MH 84 13.69% (mh84-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 84 13.69% (mh84-il) Reynolds number: 200,000 Max Cl/Cd: 62.47 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh84-il-200000.txt Download as CSV file: xf-mh84-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2628 0.11450 0.11139 -0.0057 1.0000 0.0492
-9.500 -0.2555 0.11127 0.10821 -0.0079 1.0000 0.0505
-9.250 -0.2675 0.10657 0.10360 -0.0148 1.0000 0.0523
-9.000 -0.2477 0.10369 0.10078 -0.0144 1.0000 0.0528
-8.750 -0.2194 0.10037 0.09741 -0.0176 0.9310 0.0546
-8.500 -0.2379 0.09535 0.09232 -0.0280 0.8881 0.0585
-8.250 -0.2211 0.09282 0.08970 -0.0251 0.8628 0.0589
-8.000 -0.2043 0.09106 0.08785 -0.0225 0.8409 0.0601
-7.750 -0.1964 0.08875 0.08546 -0.0224 0.8216 0.0615
-7.500 -0.1938 0.08589 0.08255 -0.0238 0.8045 0.0637
-7.250 -0.2176 0.08069 0.07738 -0.0309 0.7899 0.0659
-7.000 -0.1993 0.07870 0.07531 -0.0285 0.7758 0.0666
-6.750 -0.1876 0.07664 0.07318 -0.0277 0.7621 0.0678
-6.500 -0.1821 0.07424 0.07077 -0.0283 0.7482 0.0692
-6.250 -0.2402 0.03289 0.02768 -0.0726 0.7534 0.0366
-6.000 -0.2176 0.02997 0.02439 -0.0731 0.7422 0.0357
-5.750 -0.1929 0.02712 0.02114 -0.0739 0.7298 0.0352
-5.500 -0.1674 0.02472 0.01824 -0.0741 0.7193 0.0349
-5.250 -0.1399 0.02279 0.01593 -0.0742 0.7067 0.0349
-5.000 -0.1123 0.02131 0.01407 -0.0740 0.6957 0.0354
-4.750 -0.0841 0.02011 0.01252 -0.0737 0.6839 0.0362
-4.500 -0.0566 0.01899 0.01135 -0.0734 0.6724 0.0374
-4.250 -0.0289 0.01820 0.01045 -0.0730 0.6615 0.0391
-4.000 -0.0004 0.01742 0.00958 -0.0728 0.6495 0.0419
-3.750 0.0276 0.01692 0.00893 -0.0724 0.6393 0.0460
-3.500 0.0563 0.01622 0.00828 -0.0723 0.6270 0.0510
-3.250 0.0848 0.01559 0.00759 -0.0720 0.6168 0.0589
-3.000 0.1137 0.01497 0.00705 -0.0720 0.6052 0.0758
-2.750 0.1426 0.01445 0.00663 -0.0719 0.5946 0.1104
-2.500 0.1714 0.01425 0.00640 -0.0718 0.5836 0.1446
-2.250 0.2003 0.01414 0.00635 -0.0717 0.5725 0.1721
-2.000 0.2290 0.01412 0.00623 -0.0714 0.5624 0.1971
-1.750 0.2579 0.01403 0.00619 -0.0713 0.5510 0.2203
-1.500 0.2863 0.01401 0.00608 -0.0711 0.5415 0.2434
-1.250 0.3153 0.01390 0.00600 -0.0710 0.5300 0.2664
-1.000 0.3438 0.01385 0.00588 -0.0707 0.5206 0.2893
-0.750 0.3727 0.01375 0.00579 -0.0706 0.5097 0.3130
-0.500 0.4011 0.01367 0.00572 -0.0704 0.5003 0.3380
-0.250 0.4297 0.01355 0.00567 -0.0702 0.4899 0.3665
0.000 0.4580 0.01349 0.00564 -0.0700 0.4806 0.4012
0.250 0.4862 0.01335 0.00564 -0.0698 0.4706 0.4468
0.500 0.5139 0.01323 0.00569 -0.0695 0.4615 0.5135
0.750 0.5402 0.01299 0.00576 -0.0688 0.4521 0.6152
1.000 0.5622 0.01267 0.00583 -0.0669 0.4441 0.7602
1.250 0.5927 0.01235 0.00572 -0.0666 0.4343 1.0000
1.500 0.6217 0.01258 0.00575 -0.0666 0.4257 1.0000
1.750 0.6507 0.01276 0.00581 -0.0665 0.4165 1.0000
2.000 0.6792 0.01303 0.00590 -0.0664 0.4086 1.0000
2.250 0.7079 0.01322 0.00601 -0.0664 0.3995 1.0000
2.500 0.7361 0.01351 0.00611 -0.0663 0.3919 1.0000
2.750 0.7646 0.01371 0.00628 -0.0662 0.3831 1.0000
3.000 0.7926 0.01401 0.00640 -0.0660 0.3759 1.0000
3.250 0.8207 0.01426 0.00663 -0.0660 0.3678 1.0000
3.500 0.8486 0.01451 0.00677 -0.0658 0.3603 1.0000
3.750 0.8763 0.01484 0.00702 -0.0657 0.3531 1.0000
4.000 0.9041 0.01510 0.00724 -0.0655 0.3457 1.0000
4.250 0.9315 0.01551 0.00746 -0.0654 0.3394 1.0000
4.500 0.9590 0.01576 0.00777 -0.0652 0.3321 1.0000
4.750 0.9862 0.01607 0.00798 -0.0650 0.3258 1.0000
5.000 1.0133 0.01648 0.00833 -0.0649 0.3197 1.0000
5.250 1.0402 0.01679 0.00864 -0.0647 0.3132 1.0000
5.500 1.0670 0.01716 0.00890 -0.0645 0.3076 1.0000
5.750 1.0935 0.01758 0.00932 -0.0643 0.3018 1.0000
6.000 1.1200 0.01793 0.00967 -0.0640 0.2961 1.0000
6.250 1.1464 0.01835 0.00999 -0.0638 0.2911 1.0000
6.500 1.1724 0.01882 0.01048 -0.0636 0.2858 1.0000
6.750 1.1982 0.01920 0.01088 -0.0633 0.2804 1.0000
7.000 1.2241 0.01962 0.01124 -0.0631 0.2758 1.0000
7.250 1.2497 0.02021 0.01178 -0.0628 0.2715 1.0000
7.500 1.2746 0.02064 0.01230 -0.0625 0.2666 1.0000
7.750 1.2997 0.02106 0.01272 -0.0622 0.2620 1.0000
8.000 1.3252 0.02162 0.01317 -0.0619 0.2580 1.0000
8.250 1.3491 0.02220 0.01383 -0.0616 0.2538 1.0000
8.500 1.3729 0.02271 0.01443 -0.0612 0.2497 1.0000
8.750 1.3971 0.02321 0.01491 -0.0608 0.2458 1.0000
9.000 1.4221 0.02386 0.01545 -0.0605 0.2422 1.0000
9.250 1.4439 0.02451 0.01623 -0.0600 0.2384 1.0000
9.500 1.4657 0.02509 0.01692 -0.0594 0.2345 1.0000
9.750 1.4885 0.02566 0.01749 -0.0589 0.2311 1.0000
10.000 1.5122 0.02630 0.01808 -0.0586 0.2280 1.0000
10.250 1.5339 0.02717 0.01898 -0.0581 0.2248 1.0000
10.500 1.5522 0.02790 0.01988 -0.0572 0.2214 1.0000
10.750 1.5719 0.02857 0.02062 -0.0565 0.2181 1.0000
11.000 1.5932 0.02920 0.02124 -0.0560 0.2151 1.0000
11.250 1.6175 0.03004 0.02199 -0.0558 0.2123 1.0000
11.500 1.6330 0.03106 0.02318 -0.0548 0.2097 1.0000
11.750 1.6462 0.03204 0.02433 -0.0535 0.2070 1.0000
12.000 1.6610 0.03292 0.02531 -0.0525 0.2042 1.0000
12.250 1.6781 0.03369 0.02610 -0.0516 0.2016 1.0000
12.500 1.6996 0.03444 0.02680 -0.0511 0.1991 1.0000
12.750 1.7173 0.03569 0.02809 -0.0505 0.1967 1.0000
13.000 1.7163 0.03703 0.02966 -0.0480 0.1948 1.0000
13.250 1.7158 0.03850 0.03130 -0.0459 0.1927 1.0000
13.500 1.7188 0.03997 0.03290 -0.0444 0.1907 1.0000
13.750 1.7266 0.04126 0.03426 -0.0434 0.1886 1.0000
14.000 1.7422 0.04220 0.03519 -0.0427 0.1865 1.0000
14.250 1.7720 0.04301 0.03590 -0.0429 0.1840 1.0000
14.500 1.7608 0.04549 0.03861 -0.0413 0.1826 1.0000
14.750 1.7460 0.04851 0.04187 -0.0404 0.1811 1.0000
15.000 1.7308 0.05197 0.04556 -0.0400 0.1793 1.0000
15.250 1.7177 0.05553 0.04931 -0.0401 0.1776 1.0000
15.500 1.7114 0.05869 0.05260 -0.0403 0.1758 1.0000
15.750 1.7176 0.06067 0.05463 -0.0404 0.1740 1.0000
16.000 1.7443 0.06076 0.05466 -0.0397 0.1721 1.0000
16.250 1.7529 0.06306 0.05700 -0.0397 0.1703 1.0000
16.500 1.6866 0.07311 0.06746 -0.0431 0.1691 1.0000
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Polar data table (+)
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