MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 200,000 Max Cl/Cd: 90.1 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh122-il-200000.txt Download as CSV file: xf-mh122-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4426 0.10210 0.09890 -0.0275 1.0000 0.0312
-8.000 -0.4517 0.09986 0.09671 -0.0267 1.0000 0.0316
-7.750 -0.4616 0.09772 0.09461 -0.0258 1.0000 0.0320
-7.500 -0.4581 0.09355 0.09047 -0.0319 0.9964 0.0329
-7.250 -0.3612 0.07306 0.07016 -0.0477 0.9833 0.0353
-7.000 -0.3604 0.06976 0.06688 -0.0477 0.9798 0.0360
-6.750 -0.3637 0.06616 0.06329 -0.0489 0.9750 0.0366
-6.500 -0.3574 0.06076 0.05790 -0.0544 0.9716 0.0376
-6.250 -0.3564 0.05479 0.05188 -0.0614 0.9670 0.0381
-6.000 -0.3523 0.04956 0.04653 -0.0661 0.9624 0.0392
-5.750 -0.3374 0.04359 0.04037 -0.0724 0.9593 0.0413
-5.500 -0.3157 0.04054 0.03661 -0.0787 0.9550 0.0465
-5.000 -0.2988 0.04196 0.03744 -0.0868 0.9583 0.0497
-4.750 -0.2759 0.03921 0.03456 -0.0880 0.9555 0.0530
-4.500 -0.2498 0.03629 0.03106 -0.0897 0.9522 0.0622
-4.250 -0.2219 0.03362 0.02830 -0.0911 0.9500 0.0663
-4.000 -0.1737 0.02705 0.02052 -0.0909 0.9498 0.0210
-3.750 -0.1392 0.02439 0.01743 -0.0922 0.9486 0.0190
-3.500 -0.1048 0.02249 0.01520 -0.0932 0.9473 0.0179
-3.250 -0.0703 0.02102 0.01350 -0.0942 0.9462 0.0180
-3.000 -0.0342 0.01990 0.01227 -0.0958 0.9450 0.0196
-2.750 -0.0118 0.01928 0.01154 -0.0950 0.9412 0.0216
-2.500 0.0240 0.01656 0.01029 -0.0982 0.9402 0.3746
-2.250 0.0506 0.01645 0.01064 -0.0981 0.9371 0.5504
-2.000 0.0815 0.01657 0.01074 -0.0986 0.9346 0.5929
-1.750 0.1150 0.01670 0.01084 -0.0997 0.9327 0.6287
-1.500 0.1369 0.01686 0.01100 -0.0986 0.9286 0.6596
-1.250 0.1601 0.01698 0.01117 -0.0977 0.9244 0.6896
-1.000 0.1915 0.01704 0.01120 -0.0985 0.9217 0.7104
-0.750 0.2263 0.01707 0.01121 -0.1000 0.9197 0.7279
-0.500 0.2482 0.01718 0.01133 -0.0990 0.9149 0.7454
-0.250 0.2744 0.01724 0.01141 -0.0989 0.9105 0.7662
0.000 0.3068 0.01720 0.01144 -0.0998 0.9078 0.7888
0.250 0.3416 0.01713 0.01145 -0.1011 0.9057 0.8166
0.500 0.3534 0.01722 0.01165 -0.0980 0.8985 0.8539
0.750 0.3875 0.01698 0.01158 -0.0991 0.8954 0.9412
1.000 0.4321 0.01692 0.01146 -0.1028 0.8931 1.0000
1.250 0.4563 0.01716 0.01165 -0.1027 0.8863 1.0000
1.500 0.4931 0.01716 0.01163 -0.1046 0.8824 1.0000
1.750 0.5361 0.01701 0.01149 -0.1076 0.8800 1.0000
2.000 0.5610 0.01716 0.01164 -0.1072 0.8723 1.0000
2.250 0.6029 0.01687 0.01137 -0.1097 0.8685 1.0000
2.500 0.6557 0.01619 0.01076 -0.1140 0.8664 1.0000
2.750 0.6857 0.01594 0.01061 -0.1140 0.8573 1.0000
3.000 0.7556 0.01436 0.00915 -0.1207 0.8536 1.0000
3.250 0.7961 0.01351 0.00839 -0.1221 0.8427 1.0000
3.500 0.8344 0.01287 0.00788 -0.1233 0.8325 1.0000
3.750 0.8712 0.01227 0.00738 -0.1241 0.8208 1.0000
4.000 0.9020 0.01180 0.00702 -0.1239 0.8054 1.0000
4.250 0.9332 0.01132 0.00662 -0.1236 0.7860 1.0000
4.500 0.9568 0.01104 0.00641 -0.1219 0.7585 1.0000
4.750 0.9767 0.01084 0.00629 -0.1195 0.7107 1.0000
5.000 0.9978 0.01108 0.00594 -0.1170 0.5827 1.0000
5.250 0.9953 0.01257 0.00650 -0.1109 0.4292 1.0000
5.500 0.9921 0.01422 0.00736 -0.1053 0.2920 1.0000
5.750 0.9954 0.01582 0.00829 -0.1014 0.1828 1.0000
6.000 1.0042 0.01718 0.00925 -0.0982 0.1257 1.0000
6.250 1.0169 0.01831 0.01022 -0.0957 0.0937 1.0000
6.500 1.0291 0.01956 0.01134 -0.0931 0.0739 1.0000
6.750 1.0430 0.02088 0.01264 -0.0908 0.0603 1.0000
7.000 1.0591 0.02211 0.01388 -0.0889 0.0480 1.0000
7.250 1.0761 0.02350 0.01531 -0.0871 0.0377 1.0000
7.500 1.0940 0.02552 0.01735 -0.0857 0.0258 1.0000
7.750 1.1130 0.02628 0.01837 -0.0840 0.0195 1.0000
8.000 1.1516 0.03153 0.02388 -0.0860 0.0158 1.0000
8.250 1.1771 0.03448 0.02724 -0.0852 0.0152 1.0000
8.500 1.1964 0.03821 0.03145 -0.0836 0.0148 1.0000
8.750 1.2091 0.04091 0.03455 -0.0810 0.0137 1.0000
9.000 1.2188 0.04274 0.03666 -0.0785 0.0120 1.0000
9.250 1.2260 0.04343 0.03743 -0.0761 0.0104 1.0000
9.500 1.2261 0.04594 0.04015 -0.0727 0.0097 1.0000
9.750 1.2210 0.04942 0.04401 -0.0685 0.0096 1.0000
10.000 1.2115 0.05299 0.04794 -0.0641 0.0097 1.0000
10.250 1.1979 0.05705 0.05238 -0.0596 0.0099 1.0000
10.500 1.1776 0.06205 0.05778 -0.0554 0.0103 1.0000
10.750 1.1468 0.06861 0.06478 -0.0518 0.0111 1.0000
11.000 1.1221 0.07415 0.07058 -0.0501 0.0114 1.0000
11.250 1.0976 0.08003 0.07668 -0.0498 0.0117 1.0000
11.500 1.0740 0.08629 0.08312 -0.0510 0.0119 1.0000
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Polar data table (+)
Polar graphs
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