MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 100,000 Max Cl/Cd: 44.91 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh44-il-100000.txt Download as CSV file: xf-mh44-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
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 -0.5170 0.10340 0.09874 -0.0007 1.0000 0.1080
-9.000 -0.5220 0.09980 0.09521 -0.0039 1.0000 0.1137
-8.750 -0.5621 0.09592 0.09154 -0.0151 1.0000 0.1157
-8.500 -0.5189 0.09169 0.08721 -0.0068 1.0000 0.1199
-8.250 -0.5164 0.08825 0.08381 -0.0081 1.0000 0.1248
-8.000 -0.5754 0.08334 0.07897 -0.0225 1.0000 0.1296
-7.750 -0.5320 0.07984 0.07557 -0.0141 1.0000 0.1330
-7.500 -0.5286 0.07628 0.07205 -0.0153 1.0000 0.1380
-7.250 -0.5405 0.07124 0.06701 -0.0205 1.0000 0.1457
-7.000 -0.5292 0.06782 0.06361 -0.0200 1.0000 0.1499
-6.750 -0.5265 0.03767 0.03265 -0.0317 1.0000 0.0748
-6.500 -0.5497 0.04298 0.03719 -0.0298 1.0000 0.0588
-6.250 -0.5405 0.03814 0.03146 -0.0273 1.0000 0.0491
-6.000 -0.5288 0.03450 0.02753 -0.0254 1.0000 0.0470
-5.750 -0.5173 0.03150 0.02415 -0.0228 1.0000 0.0451
-5.500 -0.5048 0.02895 0.02117 -0.0201 1.0000 0.0435
-5.250 -0.4905 0.02678 0.01861 -0.0174 1.0000 0.0430
-5.000 -0.4751 0.02519 0.01680 -0.0151 1.0000 0.0450
-4.750 -0.4584 0.02382 0.01518 -0.0129 1.0000 0.0475
-4.500 -0.4404 0.02262 0.01371 -0.0107 1.0000 0.0498
-4.250 -0.4229 0.02061 0.01174 -0.0087 1.0000 0.0527
-4.000 -0.4066 0.01938 0.01054 -0.0065 1.0000 0.0587
-3.750 -0.3914 0.01827 0.00943 -0.0043 1.0000 0.0724
-3.500 -0.3778 0.01660 0.00815 -0.0017 1.0000 0.1214
-3.250 -0.3681 0.01492 0.00778 0.0010 1.0000 0.3548
-3.000 -0.3531 0.01458 0.00770 0.0030 1.0000 0.4323
-2.750 -0.3388 0.01422 0.00769 0.0054 1.0000 0.5195
-2.500 -0.3238 0.01380 0.00769 0.0078 1.0000 0.6173
-2.250 -0.2776 0.01330 0.00781 0.0055 0.9938 0.7965
-2.000 -0.1296 0.01351 0.00776 -0.0162 1.0000 1.0000
-1.750 -0.0949 0.01363 0.00758 -0.0191 0.9929 1.0000
-1.500 -0.0380 0.01380 0.00748 -0.0257 0.9821 1.0000
-1.250 0.0179 0.01389 0.00736 -0.0318 0.9709 1.0000
-1.000 0.0735 0.01393 0.00722 -0.0377 0.9595 1.0000
-0.750 0.1298 0.01390 0.00707 -0.0435 0.9482 1.0000
-0.500 0.1809 0.01384 0.00689 -0.0481 0.9352 1.0000
-0.250 0.2242 0.01377 0.00675 -0.0510 0.9203 1.0000
0.000 0.2591 0.01374 0.00665 -0.0520 0.9036 1.0000
0.250 0.2867 0.01374 0.00658 -0.0513 0.8865 1.0000
0.500 0.3066 0.01385 0.00664 -0.0493 0.8666 1.0000
0.750 0.3263 0.01392 0.00664 -0.0471 0.8481 1.0000
1.000 0.3456 0.01396 0.00662 -0.0446 0.8307 1.0000
1.250 0.3646 0.01404 0.00665 -0.0423 0.8115 1.0000
1.500 0.3843 0.01407 0.00664 -0.0401 0.7928 1.0000
1.750 0.4046 0.01407 0.00658 -0.0378 0.7751 1.0000
2.000 0.4254 0.01408 0.00654 -0.0357 0.7562 1.0000
2.250 0.4467 0.01409 0.00653 -0.0338 0.7364 1.0000
2.500 0.4685 0.01407 0.00644 -0.0319 0.7179 1.0000
2.750 0.4908 0.01413 0.00646 -0.0303 0.6970 1.0000
3.000 0.5134 0.01418 0.00644 -0.0286 0.6767 1.0000
3.250 0.5364 0.01429 0.00653 -0.0271 0.6550 1.0000
3.500 0.5595 0.01441 0.00658 -0.0256 0.6334 1.0000
3.750 0.5828 0.01460 0.00673 -0.0244 0.6100 1.0000
4.000 0.6061 0.01479 0.00684 -0.0230 0.5875 1.0000
4.250 0.6294 0.01502 0.00706 -0.0218 0.5631 1.0000
4.500 0.6527 0.01528 0.00729 -0.0206 0.5379 1.0000
4.750 0.6759 0.01557 0.00753 -0.0194 0.5125 1.0000
5.000 0.6990 0.01589 0.00779 -0.0183 0.4867 1.0000
5.250 0.7218 0.01625 0.00811 -0.0171 0.4600 1.0000
5.500 0.7444 0.01665 0.00845 -0.0160 0.4325 1.0000
5.750 0.7667 0.01708 0.00883 -0.0148 0.4041 1.0000
6.000 0.7886 0.01756 0.00927 -0.0137 0.3747 1.0000
6.250 0.8102 0.01809 0.00977 -0.0126 0.3455 1.0000
6.500 0.8313 0.01869 0.01035 -0.0114 0.3161 1.0000
6.750 0.8520 0.01937 0.01098 -0.0103 0.2876 1.0000
7.000 0.8722 0.02012 0.01166 -0.0091 0.2597 1.0000
7.250 0.8919 0.02097 0.01244 -0.0079 0.2333 1.0000
7.500 0.9111 0.02193 0.01326 -0.0067 0.2084 1.0000
7.750 0.9298 0.02293 0.01430 -0.0054 0.1843 1.0000
8.000 0.9479 0.02407 0.01547 -0.0041 0.1625 1.0000
8.250 0.9658 0.02526 0.01662 -0.0028 0.1430 1.0000
8.500 0.9833 0.02669 0.01795 -0.0016 0.1258 1.0000
8.750 1.0008 0.02822 0.01958 -0.0002 0.1109 1.0000
9.000 1.0173 0.02978 0.02120 0.0012 0.0976 1.0000
9.250 1.0354 0.03176 0.02312 0.0023 0.0869 1.0000
9.500 1.0496 0.03321 0.02485 0.0039 0.0776 1.0000
9.750 1.0659 0.03588 0.02774 0.0053 0.0714 1.0000
10.000 1.0800 0.03807 0.03020 0.0068 0.0658 1.0000
10.250 1.0918 0.04107 0.03334 0.0081 0.0612 1.0000
10.500 1.0962 0.04373 0.03651 0.0104 0.0579 1.0000
10.750 1.1002 0.04683 0.03995 0.0124 0.0555 1.0000
11.000 1.1032 0.04979 0.04314 0.0142 0.0535 1.0000
11.250 1.1054 0.05411 0.04751 0.0152 0.0510 1.0000
11.500 1.0892 0.05730 0.05104 0.0180 0.0503 1.0000
11.750 1.0697 0.06035 0.05437 0.0204 0.0500 1.0000
12.000 1.0495 0.06407 0.05834 0.0214 0.0499 1.0000
12.250 1.0279 0.06848 0.06297 0.0210 0.0499 1.0000
12.500 1.0077 0.07361 0.06828 0.0195 0.0502 1.0000
12.750 0.9853 0.07968 0.07449 0.0169 0.0505 1.0000
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Polar data table (+)
Polar graphs
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