MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 100,000 Max Cl/Cd: 50.08 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh43-il-100000.txt Download as CSV file: xf-mh43-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 43 8.5%
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 -0.5102 0.09706 0.09252 -0.0023 1.0000 0.0900
-8.250 -0.5150 0.09352 0.08906 -0.0061 1.0000 0.0938
-8.000 -0.5406 0.08973 0.08540 -0.0170 1.0000 0.0956
-7.750 -0.5192 0.08521 0.08092 -0.0112 1.0000 0.0984
-7.500 -0.5121 0.08180 0.07754 -0.0114 1.0000 0.1016
-7.250 -0.4514 0.06817 0.06428 -0.0164 1.0000 0.1119
-7.000 -0.5177 0.07190 0.06765 -0.0234 1.0000 0.1109
-6.750 -0.5044 0.06857 0.06436 -0.0224 1.0000 0.1143
-6.250 -0.4891 0.05990 0.05558 -0.0277 1.0000 0.1270
-6.000 -0.4800 0.04422 0.03864 -0.0357 1.0000 0.0584
-5.750 -0.4602 0.03853 0.03226 -0.0349 1.0000 0.0432
-5.500 -0.4439 0.03421 0.02767 -0.0345 1.0000 0.0410
-5.250 -0.4256 0.03060 0.02362 -0.0335 1.0000 0.0391
-5.000 -0.4064 0.02784 0.02039 -0.0322 1.0000 0.0395
-4.750 -0.3877 0.02583 0.01794 -0.0305 1.0000 0.0420
-4.500 -0.3696 0.02437 0.01598 -0.0285 1.0000 0.0438
-4.250 -0.3528 0.02177 0.01321 -0.0266 1.0000 0.0456
-4.000 -0.3362 0.02011 0.01151 -0.0247 1.0000 0.0494
-3.750 -0.3189 0.01875 0.01002 -0.0226 1.0000 0.0579
-3.500 -0.3026 0.01744 0.00882 -0.0208 1.0000 0.0816
-3.250 -0.2863 0.01591 0.00776 -0.0192 1.0000 0.1517
-3.000 -0.2702 0.01451 0.00712 -0.0179 1.0000 0.2863
-2.750 -0.2545 0.01372 0.00696 -0.0164 1.0000 0.4207
-2.500 -0.2290 0.01279 0.00707 -0.0157 0.9943 0.6570
-2.250 -0.1839 0.01244 0.00720 -0.0164 0.9893 0.9102
-2.000 -0.1006 0.01246 0.00676 -0.0273 0.9884 1.0000
-1.750 -0.0498 0.01260 0.00656 -0.0327 0.9781 1.0000
-1.500 0.0027 0.01272 0.00639 -0.0382 0.9688 1.0000
-1.250 0.0517 0.01279 0.00621 -0.0429 0.9582 1.0000
-1.000 0.1003 0.01283 0.00608 -0.0474 0.9479 1.0000
-0.750 0.1464 0.01286 0.00596 -0.0513 0.9372 1.0000
-0.500 0.1884 0.01289 0.00586 -0.0541 0.9258 1.0000
-0.250 0.2236 0.01297 0.00584 -0.0556 0.9129 1.0000
0.000 0.2527 0.01310 0.00589 -0.0557 0.8990 1.0000
0.250 0.2780 0.01327 0.00599 -0.0551 0.8848 1.0000
0.500 0.3012 0.01346 0.00612 -0.0539 0.8706 1.0000
0.750 0.3234 0.01366 0.00626 -0.0525 0.8565 1.0000
1.000 0.3450 0.01386 0.00642 -0.0509 0.8426 1.0000
1.250 0.3666 0.01406 0.00658 -0.0493 0.8287 1.0000
1.500 0.3883 0.01425 0.00676 -0.0477 0.8148 1.0000
1.750 0.4103 0.01443 0.00691 -0.0462 0.8009 1.0000
2.000 0.4326 0.01460 0.00707 -0.0446 0.7869 1.0000
2.250 0.4551 0.01476 0.00722 -0.0431 0.7728 1.0000
2.500 0.4780 0.01490 0.00736 -0.0417 0.7584 1.0000
2.750 0.5011 0.01502 0.00754 -0.0402 0.7436 1.0000
3.000 0.5245 0.01512 0.00765 -0.0387 0.7285 1.0000
3.250 0.5480 0.01518 0.00774 -0.0372 0.7131 1.0000
3.500 0.5719 0.01522 0.00778 -0.0357 0.6975 1.0000
3.750 0.5956 0.01532 0.00799 -0.0345 0.6782 1.0000
4.000 0.6197 0.01532 0.00802 -0.0330 0.6596 1.0000
4.250 0.6438 0.01534 0.00809 -0.0316 0.6391 1.0000
4.500 0.6681 0.01531 0.00808 -0.0302 0.6174 1.0000
4.750 0.6922 0.01533 0.00815 -0.0288 0.5921 1.0000
5.000 0.7162 0.01533 0.00819 -0.0274 0.5645 1.0000
5.250 0.7400 0.01537 0.00833 -0.0260 0.5324 1.0000
5.500 0.7632 0.01547 0.00843 -0.0246 0.4950 1.0000
5.750 0.7858 0.01569 0.00865 -0.0233 0.4487 1.0000
6.000 0.8070 0.01612 0.00895 -0.0219 0.3925 1.0000
6.250 0.8265 0.01688 0.00946 -0.0205 0.3253 1.0000
6.500 0.8437 0.01808 0.01028 -0.0192 0.2528 1.0000
6.750 0.8596 0.01969 0.01146 -0.0178 0.1861 1.0000
7.000 0.8751 0.02146 0.01289 -0.0164 0.1341 1.0000
7.250 0.8913 0.02352 0.01472 -0.0148 0.1020 1.0000
7.500 0.9081 0.02554 0.01651 -0.0136 0.0795 1.0000
7.750 0.9291 0.02808 0.01913 -0.0123 0.0668 1.0000
8.000 0.9491 0.03017 0.02134 -0.0112 0.0554 1.0000
8.250 0.9705 0.03293 0.02449 -0.0098 0.0482 1.0000
8.500 0.9870 0.03614 0.02784 -0.0088 0.0415 1.0000
8.750 1.0026 0.03906 0.03130 -0.0072 0.0379 1.0000
9.000 1.0142 0.04290 0.03564 -0.0055 0.0364 1.0000
9.250 1.0203 0.04709 0.04034 -0.0037 0.0359 1.0000
9.500 1.0202 0.05148 0.04522 -0.0020 0.0362 1.0000
9.750 1.0156 0.05559 0.04972 -0.0004 0.0358 1.0000
10.000 1.0045 0.05975 0.05423 0.0011 0.0359 1.0000
10.250 0.9854 0.06377 0.05851 0.0027 0.0366 1.0000
10.500 0.9636 0.06847 0.06343 0.0027 0.0381 1.0000
10.750 0.9442 0.07335 0.06846 0.0011 0.0390 1.0000
11.000 0.9203 0.07914 0.07440 -0.0024 0.0384 1.0000
11.250 0.9026 0.08567 0.08101 -0.0062 0.0401 1.0000
11.500 0.8865 0.09259 0.08798 -0.0105 0.0411 1.0000
11.750 0.8719 0.10008 0.09549 -0.0150 0.0419 1.0000
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Polar data table (+)
Polar graphs
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