MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 100,000 Max Cl/Cd: 44.57 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh45-il-100000.txt Download as CSV file: xf-mh45-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5392 0.09653 0.09226 0.0088 1.0000 0.1173
-8.250 -0.5362 0.09301 0.08880 0.0070 1.0000 0.1234
-8.000 -0.5725 0.08830 0.08426 -0.0054 1.0000 0.1268
-7.750 -0.5385 0.08473 0.08067 0.0018 1.0000 0.1314
-7.500 -0.5405 0.08089 0.07690 -0.0012 1.0000 0.1374
-7.250 -0.5482 0.07539 0.07144 -0.0078 1.0000 0.1435
-7.000 -0.5349 0.07189 0.06797 -0.0077 1.0000 0.1481
-6.750 -0.5363 0.06669 0.06272 -0.0134 1.0000 0.1579
-6.500 -0.5513 0.04342 0.03780 -0.0267 1.0000 0.0623
-6.250 -0.5324 0.03889 0.03295 -0.0266 1.0000 0.0557
-6.000 -0.5131 0.03497 0.02790 -0.0254 1.0000 0.0482
-5.750 -0.4934 0.03108 0.02373 -0.0249 1.0000 0.0470
-5.500 -0.4753 0.02831 0.02058 -0.0237 1.0000 0.0464
-5.250 -0.4619 0.02628 0.01825 -0.0214 1.0000 0.0464
-5.000 -0.4492 0.02468 0.01639 -0.0190 1.0000 0.0468
-4.750 -0.4349 0.02331 0.01478 -0.0167 1.0000 0.0477
-4.500 -0.4208 0.02144 0.01296 -0.0148 1.0000 0.0517
-4.250 -0.4054 0.02049 0.01195 -0.0130 1.0000 0.0575
-4.000 -0.3758 0.01881 0.01032 -0.0135 0.9951 0.0675
-3.750 -0.3376 0.01681 0.00867 -0.0157 0.9859 0.1248
-3.500 -0.3028 0.01519 0.00822 -0.0180 0.9760 0.3498
-3.250 -0.2625 0.01488 0.00816 -0.0206 0.9663 0.4459
-3.000 -0.2203 0.01447 0.00806 -0.0233 0.9577 0.5368
-2.750 -0.1854 0.01406 0.00790 -0.0242 0.9468 0.6204
-2.500 -0.1496 0.01368 0.00783 -0.0247 0.9369 0.7139
-2.250 -0.1032 0.01342 0.00780 -0.0265 0.9294 0.8226
-2.000 -0.0393 0.01344 0.00774 -0.0317 0.9219 0.9100
-1.750 0.0379 0.01347 0.00750 -0.0398 0.9156 0.9594
-1.500 0.1139 0.01327 0.00703 -0.0490 0.9059 0.9975
-1.250 0.1338 0.01329 0.00689 -0.0481 0.8894 1.0000
-1.000 0.1488 0.01342 0.00686 -0.0458 0.8736 1.0000
-0.750 0.1646 0.01358 0.00688 -0.0436 0.8586 1.0000
-0.500 0.1815 0.01376 0.00692 -0.0413 0.8441 1.0000
-0.250 0.1995 0.01394 0.00697 -0.0393 0.8299 1.0000
0.000 0.2184 0.01412 0.00704 -0.0373 0.8158 1.0000
0.250 0.2379 0.01428 0.00709 -0.0354 0.8018 1.0000
0.500 0.2582 0.01444 0.00716 -0.0336 0.7878 1.0000
0.750 0.2790 0.01459 0.00722 -0.0319 0.7738 1.0000
1.000 0.3002 0.01472 0.00727 -0.0302 0.7597 1.0000
1.250 0.3219 0.01483 0.00732 -0.0286 0.7456 1.0000
1.500 0.3439 0.01493 0.00735 -0.0270 0.7313 1.0000
1.750 0.3662 0.01502 0.00737 -0.0255 0.7169 1.0000
2.000 0.3890 0.01509 0.00739 -0.0240 0.7024 1.0000
2.250 0.4120 0.01514 0.00740 -0.0225 0.6876 1.0000
2.500 0.4353 0.01519 0.00738 -0.0211 0.6726 1.0000
2.750 0.4589 0.01522 0.00736 -0.0197 0.6574 1.0000
3.000 0.4829 0.01526 0.00734 -0.0184 0.6416 1.0000
3.250 0.5075 0.01535 0.00745 -0.0175 0.6235 1.0000
3.500 0.5320 0.01541 0.00748 -0.0164 0.6058 1.0000
3.750 0.5566 0.01546 0.00748 -0.0152 0.5882 1.0000
4.000 0.5812 0.01552 0.00748 -0.0140 0.5707 1.0000
4.250 0.6063 0.01567 0.00764 -0.0132 0.5497 1.0000
4.500 0.6312 0.01580 0.00772 -0.0123 0.5300 1.0000
4.750 0.6561 0.01599 0.00788 -0.0114 0.5088 1.0000
5.000 0.6810 0.01620 0.00807 -0.0106 0.4871 1.0000
5.250 0.7059 0.01648 0.00832 -0.0098 0.4642 1.0000
5.500 0.7305 0.01678 0.00853 -0.0090 0.4418 1.0000
5.750 0.7550 0.01714 0.00890 -0.0083 0.4165 1.0000
6.000 0.7793 0.01756 0.00932 -0.0076 0.3915 1.0000
6.250 0.8032 0.01802 0.00972 -0.0069 0.3659 1.0000
6.500 0.8268 0.01855 0.01016 -0.0062 0.3404 1.0000
6.750 0.8499 0.01914 0.01071 -0.0055 0.3136 1.0000
7.000 0.8727 0.01982 0.01140 -0.0049 0.2873 1.0000
7.250 0.8951 0.02058 0.01214 -0.0042 0.2623 1.0000
7.500 0.9171 0.02145 0.01289 -0.0035 0.2402 1.0000
7.750 0.9387 0.02235 0.01382 -0.0028 0.2182 1.0000
8.000 0.9602 0.02340 0.01474 -0.0021 0.1998 1.0000
8.250 0.9811 0.02450 0.01596 -0.0013 0.1820 1.0000
8.500 1.0016 0.02565 0.01716 -0.0006 0.1658 1.0000
8.750 1.0220 0.02693 0.01849 0.0002 0.1517 1.0000
9.000 1.0416 0.02826 0.01987 0.0010 0.1383 1.0000
9.250 1.0611 0.02977 0.02142 0.0018 0.1266 1.0000
9.500 1.0800 0.03130 0.02295 0.0026 0.1155 1.0000
9.750 1.0984 0.03286 0.02454 0.0034 0.1052 1.0000
10.000 1.1125 0.03461 0.02667 0.0046 0.0958 1.0000
10.250 1.1281 0.03678 0.02894 0.0056 0.0880 1.0000
10.500 1.1427 0.03844 0.03068 0.0066 0.0804 1.0000
10.750 1.1511 0.04115 0.03374 0.0079 0.0747 1.0000
11.000 1.1602 0.04359 0.03645 0.0092 0.0701 1.0000
11.250 1.1709 0.04689 0.03977 0.0100 0.0658 1.0000
11.500 1.1634 0.04975 0.04315 0.0120 0.0635 1.0000
11.750 1.1538 0.05272 0.04646 0.0138 0.0614 1.0000
12.000 1.1444 0.05556 0.04951 0.0153 0.0595 1.0000
12.250 1.1341 0.05890 0.05304 0.0160 0.0582 1.0000
12.500 1.1168 0.06312 0.05750 0.0157 0.0579 1.0000
12.750 1.0951 0.06810 0.06270 0.0143 0.0578 1.0000
13.000 1.0431 0.07747 0.07245 0.0087 0.0609 1.0000
13.250 1.0058 0.08695 0.08210 0.0027 0.0634 1.0000
13.500 0.9761 0.09645 0.09168 -0.0031 0.0651 1.0000
13.750 0.9500 0.10630 0.10155 -0.0087 0.0662 1.0000
14.000 0.8308 0.14931 0.14426 -0.0347 0.0923 1.0000
14.250 0.8416 0.15354 0.14855 -0.0342 0.0913 1.0000
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Polar data table (+)
Polar graphs
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