MH 110 10.01% (mh110-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 110 10.01% (mh110-il) Reynolds number: 100,000 Max Cl/Cd: 39 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh110-il-100000.txt Download as CSV file: xf-mh110-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 110 10.01%
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5399 0.09092 0.08697 0.0170 1.0000 0.1235
-8.500 -0.5406 0.08661 0.08269 0.0160 1.0000 0.1290
-8.250 -0.5688 0.08053 0.07669 0.0100 1.0000 0.1320
-8.000 -0.5998 0.07451 0.07069 0.0050 1.0000 0.1324
-7.000 -0.6979 0.04893 0.04329 0.0032 1.0000 0.0505
-6.750 -0.6930 0.04350 0.03679 0.0065 1.0000 0.0417
-6.500 -0.6771 0.03931 0.03231 0.0077 1.0000 0.0402
-6.250 -0.6610 0.03598 0.02855 0.0094 1.0000 0.0402
-6.000 -0.6420 0.03341 0.02549 0.0111 1.0000 0.0408
-5.750 -0.6219 0.03056 0.02219 0.0127 1.0000 0.0418
-5.500 -0.5988 0.02719 0.01855 0.0138 1.0000 0.0429
-5.250 -0.5734 0.02468 0.01590 0.0147 1.0000 0.0445
-5.000 -0.5476 0.02270 0.01384 0.0157 1.0000 0.0478
-4.750 -0.5224 0.02103 0.01205 0.0169 1.0000 0.0549
-4.500 -0.5005 0.01929 0.01042 0.0183 1.0000 0.0680
-4.250 -0.4830 0.01724 0.00877 0.0205 1.0000 0.1116
-4.000 -0.4723 0.01473 0.00756 0.0233 1.0000 0.2887
-3.750 -0.4591 0.01341 0.00710 0.0261 1.0000 0.4545
-3.500 -0.4433 0.01250 0.00689 0.0292 1.0000 0.5989
-3.250 -0.4192 0.01203 0.00691 0.0315 1.0000 0.7294
-3.000 -0.3798 0.01217 0.00716 0.0315 1.0000 0.8268
-2.750 -0.3286 0.01271 0.00753 0.0291 1.0000 0.8871
-2.500 -0.2609 0.01342 0.00792 0.0232 1.0000 0.9218
-2.250 -0.1913 0.01381 0.00806 0.0160 1.0000 0.9484
-2.000 -0.1228 0.01383 0.00790 0.0080 1.0000 0.9716
-1.750 -0.0325 0.01377 0.00753 -0.0048 0.8778 0.9908
-1.500 0.0074 0.01377 0.00704 -0.0071 0.7901 1.0000
-1.250 0.0240 0.01379 0.00671 -0.0052 0.7423 1.0000
-1.000 0.0422 0.01380 0.00645 -0.0037 0.7046 1.0000
-0.750 0.0609 0.01383 0.00623 -0.0022 0.6718 1.0000
-0.500 0.0805 0.01388 0.00605 -0.0009 0.6432 1.0000
-0.250 0.1008 0.01396 0.00589 0.0004 0.6176 1.0000
0.000 0.1225 0.01405 0.00579 0.0014 0.5936 1.0000
0.250 0.1445 0.01416 0.00574 0.0023 0.5712 1.0000
0.500 0.1665 0.01429 0.00569 0.0033 0.5514 1.0000
0.750 0.1893 0.01445 0.00570 0.0041 0.5323 1.0000
1.000 0.2123 0.01462 0.00575 0.0049 0.5145 1.0000
1.250 0.2354 0.01481 0.00582 0.0057 0.4984 1.0000
1.500 0.2586 0.01503 0.00592 0.0065 0.4833 1.0000
1.750 0.2821 0.01527 0.00608 0.0073 0.4692 1.0000
2.000 0.3058 0.01554 0.00628 0.0080 0.4562 1.0000
2.250 0.3296 0.01584 0.00653 0.0086 0.4443 1.0000
2.500 0.3535 0.01616 0.00679 0.0093 0.4332 1.0000
2.750 0.3772 0.01649 0.00705 0.0101 0.4236 1.0000
3.000 0.4013 0.01683 0.00742 0.0107 0.4130 1.0000
3.250 0.4255 0.01726 0.00788 0.0112 0.4042 1.0000
3.500 0.4495 0.01766 0.00821 0.0120 0.3968 1.0000
3.750 0.4737 0.01812 0.00882 0.0125 0.3879 1.0000
4.000 0.4977 0.01858 0.00924 0.0131 0.3811 1.0000
4.250 0.5219 0.01911 0.00991 0.0136 0.3734 1.0000
4.500 0.5460 0.01965 0.01041 0.0143 0.3682 1.0000
4.750 0.5699 0.02031 0.01133 0.0147 0.3608 1.0000
5.000 0.5939 0.02082 0.01182 0.0154 0.3553 1.0000
5.250 0.6173 0.02163 0.01287 0.0159 0.3487 1.0000
5.500 0.6411 0.02229 0.01363 0.0165 0.3435 1.0000
5.750 0.6643 0.02310 0.01458 0.0170 0.3380 1.0000
6.000 0.6872 0.02393 0.01567 0.0176 0.3317 1.0000
6.250 0.7112 0.02457 0.01630 0.0183 0.3271 1.0000
6.500 0.7322 0.02576 0.01787 0.0187 0.3199 1.0000
6.750 0.7561 0.02628 0.01842 0.0196 0.3143 1.0000
7.000 0.7763 0.02747 0.01995 0.0201 0.3065 1.0000
7.250 0.8010 0.02766 0.02010 0.0211 0.2998 1.0000
7.500 0.8208 0.02859 0.02136 0.0219 0.2900 1.0000
7.750 0.8429 0.02889 0.02185 0.0229 0.2801 1.0000
8.000 0.8671 0.02851 0.02147 0.0241 0.2686 1.0000
8.250 0.8906 0.02788 0.02089 0.0253 0.2544 1.0000
8.500 0.9134 0.02705 0.02015 0.0266 0.2377 1.0000
8.750 0.9366 0.02586 0.01897 0.0279 0.2190 1.0000
9.000 0.9567 0.02453 0.01781 0.0294 0.1902 1.0000
9.250 0.9642 0.02540 0.01836 0.0309 0.1030 1.0000
9.500 0.9620 0.02874 0.02138 0.0328 0.0743 1.0000
9.750 0.9615 0.03153 0.02411 0.0349 0.0616 1.0000
10.000 0.9639 0.03384 0.02653 0.0366 0.0526 1.0000
10.250 0.9641 0.03644 0.02911 0.0388 0.0472 1.0000
10.500 0.9687 0.03870 0.03156 0.0407 0.0433 1.0000
11.000 0.9675 0.04400 0.03692 0.0440 0.0366 1.0000
11.250 0.9661 0.04671 0.03985 0.0446 0.0351 1.0000
11.500 0.9656 0.04981 0.04314 0.0448 0.0341 1.0000
11.750 0.9623 0.05334 0.04688 0.0443 0.0335 1.0000
12.000 0.9551 0.05742 0.05116 0.0431 0.0328 1.0000
12.250 0.9457 0.06190 0.05584 0.0411 0.0327 1.0000
12.500 0.9323 0.06709 0.06124 0.0383 0.0325 1.0000
12.750 0.9168 0.07283 0.06718 0.0347 0.0329 1.0000
13.000 0.8994 0.07914 0.07367 0.0306 0.0336 1.0000
13.250 0.8767 0.08672 0.08142 0.0254 0.0338 1.0000
13.500 0.8568 0.09418 0.08901 0.0205 0.0349 1.0000
13.750 0.8297 0.10358 0.09852 0.0144 0.0355 1.0000
14.000 0.8098 0.11212 0.10711 0.0094 0.0366 1.0000
14.250 0.7885 0.12162 0.11658 0.0042 0.0375 1.0000
14.500 0.7348 0.14438 0.13930 -0.0071 0.0485 1.0000
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Polar data table (+)
Polar graphs
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