MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 50,000 Max Cl/Cd: 30.06 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh84-il-50000-n5.txt Download as CSV file: xf-mh84-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 84 13.69%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2383 0.10831 0.10216 -0.0170 1.0000 0.0638
-8.750 -0.2311 0.10465 0.09859 -0.0190 1.0000 0.0614
-8.500 -0.2322 0.10010 0.09414 -0.0227 1.0000 0.0579
-8.250 -0.2235 0.09694 0.09110 -0.0244 1.0000 0.0570
-8.000 -0.2185 0.09360 0.08788 -0.0265 1.0000 0.0562
-7.750 -0.2136 0.09010 0.08451 -0.0295 0.9797 0.0553
-7.500 -0.1974 0.08493 0.07934 -0.0364 0.9413 0.0543
-7.250 -0.1861 0.07963 0.07401 -0.0429 0.9136 0.0535
-7.000 -0.1799 0.07509 0.06944 -0.0476 0.8892 0.0534
-6.750 -0.1747 0.07045 0.06476 -0.0524 0.8680 0.0535
-6.500 -0.1813 0.05934 0.05341 -0.0658 0.8505 0.0521
-6.250 -0.1702 0.05597 0.04994 -0.0684 0.8336 0.0530
-6.000 -0.1603 0.05107 0.04476 -0.0728 0.8188 0.0540
-5.750 -0.1471 0.04606 0.03933 -0.0771 0.8039 0.0552
-5.500 -0.1296 0.04131 0.03398 -0.0804 0.7899 0.0566
-5.250 -0.1082 0.03723 0.02914 -0.0823 0.7776 0.0582
-5.000 -0.0853 0.03569 0.02744 -0.0822 0.7639 0.0609
-4.750 -0.0604 0.03349 0.02471 -0.0826 0.7504 0.0653
-4.500 -0.0362 0.03230 0.02342 -0.0820 0.7385 0.0696
-4.250 -0.0105 0.03085 0.02167 -0.0818 0.7252 0.0755
-4.000 0.0154 0.02970 0.02029 -0.0814 0.7127 0.0836
-3.750 0.0411 0.02875 0.01919 -0.0807 0.7014 0.0941
-3.500 0.0673 0.02802 0.01843 -0.0804 0.6881 0.1081
-3.250 0.0939 0.02730 0.01756 -0.0798 0.6771 0.1279
-3.000 0.1203 0.02682 0.01712 -0.0794 0.6645 0.1510
-2.750 0.1474 0.02647 0.01665 -0.0790 0.6527 0.1789
-2.500 0.1737 0.02619 0.01633 -0.0783 0.6418 0.2058
-2.250 0.2008 0.02596 0.01596 -0.0779 0.6293 0.2336
-2.000 0.2273 0.02562 0.01554 -0.0770 0.6198 0.2585
-1.750 0.2546 0.02546 0.01535 -0.0767 0.6068 0.2840
-1.500 0.2821 0.02523 0.01498 -0.0761 0.5966 0.3106
-1.250 0.3093 0.02505 0.01474 -0.0756 0.5851 0.3374
-1.000 0.3363 0.02489 0.01458 -0.0751 0.5743 0.3656
-0.750 0.3634 0.02471 0.01434 -0.0745 0.5640 0.3978
-0.500 0.3899 0.02462 0.01430 -0.0739 0.5529 0.4332
-0.250 0.4164 0.02440 0.01411 -0.0730 0.5435 0.4762
0.000 0.4415 0.02433 0.01423 -0.0723 0.5324 0.5283
0.250 0.4656 0.02403 0.01407 -0.0707 0.5238 0.6003
0.500 0.4859 0.02384 0.01424 -0.0687 0.5131 0.7023
0.750 0.5150 0.02326 0.01382 -0.0674 0.5045 1.0000
1.000 0.5433 0.02373 0.01404 -0.0678 0.4931 1.0000
1.250 0.5720 0.02394 0.01388 -0.0675 0.4851 1.0000
1.500 0.5989 0.02449 0.01427 -0.0676 0.4741 1.0000
1.750 0.6270 0.02471 0.01418 -0.0672 0.4664 1.0000
2.000 0.6531 0.02531 0.01468 -0.0672 0.4556 1.0000
2.250 0.6809 0.02558 0.01468 -0.0667 0.4482 1.0000
2.500 0.7064 0.02624 0.01527 -0.0667 0.4381 1.0000
2.750 0.7336 0.02654 0.01534 -0.0662 0.4305 1.0000
3.000 0.7587 0.02724 0.01598 -0.0661 0.4212 1.0000
3.250 0.7852 0.02765 0.01623 -0.0657 0.4137 1.0000
3.500 0.8103 0.02830 0.01679 -0.0654 0.4055 1.0000
3.750 0.8355 0.02887 0.01728 -0.0651 0.3975 1.0000
4.000 0.8620 0.02932 0.01755 -0.0646 0.3911 1.0000
4.250 0.8847 0.03024 0.01852 -0.0644 0.3824 1.0000
4.500 0.9112 0.03062 0.01873 -0.0639 0.3764 1.0000
4.750 0.9331 0.03163 0.01978 -0.0637 0.3685 1.0000
5.000 0.9572 0.03231 0.02042 -0.0633 0.3618 1.0000
5.250 0.9837 0.03272 0.02066 -0.0628 0.3566 1.0000
5.500 1.0017 0.03411 0.02220 -0.0625 0.3485 1.0000
5.750 1.0264 0.03468 0.02269 -0.0620 0.3428 1.0000
6.000 1.0487 0.03557 0.02355 -0.0615 0.3372 1.0000
6.250 1.0656 0.03700 0.02509 -0.0611 0.3303 1.0000
6.500 1.0901 0.03756 0.02557 -0.0606 0.3252 1.0000
6.750 1.1095 0.03870 0.02675 -0.0601 0.3199 1.0000
7.000 1.1216 0.04052 0.02872 -0.0595 0.3135 1.0000
7.250 1.1443 0.04124 0.02939 -0.0589 0.3088 1.0000
7.500 1.1671 0.04200 0.03008 -0.0584 0.3047 1.0000
7.750 1.1643 0.04507 0.03344 -0.0576 0.2981 1.0000
8.000 1.1802 0.04633 0.03474 -0.0569 0.2935 1.0000
8.250 1.2089 0.04650 0.03479 -0.0563 0.2901 1.0000
8.500 1.1837 0.05139 0.04002 -0.0554 0.2842 1.0000
8.750 1.1498 0.05692 0.04573 -0.0549 0.2786 1.0000
9.000 1.1750 0.05716 0.04593 -0.0540 0.2753 1.0000
9.250 1.2252 0.05534 0.04399 -0.0530 0.2730 1.0000
9.500 0.9793 0.09249 0.08178 -0.0690 0.2524 1.0000
9.750 1.0721 0.08059 0.06974 -0.0613 0.2570 1.0000
10.250 1.0016 0.10101 0.09036 -0.0700 0.2419 1.0000
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Polar data table (+)
Polar graphs
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