MH33 (mh33-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH33 (mh33-il) Reynolds number: 500,000 Max Cl/Cd: 64.17 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh33-il-500000-n5.txt Download as CSV file: xf-mh33-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH33
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5505 0.08079 0.07855 -0.0166 1.0000 0.0030
-8.500 -0.5561 0.07588 0.07368 -0.0194 1.0000 0.0030
-8.250 -0.5666 0.07079 0.06864 -0.0232 1.0000 0.0029
-8.000 -0.5764 0.06480 0.06264 -0.0280 1.0000 0.0029
-7.750 -0.5823 0.05808 0.05584 -0.0318 1.0000 0.0029
-7.500 -0.5869 0.05149 0.04910 -0.0334 1.0000 0.0028
-7.250 -0.5894 0.04525 0.04265 -0.0332 1.0000 0.0028
-7.000 -0.5913 0.03898 0.03609 -0.0316 1.0000 0.0028
-6.750 -0.5914 0.03300 0.02973 -0.0289 1.0000 0.0028
-6.500 -0.5861 0.02849 0.02480 -0.0261 1.0000 0.0029
-6.250 -0.5760 0.02503 0.02094 -0.0236 1.0000 0.0031
-6.000 -0.5530 0.02197 0.01745 -0.0233 0.9984 0.0033
-5.750 -0.5247 0.01952 0.01459 -0.0238 0.9961 0.0035
-5.500 -0.4945 0.01805 0.01286 -0.0246 0.9942 0.0039
-5.250 -0.4637 0.01771 0.01237 -0.0253 0.9921 0.0044
-5.000 -0.4374 0.01493 0.00920 -0.0252 0.9893 0.0048
-4.750 -0.4073 0.01372 0.00781 -0.0257 0.9868 0.0048
-4.500 -0.3762 0.01266 0.00657 -0.0265 0.9845 0.0048
-4.250 -0.3436 0.01174 0.00553 -0.0275 0.9825 0.0048
-4.000 -0.3124 0.01099 0.00467 -0.0283 0.9797 0.0049
-3.750 -0.2824 0.01033 0.00390 -0.0287 0.9758 0.0051
-3.500 -0.2496 0.00987 0.00334 -0.0297 0.9728 0.0055
-3.250 -0.2158 0.00950 0.00287 -0.0309 0.9701 0.0064
-3.000 -0.1844 0.00916 0.00247 -0.0316 0.9661 0.0128
-2.750 -0.1566 0.00850 0.00215 -0.0318 0.9602 0.0857
-2.500 -0.1259 0.00792 0.00193 -0.0327 0.9556 0.1768
-2.250 -0.1002 0.00736 0.00177 -0.0325 0.9477 0.2832
-2.000 -0.0705 0.00702 0.00162 -0.0330 0.9413 0.3495
-1.750 -0.0444 0.00671 0.00150 -0.0327 0.9314 0.4147
-1.500 -0.0177 0.00640 0.00138 -0.0324 0.9212 0.4823
-1.250 0.0086 0.00609 0.00128 -0.0320 0.9094 0.5527
-1.000 0.0341 0.00579 0.00120 -0.0314 0.8954 0.6283
-0.750 0.0587 0.00549 0.00113 -0.0305 0.8784 0.7054
-0.500 0.0827 0.00525 0.00107 -0.0293 0.8577 0.7773
-0.250 0.1060 0.00511 0.00107 -0.0278 0.8320 0.8447
0.000 0.1306 0.00513 0.00109 -0.0266 0.8015 0.8953
0.500 0.1849 0.00541 0.00111 -0.0256 0.7294 0.9449
0.750 0.2142 0.00559 0.00114 -0.0257 0.6886 0.9586
1.000 0.2436 0.00580 0.00116 -0.0260 0.6452 0.9694
1.250 0.2763 0.00603 0.00120 -0.0270 0.5986 0.9768
1.500 0.3088 0.00628 0.00125 -0.0281 0.5515 0.9832
1.750 0.3446 0.00654 0.00132 -0.0300 0.5008 0.9879
2.000 0.3781 0.00681 0.00140 -0.0314 0.4524 0.9932
2.250 0.4126 0.00709 0.00148 -0.0331 0.4034 0.9974
2.500 0.4431 0.00734 0.00158 -0.0339 0.3620 1.0000
2.750 0.4658 0.00760 0.00170 -0.0329 0.3246 1.0000
3.000 0.4885 0.00787 0.00187 -0.0320 0.2885 1.0000
3.250 0.5110 0.00816 0.00202 -0.0311 0.2511 1.0000
3.500 0.5337 0.00847 0.00220 -0.0301 0.2166 1.0000
3.750 0.5568 0.00875 0.00239 -0.0293 0.1896 1.0000
4.000 0.5796 0.00907 0.00260 -0.0284 0.1597 1.0000
4.250 0.6026 0.00939 0.00286 -0.0275 0.1345 1.0000
4.500 0.6254 0.00975 0.00311 -0.0266 0.1072 1.0000
4.750 0.6481 0.01016 0.00340 -0.0258 0.0794 1.0000
5.000 0.6716 0.01051 0.00369 -0.0250 0.0621 1.0000
5.250 0.6953 0.01086 0.00401 -0.0243 0.0492 1.0000
5.500 0.7191 0.01123 0.00436 -0.0236 0.0382 1.0000
5.750 0.7425 0.01166 0.00475 -0.0229 0.0261 1.0000
6.000 0.7659 0.01213 0.00522 -0.0222 0.0167 1.0000
6.250 0.7897 0.01256 0.00567 -0.0215 0.0120 1.0000
6.500 0.8135 0.01299 0.00613 -0.0209 0.0092 1.0000
6.750 0.8370 0.01348 0.00665 -0.0202 0.0064 1.0000
7.000 0.8604 0.01399 0.00719 -0.0196 0.0035 1.0000
7.250 0.8832 0.01463 0.00791 -0.0187 0.0023 1.0000
7.500 0.9057 0.01532 0.00869 -0.0179 0.0018 1.0000
7.750 0.9273 0.01617 0.00969 -0.0169 0.0015 1.0000
8.000 0.9475 0.01727 0.01098 -0.0157 0.0013 1.0000
8.250 0.9665 0.01853 0.01246 -0.0144 0.0013 1.0000
8.500 0.9845 0.01991 0.01404 -0.0130 0.0012 1.0000
8.750 1.0016 0.02142 0.01584 -0.0115 0.0012 1.0000
9.000 1.0178 0.02303 0.01769 -0.0099 0.0012 1.0000
9.250 1.0317 0.02495 0.01990 -0.0082 0.0012 1.0000
9.500 1.0442 0.02695 0.02220 -0.0064 0.0012 1.0000
9.750 1.0514 0.02960 0.02521 -0.0041 0.0011 1.0000
10.000 1.0567 0.03219 0.02812 -0.0018 0.0011 1.0000
10.250 1.0535 0.03551 0.03182 0.0011 0.0011 1.0000
10.500 1.0454 0.03848 0.03509 0.0043 0.0011 1.0000
10.750 1.0285 0.04169 0.03856 0.0078 0.0011 1.0000
11.000 1.0115 0.04524 0.04233 0.0096 0.0012 1.0000
11.250 0.9904 0.05002 0.04733 0.0090 0.0012 1.0000
11.500 0.9794 0.05466 0.05210 0.0063 0.0012 1.0000
11.750 0.9555 0.06396 0.06160 -0.0013 0.0012 1.0000
12.000 0.9406 0.07379 0.07154 -0.0089 0.0012 1.0000
12.250 0.9134 0.08662 0.08447 -0.0165 0.0012 1.0000
12.500 0.8974 0.09544 0.09330 -0.0210 0.0012 1.0000
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Polar data table (+)
Polar graphs
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