MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 1,000,000 Max Cl/Cd: 161.21 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh122-il-1000000.txt Download as CSV file: xf-mh122-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4151 0.14078 0.13907 -0.0308 1.0000 0.0050
-12.000 -0.4130 0.13773 0.13604 -0.0311 1.0000 0.0051
-11.750 -0.4120 0.13475 0.13307 -0.0311 1.0000 0.0051
-11.500 -0.4065 0.13124 0.12958 -0.0325 0.9998 0.0054
-11.250 -0.3955 0.12710 0.12543 -0.0357 0.9991 0.0056
-11.000 -0.3857 0.12283 0.12117 -0.0388 0.9983 0.0056
-10.750 -0.3753 0.11867 0.11700 -0.0420 0.9974 0.0056
-10.500 -0.3627 0.11470 0.11304 -0.0455 0.9965 0.0059
-10.250 -0.3510 0.11063 0.10897 -0.0489 0.9956 0.0060
-10.000 -0.3391 0.10647 0.10480 -0.0525 0.9948 0.0060
-6.750 -0.1683 0.03040 0.02780 -0.1364 0.9419 0.0068
-6.500 -0.1469 0.02676 0.02387 -0.1389 0.9347 0.0072
-6.250 -0.1234 0.02451 0.02140 -0.1402 0.9289 0.0076
-6.000 -0.1007 0.02248 0.01915 -0.1407 0.9227 0.0082
-5.750 -0.0752 0.02042 0.01682 -0.1414 0.9179 0.0090
-5.500 -0.0520 0.01874 0.01493 -0.1410 0.9123 0.0100
-5.250 -0.0249 0.01762 0.01361 -0.1409 0.9080 0.0115
-5.000 0.0054 0.01818 0.01404 -0.1410 0.9047 0.0126
-4.750 0.0249 0.01350 0.00890 -0.1406 0.8998 0.0148
-4.500 0.0524 0.01099 0.00613 -0.1392 0.8960 0.0058
-4.250 0.0786 0.00936 0.00426 -0.1389 0.8925 0.0049
-4.000 0.1051 0.00849 0.00324 -0.1387 0.8891 0.0045
-3.750 0.1325 0.00797 0.00258 -0.1386 0.8858 0.0044
-3.500 0.1606 0.00764 0.00214 -0.1387 0.8828 0.0045
-3.250 0.1894 0.00742 0.00182 -0.1389 0.8800 0.0053
-2.750 0.2440 0.00614 0.00132 -0.1397 0.8743 0.2552
-2.500 0.2711 0.00559 0.00128 -0.1401 0.8713 0.4237
-2.250 0.2993 0.00549 0.00126 -0.1403 0.8687 0.4670
-2.000 0.3281 0.00546 0.00124 -0.1406 0.8662 0.4893
-1.750 0.3562 0.00543 0.00125 -0.1408 0.8636 0.5109
-1.500 0.3839 0.00540 0.00124 -0.1409 0.8607 0.5320
-1.250 0.4120 0.00538 0.00125 -0.1410 0.8578 0.5500
-1.000 0.4402 0.00536 0.00125 -0.1411 0.8548 0.5648
-0.750 0.4688 0.00537 0.00125 -0.1413 0.8513 0.5772
-0.500 0.4958 0.00535 0.00126 -0.1412 0.8470 0.5884
-0.250 0.5235 0.00532 0.00125 -0.1412 0.8424 0.5993
0.000 0.5516 0.00533 0.00126 -0.1413 0.8377 0.6109
0.250 0.5783 0.00529 0.00126 -0.1411 0.8321 0.6229
0.500 0.6060 0.00528 0.00127 -0.1411 0.8264 0.6358
0.750 0.6327 0.00526 0.00129 -0.1408 0.8199 0.6495
1.000 0.6598 0.00525 0.00129 -0.1407 0.8128 0.6644
1.250 0.6858 0.00521 0.00131 -0.1403 0.8037 0.6805
1.500 0.7121 0.00520 0.00133 -0.1399 0.7939 0.6976
1.750 0.7387 0.00519 0.00139 -0.1396 0.7854 0.7161
2.000 0.7650 0.00517 0.00145 -0.1393 0.7758 0.7369
2.250 0.7909 0.00517 0.00151 -0.1389 0.7642 0.7591
2.500 0.8159 0.00517 0.00158 -0.1383 0.7488 0.7844
2.750 0.8399 0.00521 0.00165 -0.1374 0.7276 0.8131
3.250 0.8726 0.00569 0.00195 -0.1323 0.6157 0.8977
3.500 0.8835 0.00627 0.00223 -0.1287 0.5247 1.0000
3.750 0.8972 0.00711 0.00261 -0.1261 0.4251 1.0000
4.000 0.9113 0.00800 0.00302 -0.1236 0.3232 1.0000
4.250 0.9290 0.00870 0.00339 -0.1219 0.2494 1.0000
4.500 0.9470 0.00940 0.00377 -0.1202 0.1820 1.0000
4.750 0.9664 0.01001 0.00416 -0.1188 0.1314 1.0000
5.000 0.9875 0.01050 0.00450 -0.1178 0.1003 1.0000
5.250 1.0095 0.01092 0.00483 -0.1168 0.0782 1.0000
5.500 1.0313 0.01135 0.00518 -0.1158 0.0589 1.0000
5.750 1.0529 0.01180 0.00553 -0.1148 0.0427 1.0000
6.000 1.0740 0.01229 0.00591 -0.1137 0.0279 1.0000
6.250 1.0959 0.01269 0.00629 -0.1128 0.0204 1.0000
6.500 1.1176 0.01310 0.00668 -0.1118 0.0141 1.0000
6.750 1.1360 0.01385 0.00734 -0.1102 0.0041 1.0000
7.000 1.1566 0.01436 0.00794 -0.1089 0.0031 1.0000
7.250 1.1756 0.01497 0.00861 -0.1073 0.0024 1.0000
7.500 1.1908 0.01604 0.00984 -0.1049 0.0018 1.0000
7.750 1.2108 0.01648 0.01032 -0.1037 0.0016 1.0000
8.000 1.2290 0.01713 0.01105 -0.1020 0.0014 1.0000
8.250 1.2463 0.01789 0.01189 -0.1002 0.0012 1.0000
8.500 1.2627 0.01877 0.01287 -0.0983 0.0011 1.0000
8.750 1.2785 0.01974 0.01395 -0.0964 0.0010 1.0000
9.000 1.2931 0.02084 0.01518 -0.0942 0.0010 1.0000
9.250 1.3065 0.02213 0.01662 -0.0920 0.0009 1.0000
9.500 1.3187 0.02364 0.01831 -0.0895 0.0009 1.0000
9.750 1.3300 0.02530 0.02017 -0.0871 0.0009 1.0000
10.000 1.3391 0.02730 0.02244 -0.0843 0.0009 1.0000
10.250 1.3451 0.02976 0.02520 -0.0811 0.0009 1.0000
10.500 1.3379 0.03441 0.03038 -0.0762 0.0010 1.0000
10.750 1.3066 0.04164 0.03830 -0.0687 0.0012 1.0000
11.000 1.2772 0.04739 0.04448 -0.0629 0.0013 1.0000
11.250 1.2522 0.05240 0.04979 -0.0589 0.0014 1.0000
11.500 1.2271 0.05759 0.05524 -0.0560 0.0015 1.0000
11.750 1.2039 0.06286 0.06069 -0.0545 0.0015 1.0000
12.000 1.1809 0.06860 0.06662 -0.0542 0.0015 1.0000
12.250 1.1578 0.07498 0.07317 -0.0553 0.0015 1.0000
12.500 1.1380 0.08171 0.08005 -0.0578 0.0015 1.0000
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Polar data table (+)
Polar graphs
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