MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 500,000 Max Cl/Cd: 137.68 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh122-il-500000.txt Download as CSV file: xf-mh122-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3263 0.14596 0.14379 -0.0326 1.0000 0.0095
-13.000 -0.3283 0.14411 0.14195 -0.0318 1.0000 0.0096
-12.750 -0.3295 0.14200 0.13987 -0.0313 0.9999 0.0098
-12.500 -0.3224 0.13850 0.13636 -0.0335 0.9991 0.0101
-12.250 -0.3155 0.13489 0.13275 -0.0357 0.9983 0.0104
-12.000 -0.3092 0.13127 0.12912 -0.0379 0.9975 0.0107
-11.750 -0.3027 0.12750 0.12535 -0.0402 0.9966 0.0111
-11.500 -0.2965 0.12370 0.12155 -0.0426 0.9957 0.0115
-11.250 -0.2901 0.11985 0.11770 -0.0452 0.9949 0.0117
-11.000 -0.2835 0.11595 0.11379 -0.0480 0.9942 0.0120
-10.750 -0.2763 0.11214 0.10998 -0.0502 0.9928 0.0122
-10.500 -0.2692 0.10813 0.10594 -0.0526 0.9912 0.0124
-10.250 -0.2623 0.10398 0.10179 -0.0550 0.9896 0.0124
-10.000 -0.2551 0.09966 0.09748 -0.0575 0.9881 0.0125
-9.750 -0.2480 0.09524 0.09305 -0.0602 0.9867 0.0125
-9.500 -0.2407 0.09063 0.08844 -0.0630 0.9854 0.0126
-9.250 -0.2332 0.08582 0.08364 -0.0660 0.9842 0.0126
-9.000 -0.2254 0.08094 0.07876 -0.0693 0.9832 0.0126
-8.750 -0.2171 0.07587 0.07369 -0.0729 0.9823 0.0126
-8.500 -0.2152 0.07137 0.06920 -0.0748 0.9772 0.0126
-8.250 -0.2229 0.06308 0.06096 -0.0791 0.9743 0.0131
-8.000 -0.2225 0.05640 0.05429 -0.0840 0.9721 0.0134
-7.750 -0.2167 0.05007 0.04796 -0.0902 0.9703 0.0136
-7.500 -0.2214 0.04310 0.04097 -0.0976 0.9621 0.0134
-7.250 -0.2137 0.03548 0.03316 -0.1103 0.9586 0.0135
-4.750 -0.0053 0.01601 0.01070 -0.1348 0.9332 0.0107
-4.500 0.0270 0.01333 0.00768 -0.1354 0.9318 0.0085
-4.250 0.0488 0.01213 0.00628 -0.1340 0.9269 0.0077
-4.000 0.0779 0.01121 0.00523 -0.1344 0.9241 0.0075
-3.750 0.1093 0.01045 0.00434 -0.1353 0.9219 0.0077
-3.500 0.1416 0.00989 0.00364 -0.1363 0.9201 0.0089
-3.250 0.1740 0.00915 0.00302 -0.1374 0.9183 0.0683
-3.000 0.1957 0.00782 0.00285 -0.1376 0.9139 0.3919
-2.750 0.2239 0.00761 0.00287 -0.1379 0.9111 0.4836
-2.500 0.2542 0.00756 0.00277 -0.1384 0.9088 0.5078
-2.250 0.2851 0.00751 0.00273 -0.1391 0.9067 0.5356
-2.000 0.3147 0.00749 0.00271 -0.1396 0.9045 0.5562
-1.750 0.3396 0.00752 0.00278 -0.1390 0.9008 0.5786
-1.500 0.3674 0.00751 0.00278 -0.1391 0.8977 0.5967
-1.250 0.3969 0.00748 0.00275 -0.1395 0.8953 0.6106
-1.000 0.4274 0.00746 0.00273 -0.1401 0.8931 0.6228
-0.750 0.4550 0.00747 0.00276 -0.1402 0.8901 0.6348
-0.500 0.4809 0.00748 0.00281 -0.1398 0.8861 0.6472
-0.250 0.5095 0.00745 0.00281 -0.1400 0.8827 0.6605
0.000 0.5399 0.00741 0.00279 -0.1406 0.8798 0.6747
0.250 0.5660 0.00741 0.00284 -0.1402 0.8753 0.6897
0.500 0.5929 0.00736 0.00286 -0.1400 0.8703 0.7062
0.750 0.6233 0.00729 0.00282 -0.1405 0.8660 0.7244
1.000 0.6477 0.00724 0.00287 -0.1396 0.8594 0.7438
1.250 0.6766 0.00714 0.00281 -0.1397 0.8533 0.7659
1.500 0.7008 0.00705 0.00283 -0.1387 0.8451 0.7902
1.750 0.7271 0.00693 0.00277 -0.1381 0.8364 0.8184
2.000 0.7511 0.00678 0.00275 -0.1370 0.8260 0.8515
2.250 0.7707 0.00664 0.00276 -0.1348 0.8161 0.8968
2.500 0.7979 0.00647 0.00270 -0.1344 0.8071 1.0000
2.750 0.8249 0.00648 0.00270 -0.1342 0.7968 1.0000
3.000 0.8507 0.00650 0.00275 -0.1337 0.7841 1.0000
3.250 0.8750 0.00652 0.00280 -0.1329 0.7671 1.0000
3.500 0.8994 0.00657 0.00283 -0.1320 0.7460 1.0000
3.750 0.9211 0.00669 0.00287 -0.1306 0.7076 1.0000
4.000 0.9373 0.00709 0.00297 -0.1279 0.6356 1.0000
4.250 0.9425 0.00809 0.00337 -0.1233 0.5185 1.0000
4.500 0.9479 0.00928 0.00394 -0.1191 0.3957 1.0000
4.750 0.9590 0.01031 0.00452 -0.1162 0.2953 1.0000
5.000 0.9725 0.01129 0.00506 -0.1138 0.2086 1.0000
5.250 0.9880 0.01217 0.00559 -0.1118 0.1417 1.0000
5.500 1.0063 0.01287 0.00609 -0.1102 0.1021 1.0000
5.750 1.0257 0.01349 0.00660 -0.1088 0.0767 1.0000
6.000 1.0454 0.01409 0.00713 -0.1075 0.0577 1.0000
6.250 1.0647 0.01469 0.00768 -0.1060 0.0435 1.0000
6.500 1.0839 0.01524 0.00821 -0.1046 0.0326 1.0000
6.750 1.1027 0.01583 0.00878 -0.1031 0.0238 1.0000
7.000 1.1199 0.01662 0.00955 -0.1012 0.0136 1.0000
7.250 1.1339 0.01781 0.01084 -0.0987 0.0074 1.0000
7.500 1.1529 0.01841 0.01147 -0.0973 0.0056 1.0000
7.750 1.1641 0.01998 0.01319 -0.0944 0.0044 1.0000
8.000 1.1776 0.02142 0.01479 -0.0920 0.0040 1.0000
8.250 1.1948 0.02240 0.01588 -0.0903 0.0036 1.0000
8.500 1.2112 0.02360 0.01723 -0.0885 0.0031 1.0000
8.750 1.2272 0.02504 0.01883 -0.0867 0.0028 1.0000
9.000 1.2427 0.02670 0.02068 -0.0849 0.0026 1.0000
9.250 1.2572 0.02870 0.02290 -0.0829 0.0025 1.0000
9.500 1.2695 0.03103 0.02550 -0.0807 0.0024 1.0000
9.750 1.2779 0.03404 0.02888 -0.0780 0.0024 1.0000
10.000 1.2774 0.03835 0.03370 -0.0741 0.0025 1.0000
10.250 1.2617 0.04408 0.04000 -0.0685 0.0027 1.0000
10.500 1.2399 0.04940 0.04577 -0.0631 0.0029 1.0000
10.750 1.2180 0.05426 0.05097 -0.0588 0.0030 1.0000
11.000 1.1946 0.05927 0.05626 -0.0555 0.0032 1.0000
11.250 1.1720 0.06435 0.06159 -0.0534 0.0032 1.0000
11.500 1.1496 0.06974 0.06719 -0.0525 0.0033 1.0000
11.750 1.1277 0.07555 0.07318 -0.0530 0.0033 1.0000
12.000 1.1063 0.08199 0.07979 -0.0548 0.0033 1.0000
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Polar data table (+)
Polar graphs
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