MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 43 8.5% (mh43-il) Reynolds number: 50,000 Max Cl/Cd: 35.49 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh43-il-50000-n5.txt Download as CSV file: xf-mh43-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5187 0.09540 0.08883 -0.0068 1.0000 0.0359
-8.500 -0.5201 0.09045 0.08397 -0.0101 1.0000 0.0348
-8.250 -0.5249 0.08457 0.07819 -0.0149 1.0000 0.0334
-7.750 -0.5309 0.07231 0.06589 -0.0258 1.0000 0.0314
-7.500 -0.5297 0.06769 0.06122 -0.0281 1.0000 0.0311
-7.250 -0.5275 0.06297 0.05640 -0.0302 1.0000 0.0308
-7.000 -0.5231 0.05829 0.05155 -0.0320 1.0000 0.0306
-6.750 -0.5162 0.05368 0.04669 -0.0333 1.0000 0.0304
-6.500 -0.5066 0.04915 0.04180 -0.0342 1.0000 0.0303
-6.250 -0.4940 0.04492 0.03716 -0.0346 1.0000 0.0303
-6.000 -0.4786 0.04094 0.03267 -0.0345 1.0000 0.0306
-5.750 -0.4605 0.03735 0.02852 -0.0341 1.0000 0.0311
-5.500 -0.4411 0.03409 0.02480 -0.0334 1.0000 0.0322
-5.250 -0.4220 0.03182 0.02239 -0.0330 1.0000 0.0362
-5.000 -0.4002 0.02967 0.01985 -0.0320 1.0000 0.0410
-4.750 -0.3774 0.02739 0.01716 -0.0307 1.0000 0.0445
-4.500 -0.3572 0.02556 0.01519 -0.0295 1.0000 0.0510
-4.250 -0.3372 0.02411 0.01365 -0.0282 1.0000 0.0651
-4.000 -0.3173 0.02256 0.01197 -0.0265 1.0000 0.0820
-3.750 -0.2976 0.02118 0.01078 -0.0255 1.0000 0.1208
-3.500 -0.2795 0.01991 0.00984 -0.0243 1.0000 0.1889
-3.250 -0.2632 0.01890 0.00926 -0.0230 1.0000 0.2819
-3.000 -0.2479 0.01803 0.00886 -0.0214 1.0000 0.3862
-2.750 -0.2342 0.01727 0.00863 -0.0189 1.0000 0.5087
-2.500 -0.2121 0.01663 0.00854 -0.0170 0.9925 0.6677
-2.250 -0.1712 0.01631 0.00836 -0.0176 0.9842 0.8436
-2.000 -0.0893 0.01614 0.00774 -0.0274 0.9844 0.9927
-1.750 -0.0455 0.01623 0.00740 -0.0314 0.9716 1.0000
-1.500 -0.0035 0.01632 0.00715 -0.0350 0.9586 1.0000
-1.250 0.0376 0.01642 0.00691 -0.0382 0.9459 1.0000
-1.000 0.0764 0.01654 0.00679 -0.0408 0.9329 1.0000
-0.750 0.1131 0.01667 0.00671 -0.0429 0.9197 1.0000
-0.500 0.1477 0.01682 0.00665 -0.0445 0.9064 1.0000
-0.250 0.1800 0.01698 0.00667 -0.0456 0.8930 1.0000
0.000 0.2103 0.01716 0.00673 -0.0462 0.8795 1.0000
0.250 0.2388 0.01736 0.00683 -0.0463 0.8659 1.0000
0.500 0.2660 0.01757 0.00696 -0.0462 0.8524 1.0000
0.750 0.2921 0.01779 0.00711 -0.0458 0.8388 1.0000
1.000 0.3174 0.01802 0.00728 -0.0452 0.8253 1.0000
1.250 0.3423 0.01825 0.00748 -0.0445 0.8118 1.0000
1.500 0.3667 0.01849 0.00770 -0.0437 0.7981 1.0000
1.750 0.3910 0.01872 0.00795 -0.0428 0.7843 1.0000
2.000 0.4151 0.01895 0.00819 -0.0418 0.7703 1.0000
2.250 0.4391 0.01918 0.00843 -0.0408 0.7561 1.0000
2.500 0.4631 0.01940 0.00868 -0.0397 0.7417 1.0000
2.750 0.4875 0.01960 0.00899 -0.0387 0.7270 1.0000
3.000 0.5119 0.01979 0.00924 -0.0376 0.7120 1.0000
3.250 0.5359 0.01999 0.00953 -0.0365 0.6960 1.0000
3.500 0.5596 0.02022 0.00985 -0.0354 0.6785 1.0000
3.750 0.5836 0.02039 0.01012 -0.0341 0.6610 1.0000
4.000 0.6079 0.02050 0.01040 -0.0328 0.6435 1.0000
4.250 0.6312 0.02071 0.01075 -0.0316 0.6222 1.0000
4.500 0.6550 0.02081 0.01096 -0.0301 0.6011 1.0000
4.750 0.6784 0.02095 0.01123 -0.0287 0.5771 1.0000
5.000 0.7014 0.02109 0.01150 -0.0272 0.5503 1.0000
5.250 0.7242 0.02125 0.01186 -0.0257 0.5204 1.0000
5.500 0.7463 0.02148 0.01221 -0.0241 0.4853 1.0000
5.750 0.7677 0.02177 0.01256 -0.0225 0.4456 1.0000
6.000 0.7882 0.02221 0.01296 -0.0209 0.4005 1.0000
6.250 0.8072 0.02287 0.01355 -0.0193 0.3488 1.0000
6.500 0.8245 0.02383 0.01434 -0.0178 0.2942 1.0000
6.750 0.8402 0.02510 0.01540 -0.0164 0.2398 1.0000
7.000 0.8549 0.02662 0.01673 -0.0152 0.1905 1.0000
7.250 0.8686 0.02836 0.01828 -0.0139 0.1503 1.0000
7.500 0.8818 0.03024 0.02001 -0.0126 0.1197 1.0000
7.750 0.8955 0.03218 0.02192 -0.0113 0.0959 1.0000
8.000 0.9086 0.03420 0.02401 -0.0100 0.0789 1.0000
8.250 0.9248 0.03637 0.02630 -0.0085 0.0678 1.0000
8.500 0.9397 0.03841 0.02852 -0.0074 0.0567 1.0000
8.750 0.9572 0.04097 0.03136 -0.0061 0.0494 1.0000
9.000 0.9741 0.04377 0.03438 -0.0049 0.0449 1.0000
9.250 0.9876 0.04716 0.03802 -0.0037 0.0411 1.0000
9.500 0.9943 0.05022 0.04158 -0.0025 0.0368 1.0000
9.750 0.9980 0.05302 0.04461 -0.0014 0.0336 1.0000
10.000 0.9997 0.05650 0.04829 -0.0003 0.0323 1.0000
10.500 0.9850 0.06443 0.05669 0.0016 0.0312 1.0000
10.750 0.9724 0.06853 0.06105 0.0015 0.0311 1.0000
11.000 0.9557 0.07335 0.06613 0.0002 0.0310 1.0000
11.250 0.9409 0.07845 0.07140 -0.0019 0.0311 1.0000
11.500 0.9251 0.08417 0.07728 -0.0050 0.0312 1.0000
11.750 0.9090 0.09055 0.08377 -0.0088 0.0314 1.0000
12.000 0.8751 0.10217 0.09570 -0.0181 0.0334 1.0000
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Polar data table (+)
Polar graphs
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