MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 200,000 Max Cl/Cd: 59.15 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh24-il-200000-n5.txt Download as CSV file: xf-mh24-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3976 0.08514 0.08183 -0.0352 1.0000 0.0141
-9.250 -0.4042 0.08124 0.07797 -0.0353 1.0000 0.0136
-8.250 -0.4547 0.06447 0.06138 -0.0372 1.0000 0.0127
-7.750 -0.5642 0.06877 0.06541 -0.0319 1.0000 0.0143
-7.500 -0.5793 0.06564 0.06225 -0.0291 1.0000 0.0137
-7.250 -0.5881 0.06237 0.05889 -0.0269 0.9998 0.0133
-7.000 -0.5815 0.05713 0.05347 -0.0284 0.9963 0.0125
-6.750 -0.5715 0.05206 0.04816 -0.0294 0.9930 0.0117
-6.500 -0.5623 0.04698 0.04279 -0.0291 0.9891 0.0108
-6.250 -0.5492 0.04191 0.03734 -0.0285 0.9856 0.0100
-6.000 -0.5337 0.03583 0.03066 -0.0272 0.9826 0.0089
-5.750 -0.5159 0.03185 0.02614 -0.0253 0.9796 0.0081
-5.500 -0.4964 0.02949 0.02338 -0.0239 0.9763 0.0078
-5.250 -0.4726 0.02767 0.02122 -0.0233 0.9736 0.0076
-5.000 -0.4469 0.02566 0.01885 -0.0230 0.9714 0.0075
-4.500 -0.3945 0.02212 0.01458 -0.0224 0.9672 0.0073
-4.250 -0.3710 0.02048 0.01269 -0.0214 0.9639 0.0073
-4.000 -0.3441 0.01911 0.01114 -0.0211 0.9613 0.0073
-3.750 -0.3161 0.01777 0.00968 -0.0211 0.9590 0.0074
-3.500 -0.2875 0.01652 0.00827 -0.0213 0.9570 0.0079
-3.250 -0.2607 0.01577 0.00736 -0.0211 0.9541 0.0084
-3.000 -0.2376 0.01519 0.00666 -0.0201 0.9495 0.0101
-2.750 -0.2076 0.01478 0.00612 -0.0205 0.9464 0.0126
-2.500 -0.1840 0.01314 0.00560 -0.0205 0.9437 0.2325
-2.250 -0.1785 0.01147 0.00542 -0.0166 0.9373 0.5667
-2.000 -0.1405 0.01105 0.00598 -0.0172 0.9372 0.8381
-1.750 -0.1041 0.01126 0.00610 -0.0184 0.9345 0.8900
-1.500 -0.0655 0.01144 0.00615 -0.0202 0.9323 0.9154
-1.250 -0.0175 0.01168 0.00625 -0.0240 0.9314 0.9318
-1.000 0.0420 0.01196 0.00641 -0.0302 0.9317 0.9466
-0.750 0.0884 0.01200 0.00636 -0.0339 0.9301 0.9550
-0.500 0.1348 0.01195 0.00622 -0.0378 0.9272 0.9590
-0.250 0.1748 0.01187 0.00611 -0.0404 0.9219 0.9645
0.000 0.2150 0.01175 0.00596 -0.0429 0.9178 0.9695
0.250 0.2570 0.01158 0.00577 -0.0459 0.9120 0.9727
0.750 0.3270 0.01123 0.00543 -0.0489 0.8964 0.9803
1.000 0.3618 0.01101 0.00522 -0.0503 0.8879 0.9829
1.250 0.3959 0.01078 0.00503 -0.0516 0.8760 0.9854
1.500 0.4264 0.01060 0.00489 -0.0521 0.8597 0.9887
1.750 0.4567 0.01040 0.00471 -0.0526 0.8398 0.9915
2.000 0.4883 0.01017 0.00448 -0.0531 0.8137 0.9935
2.250 0.5225 0.00989 0.00413 -0.0540 0.7757 0.9946
2.500 0.5542 0.00979 0.00388 -0.0544 0.7217 0.9959
2.750 0.5818 0.00995 0.00377 -0.0542 0.6578 0.9978
3.000 0.6075 0.01027 0.00381 -0.0538 0.5928 1.0000
3.250 0.6247 0.01065 0.00396 -0.0518 0.5349 1.0000
3.500 0.6412 0.01108 0.00419 -0.0496 0.4760 1.0000
3.750 0.6580 0.01150 0.00441 -0.0476 0.4226 1.0000
4.000 0.6747 0.01194 0.00466 -0.0457 0.3710 1.0000
4.250 0.6912 0.01241 0.00493 -0.0437 0.3206 1.0000
4.500 0.7080 0.01288 0.00524 -0.0418 0.2737 1.0000
4.750 0.7247 0.01336 0.00556 -0.0399 0.2306 1.0000
5.000 0.7411 0.01387 0.00592 -0.0380 0.1893 1.0000
5.250 0.7577 0.01438 0.00631 -0.0361 0.1537 1.0000
5.500 0.7735 0.01495 0.00681 -0.0341 0.1189 1.0000
5.750 0.7891 0.01553 0.00728 -0.0321 0.0893 1.0000
6.000 0.8044 0.01612 0.00778 -0.0299 0.0663 1.0000
6.250 0.8193 0.01674 0.00835 -0.0277 0.0483 1.0000
6.500 0.8343 0.01734 0.00899 -0.0254 0.0385 1.0000
6.750 0.8479 0.01806 0.00976 -0.0228 0.0317 1.0000
7.000 0.8613 0.01876 0.01057 -0.0202 0.0271 1.0000
7.250 0.8708 0.01978 0.01165 -0.0169 0.0229 1.0000
7.500 0.8852 0.02038 0.01240 -0.0145 0.0200 1.0000
7.750 0.8990 0.02103 0.01313 -0.0122 0.0160 1.0000
8.000 0.9127 0.02171 0.01386 -0.0099 0.0111 1.0000
8.250 0.9260 0.02245 0.01468 -0.0076 0.0084 1.0000
8.500 0.9319 0.02393 0.01637 -0.0040 0.0070 1.0000
8.750 0.9416 0.02519 0.01784 -0.0009 0.0061 1.0000
9.000 0.9507 0.02664 0.01950 0.0021 0.0055 1.0000
9.250 0.9593 0.02827 0.02135 0.0050 0.0049 1.0000
9.500 0.9671 0.02999 0.02330 0.0080 0.0046 1.0000
9.750 0.9723 0.03177 0.02533 0.0112 0.0044 1.0000
10.000 0.9752 0.03371 0.02753 0.0145 0.0043 1.0000
10.250 0.9751 0.03581 0.02990 0.0181 0.0042 1.0000
10.500 0.9729 0.03783 0.03215 0.0214 0.0040 1.0000
10.750 0.9676 0.04040 0.03503 0.0248 0.0040 1.0000
11.000 0.9596 0.04295 0.03782 0.0277 0.0039 1.0000
11.250 0.9474 0.04624 0.04141 0.0304 0.0040 1.0000
11.500 0.9342 0.04953 0.04493 0.0321 0.0039 1.0000
11.750 0.9170 0.05376 0.04944 0.0329 0.0040 1.0000
12.000 0.8984 0.05858 0.05448 0.0322 0.0040 1.0000
12.250 0.8786 0.06441 0.06052 0.0297 0.0040 1.0000
12.500 0.8552 0.07228 0.06860 0.0249 0.0041 1.0000
12.750 0.8326 0.08174 0.07823 0.0183 0.0041 1.0000
13.000 0.8038 0.09465 0.09127 0.0100 0.0043 1.0000
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Polar data table (+)
Polar graphs
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