.0633 0.8647 0.8088
-1.500 0.0913 0.01550 0.01001 -0.0625 0.8608 0.8188
-1.250 0.1209 0.01553 0.00997 -0.0625 0.8580 0.8287
-1.000 0.1429 0.01567 0.01009 -0.0609 0.8538 0.8365
-0.750 0.1610 0.01583 0.01022 -0.0590 0.8477 0.8464
-0.500 0.1883 0.01582 0.01018 -0.0583 0.8443 0.8549
-0.250 0.2193 0.01572 0.01003 -0.0584 0.8418 0.8624
0.000 0.2321 0.01592 0.01023 -0.0557 0.8336 0.8712
0.250 0.2614 0.01577 0.01005 -0.0555 0.8299 0.8769
0.500 0.2945 0.01559 0.00983 -0.0561 0.8271 0.8827
0.750 0.3085 0.01570 0.00996 -0.0537 0.8185 0.8901
1.000 0.3396 0.01550 0.00973 -0.0539 0.8146 0.8954
1.250 0.3616 0.01549 0.00972 -0.0529 0.8081 0.9023
1.500 0.3881 0.01532 0.00957 -0.0522 0.8022 0.9076
1.750 0.4225 0.01504 0.00925 -0.0531 0.7985 0.9129
2.000 0.4406 0.01500 0.00926 -0.0512 0.7894 0.9192
2.250 0.4757 0.01466 0.00890 -0.0521 0.7847 0.9235
2.500 0.4957 0.01458 0.00886 -0.0507 0.7754 0.9302
2.750 0.5321 0.01422 0.00849 -0.0519 0.7701 0.9335
3.000 0.5547 0.01411 0.00843 -0.0508 0.7604 0.9394
3.250 0.5889 0.01379 0.00811 -0.0517 0.7546 0.9437
3.500 0.6157 0.01364 0.00803 -0.0515 0.7442 0.9482
3.750 0.6454 0.01344 0.00787 -0.0518 0.7350 0.9531
4.000 0.6780 0.01314 0.00759 -0.0525 0.7264 0.9575
4.250 0.7103 0.01295 0.00748 -0.0534 0.7143 0.9614
4.500 0.7416 0.01274 0.00733 -0.0540 0.7013 0.9662
4.750 0.7717 0.01253 0.00718 -0.0544 0.6871 0.9712
5.000 0.8078 0.01231 0.00703 -0.0560 0.6701 0.9747
5.250 0.8395 0.01217 0.00697 -0.0569 0.6477 0.9799
5.500 0.8723 0.01205 0.00687 -0.0580 0.6197 0.9846
5.750 0.9064 0.01205 0.00680 -0.0594 0.5813 0.9891
6.000 0.9358 0.01230 0.00686 -0.0600 0.5314 0.9955
6.250 0.9488 0.01272 0.00705 -0.0577 0.4845 1.0000
6.500 0.9461 0.01307 0.00725 -0.0523 0.4484 1.0000
6.750 0.9541 0.01364 0.00761 -0.0493 0.4069 1.0000
7.000 0.9666 0.01433 0.00812 -0.0473 0.3645 1.0000
7.250 0.9799 0.01509 0.00868 -0.0455 0.3249 1.0000
7.500 0.9939 0.01582 0.00926 -0.0438 0.2894 1.0000
7.750 1.0068 0.01658 0.00989 -0.0419 0.2584 1.0000
8.000 1.0201 0.01738 0.01057 -0.0401 0.2308 1.0000
8.250 1.0333 0.01821 0.01129 -0.0384 0.2050 1.0000
8.500 1.0455 0.01910 0.01209 -0.0366 0.1811 1.0000
8.750 1.0583 0.02000 0.01292 -0.0349 0.1573 1.0000
9.000 1.0701 0.02099 0.01383 -0.0332 0.1354 1.0000
9.250 1.0801 0.02213 0.01486 -0.0313 0.1158 1.0000
9.500 1.0890 0.02340 0.01605 -0.0294 0.0989 1.0000
9.750 1.0985 0.02468 0.01729 -0.0276 0.0847 1.0000
10.000 1.1060 0.02615 0.01871 -0.0256 0.0742 1.0000
10.250 1.1171 0.02741 0.02003 -0.0241 0.0660 1.0000
10.500 1.1258 0.02896 0.02162 -0.0224 0.0593 1.0000
10.750 1.1355 0.03038 0.02308 -0.0210 0.0536 1.0000
11.000 1.1451 0.03211 0.02487 -0.0195 0.0491 1.0000
11.250 1.1560 0.03347 0.02633 -0.0183 0.0447 1.0000
11.500 1.1656 0.03570 0.02850 -0.0169 0.0405 1.0000
11.750 1.1757 0.03706 0.03009 -0.0157 0.0375 1.0000
12.000 1.1841 0.03867 0.03179 -0.0146 0.0343 1.0000
12.250 1.1944 0.04139 0.03451 -0.0135 0.0308 1.0000
12.500 1.1995 0.04308 0.03644 -0.0123 0.0286 1.0000
12.750 1.2033 0.04496 0.03847 -0.0113 0.0261 1.0000
13.000 1.2072 0.04723 0.04078 -0.0105 0.0241 1.0000
13.250 1.2086 0.05067 0.04445 -0.0094 0.0222 1.0000
13.500 1.2073 0.05312 0.04713 -0.0087 0.0204 1.0000
13.750 1.2065 0.05574 0.04991 -0.0082 0.0190 1.0000
14.000 1.2052 0.05850 0.05274 -0.0081 0.0178 1.0000
14.250 1.2014 0.06240 0.05675 -0.0078 0.0168 1.0000
14.500 1.1891 0.06769 0.06232 -0.0078 0.0163 1.0000
14.750 1.1793 0.07209 0.06698 -0.0084 0.0161 1.0000
15.000 1.1653 0.07722 0.07240 -0.0097 0.0157 1.0000
15.250 1.1514 0.08279 0.07823 -0.0115 0.0156 1.0000
15.500 1.1357 0.08899 0.08467 -0.0140 0.0154 1.0000
15.750 1.1176 0.09600 0.09192 -0.0175 0.0153 1.0000
16.000 1.0995 0.10347 0.09960 -0.0214 0.0154 1.0000
16.250 1.0800 0.11171 0.10805 -0.0263 0.0154 1.0000
16.500 1.0603 0.12049 0.11702 -0.0318 0.0157 1.0000
16.750 1.0394 0.13006 0.12674 -0.0378 0.0160 1.0000
17.000 1.0182 0.14022 0.13704 -0.0444 0.0162 1.0000
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Polar data table (+)
Polar graphs
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