MH 44 9.66% (mh44-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 44 9.66% (mh44-il) Reynolds number: 200,000 Max Cl/Cd: 58.13 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh44-il-200000-n5.txt Download as CSV file: xf-mh44-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 44 9.66%
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 -0.5563 0.08796 0.08460 -0.0068 1.0000 0.0118
-9.250 -0.5621 0.08218 0.07887 -0.0101 1.0000 0.0114
-9.000 -0.5718 0.07528 0.07203 -0.0147 1.0000 0.0112
-8.750 -0.6305 0.05485 0.05136 -0.0297 1.0000 0.0093
-8.500 -0.6139 0.05662 0.05324 -0.0288 1.0000 0.0104
-8.250 -0.6462 0.04622 0.04227 -0.0305 1.0000 0.0095
-8.000 -0.6467 0.04185 0.03751 -0.0299 1.0000 0.0095
-7.750 -0.6418 0.03786 0.03307 -0.0289 1.0000 0.0093
-7.500 -0.6314 0.03469 0.02949 -0.0277 1.0000 0.0092
-7.250 -0.6179 0.03199 0.02642 -0.0265 1.0000 0.0091
-7.000 -0.6034 0.02937 0.02343 -0.0251 1.0000 0.0091
-6.750 -0.5872 0.02715 0.02088 -0.0237 1.0000 0.0091
-6.500 -0.5716 0.02511 0.01853 -0.0220 1.0000 0.0091
-6.250 -0.5470 0.02293 0.01605 -0.0220 0.9901 0.0092
-6.000 -0.5169 0.02089 0.01376 -0.0229 0.9793 0.0094
-5.500 -0.4563 0.01802 0.01056 -0.0244 0.9597 0.0099
-5.250 -0.4276 0.01697 0.00941 -0.0247 0.9496 0.0104
-5.000 -0.3997 0.01609 0.00841 -0.0248 0.9397 0.0112
-4.750 -0.3733 0.01534 0.00753 -0.0244 0.9294 0.0122
-4.500 -0.3482 0.01474 0.00676 -0.0237 0.9187 0.0135
-4.250 -0.3238 0.01413 0.00607 -0.0229 0.9087 0.0180
-4.000 -0.3000 0.01350 0.00536 -0.0218 0.8992 0.0279
-3.750 -0.2783 0.01261 0.00475 -0.0206 0.8889 0.0787
-3.500 -0.2572 0.01176 0.00442 -0.0196 0.8789 0.1893
-3.250 -0.2336 0.01138 0.00418 -0.0187 0.8698 0.2441
-3.000 -0.2101 0.01102 0.00396 -0.0178 0.8601 0.3006
-2.750 -0.1867 0.01064 0.00378 -0.0168 0.8500 0.3634
-2.500 -0.1628 0.01037 0.00360 -0.0159 0.8405 0.4116
-2.250 -0.1387 0.01012 0.00344 -0.0149 0.8307 0.4563
-2.000 -0.1145 0.00987 0.00329 -0.0139 0.8198 0.5030
-1.750 -0.0905 0.00962 0.00315 -0.0129 0.8090 0.5534
-1.500 -0.0669 0.00937 0.00303 -0.0117 0.7981 0.6081
-1.250 -0.0433 0.00910 0.00292 -0.0105 0.7870 0.6689
-1.000 -0.0187 0.00882 0.00284 -0.0093 0.7747 0.7384
-0.750 0.0134 0.00858 0.00280 -0.0096 0.7621 0.8185
-0.500 0.0660 0.00850 0.00277 -0.0143 0.7485 0.8909
-0.250 0.1161 0.00851 0.00270 -0.0186 0.7334 0.9314
0.000 0.1574 0.00856 0.00263 -0.0212 0.7170 0.9564
0.250 0.1953 0.00863 0.00259 -0.0231 0.6993 0.9749
0.500 0.2325 0.00870 0.00254 -0.0250 0.6804 0.9906
0.750 0.2708 0.00876 0.00247 -0.0272 0.6608 1.0000
1.000 0.2952 0.00883 0.00243 -0.0264 0.6417 1.0000
1.250 0.3196 0.00892 0.00241 -0.0257 0.6220 1.0000
1.500 0.3441 0.00903 0.00241 -0.0250 0.6023 1.0000
1.750 0.3689 0.00914 0.00243 -0.0243 0.5817 1.0000
2.000 0.3936 0.00928 0.00246 -0.0236 0.5616 1.0000
2.250 0.4184 0.00942 0.00253 -0.0230 0.5412 1.0000
2.500 0.4432 0.00959 0.00260 -0.0224 0.5210 1.0000
2.750 0.4681 0.00976 0.00269 -0.0218 0.5009 1.0000
3.000 0.4930 0.00994 0.00280 -0.0212 0.4807 1.0000
3.250 0.5178 0.01014 0.00295 -0.0206 0.4605 1.0000
3.500 0.5426 0.01035 0.00310 -0.0200 0.4397 1.0000
4.000 0.5920 0.01081 0.00344 -0.0189 0.3977 1.0000
4.250 0.6164 0.01108 0.00366 -0.0183 0.3763 1.0000
4.500 0.6410 0.01135 0.00389 -0.0177 0.3542 1.0000
4.750 0.6652 0.01165 0.00413 -0.0171 0.3320 1.0000
5.000 0.6893 0.01197 0.00440 -0.0165 0.3092 1.0000
5.250 0.7132 0.01231 0.00471 -0.0159 0.2859 1.0000
5.500 0.7368 0.01269 0.00503 -0.0153 0.2632 1.0000
5.750 0.7604 0.01308 0.00538 -0.0147 0.2407 1.0000
6.000 0.7836 0.01350 0.00576 -0.0140 0.2193 1.0000
6.250 0.8065 0.01395 0.00617 -0.0133 0.1978 1.0000
6.500 0.8293 0.01443 0.00663 -0.0126 0.1783 1.0000
6.750 0.8518 0.01491 0.00709 -0.0119 0.1593 1.0000
7.000 0.8739 0.01545 0.00760 -0.0111 0.1418 1.0000
7.250 0.8957 0.01600 0.00813 -0.0103 0.1248 1.0000
7.500 0.9173 0.01657 0.00870 -0.0095 0.1090 1.0000
7.750 0.9384 0.01719 0.00934 -0.0086 0.0944 1.0000
8.000 0.9591 0.01783 0.01000 -0.0077 0.0818 1.0000
8.250 0.9793 0.01853 0.01070 -0.0067 0.0697 1.0000
8.500 0.9988 0.01927 0.01145 -0.0057 0.0594 1.0000
8.750 1.0171 0.02010 0.01227 -0.0046 0.0505 1.0000
9.000 1.0361 0.02085 0.01312 -0.0035 0.0434 1.0000
9.250 1.0528 0.02179 0.01412 -0.0022 0.0381 1.0000
9.500 1.0697 0.02267 0.01513 -0.0009 0.0332 1.0000
9.750 1.0832 0.02381 0.01632 0.0007 0.0292 1.0000
10.000 1.0982 0.02477 0.01743 0.0022 0.0262 1.0000
10.250 1.1105 0.02589 0.01866 0.0039 0.0239 1.0000
10.500 1.1177 0.02732 0.02016 0.0061 0.0219 1.0000
10.750 1.1249 0.02857 0.02156 0.0084 0.0203 1.0000
11.000 1.1308 0.02979 0.02292 0.0107 0.0189 1.0000
11.250 1.1356 0.03116 0.02442 0.0127 0.0175 1.0000
11.500 1.1392 0.03274 0.02611 0.0143 0.0164 1.0000
11.750 1.1379 0.03485 0.02831 0.0158 0.0153 1.0000
12.000 1.1376 0.03709 0.03069 0.0169 0.0144 1.0000
12.250 1.1408 0.03913 0.03297 0.0176 0.0133 1.0000
12.500 1.1410 0.04158 0.03558 0.0179 0.0126 1.0000
12.750 1.1400 0.04432 0.03846 0.0179 0.0117 1.0000
13.000 1.1390 0.04721 0.04148 0.0173 0.0111 1.0000
13.250 1.1328 0.05092 0.04531 0.0161 0.0104 1.0000
13.500 1.1234 0.05529 0.04981 0.0146 0.0101 1.0000
13.750 1.1170 0.05956 0.05427 0.0129 0.0096 1.0000
14.000 1.1103 0.06406 0.05896 0.0109 0.0091 1.0000
14.250 1.0985 0.06944 0.06450 0.0085 0.0091 1.0000
14.500 1.0877 0.07500 0.07024 0.0056 0.0087 1.0000
14.750 1.0740 0.08127 0.07668 0.0023 0.0084 1.0000
15.000 1.0595 0.08791 0.08347 -0.0011 0.0084 1.0000
15.250 1.0457 0.09463 0.09033 -0.0047 0.0084 1.0000
15.500 1.0286 0.10232 0.09817 -0.0088 0.0083 1.0000
15.750 1.0117 0.11021 0.10620 -0.0129 0.0084 1.0000
16.000 0.9935 0.11876 0.11488 -0.0175 0.0084 1.0000
16.250 0.9748 0.12773 0.12397 -0.0222 0.0086 1.0000
16.500 0.9555 0.13711 0.13346 -0.0271 0.0090 1.0000
16.750 0.9332 0.14786 0.14431 -0.0326 0.0092 1.0000
17.000 0.9079 0.16023 0.15671 -0.0389 0.0095 1.0000
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Polar data table (+)
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