MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 200,000 Max Cl/Cd: 82.42 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh121-il-200000-n5.txt Download as CSV file: xf-mh121-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4147 0.10977 0.10617 -0.0361 1.0000 0.0122
-9.500 -0.4163 0.10649 0.10293 -0.0360 1.0000 0.0106
-9.250 -0.4198 0.10300 0.09950 -0.0360 1.0000 0.0096
-9.000 -0.4250 0.09951 0.09606 -0.0359 1.0000 0.0087
-8.500 -0.4357 0.09103 0.08772 -0.0373 0.9992 0.0067
-8.250 -0.4220 0.08671 0.08340 -0.0417 0.9963 0.0064
-8.000 -0.4085 0.08296 0.07962 -0.0456 0.9933 0.0061
-7.750 -0.4045 0.07755 0.07423 -0.0505 0.9880 0.0059
-7.500 -0.3963 0.07151 0.06821 -0.0577 0.9823 0.0059
-7.250 -0.3877 0.06399 0.06069 -0.0679 0.9735 0.0056
-7.000 -0.3738 0.05588 0.05241 -0.0791 0.9667 0.0055
-6.750 -0.3607 0.04965 0.04595 -0.0852 0.9598 0.0055
-6.500 -0.3399 0.04343 0.03939 -0.0910 0.9561 0.0054
-6.250 -0.3255 0.03871 0.03433 -0.0928 0.9494 0.0053
-6.000 -0.3000 0.03378 0.02894 -0.0957 0.9463 0.0055
-5.750 -0.2703 0.02977 0.02442 -0.0981 0.9443 0.0058
-5.500 -0.2484 0.02641 0.02052 -0.0984 0.9394 0.0067
-5.250 -0.2230 0.02468 0.01856 -0.1000 0.9364 0.0095
-5.000 -0.1923 0.02217 0.01550 -0.1009 0.9345 0.0101
-4.750 -0.1606 0.01993 0.01287 -0.1017 0.9331 0.0100
-4.500 -0.1284 0.01812 0.01080 -0.1025 0.9319 0.0101
-4.250 -0.0960 0.01664 0.00914 -0.1035 0.9309 0.0103
-4.000 -0.0745 0.01571 0.00808 -0.1024 0.9259 0.0106
-3.750 -0.0444 0.01477 0.00697 -0.1031 0.9236 0.0115
-3.500 -0.0119 0.01404 0.00601 -0.1042 0.9218 0.0136
-3.250 0.0216 0.01292 0.00517 -0.1059 0.9204 0.0873
-3.000 0.0531 0.01134 0.00490 -0.1084 0.9193 0.4237
-2.750 0.0860 0.01117 0.00476 -0.1095 0.9181 0.4831
-2.500 0.1094 0.01118 0.00468 -0.1087 0.9135 0.5162
-2.250 0.1381 0.01112 0.00465 -0.1089 0.9107 0.5545
-2.000 0.1684 0.01106 0.00461 -0.1095 0.9086 0.5868
-1.750 0.2004 0.01099 0.00450 -0.1104 0.9069 0.6029
-1.500 0.2332 0.01092 0.00437 -0.1115 0.9055 0.6151
-1.250 0.2582 0.01095 0.00433 -0.1111 0.9015 0.6264
-1.000 0.2858 0.01095 0.00432 -0.1111 0.8981 0.6380
-0.750 0.3162 0.01091 0.00429 -0.1118 0.8957 0.6504
-0.500 0.3479 0.01086 0.00425 -0.1127 0.8938 0.6632
-0.250 0.3804 0.01079 0.00422 -0.1137 0.8921 0.6766
0.000 0.4029 0.01087 0.00437 -0.1127 0.8870 0.6903
0.250 0.4313 0.01085 0.00442 -0.1129 0.8836 0.7052
0.500 0.4623 0.01078 0.00443 -0.1136 0.8810 0.7214
0.750 0.4948 0.01069 0.00442 -0.1145 0.8788 0.7391
1.000 0.5160 0.01076 0.00459 -0.1132 0.8724 0.7583
1.250 0.5454 0.01067 0.00466 -0.1134 0.8685 0.7799
1.500 0.5754 0.01055 0.00466 -0.1136 0.8646 0.8039
1.750 0.5976 0.01051 0.00476 -0.1123 0.8573 0.8331
2.000 0.6275 0.01030 0.00468 -0.1122 0.8518 0.8685
2.250 0.6520 0.01013 0.00466 -0.1111 0.8423 0.9275
2.500 0.6850 0.00995 0.00456 -0.1119 0.8303 1.0000
2.750 0.7157 0.00975 0.00446 -0.1120 0.8128 1.0000
3.000 0.7408 0.00965 0.00440 -0.1110 0.7888 1.0000
3.250 0.7663 0.00961 0.00439 -0.1102 0.7617 1.0000
3.500 0.7912 0.00960 0.00434 -0.1091 0.7144 1.0000
3.750 0.8099 0.01012 0.00417 -0.1065 0.5710 1.0000
4.000 0.8134 0.01149 0.00469 -0.1017 0.4135 1.0000
4.250 0.8206 0.01287 0.00537 -0.0982 0.2736 1.0000
4.500 0.8276 0.01461 0.00619 -0.0951 0.1141 1.0000
4.750 0.8407 0.01605 0.00696 -0.0929 0.0257 1.0000
5.000 0.8595 0.01704 0.00797 -0.0913 0.0055 1.0000
5.250 0.8805 0.01783 0.00894 -0.0899 0.0046 1.0000
5.500 0.9006 0.01878 0.01009 -0.0884 0.0041 1.0000
5.750 0.9197 0.01989 0.01138 -0.0867 0.0038 1.0000
6.000 0.9384 0.02121 0.01286 -0.0850 0.0036 1.0000
6.250 0.9584 0.02278 0.01460 -0.0835 0.0035 1.0000
6.500 0.9809 0.02472 0.01675 -0.0824 0.0034 1.0000
6.750 1.0057 0.02699 0.01928 -0.0817 0.0034 1.0000
7.000 1.0303 0.02973 0.02238 -0.0808 0.0034 1.0000
7.250 1.0517 0.03292 0.02602 -0.0793 0.0035 1.0000
7.500 1.0683 0.03646 0.03004 -0.0771 0.0036 1.0000
7.750 1.0797 0.04032 0.03438 -0.0743 0.0037 1.0000
8.000 1.0863 0.04439 0.03892 -0.0711 0.0038 1.0000
8.250 1.0885 0.04862 0.04355 -0.0675 0.0039 1.0000
8.500 1.0865 0.05284 0.04814 -0.0638 0.0040 1.0000
8.750 1.0807 0.05698 0.05259 -0.0601 0.0041 1.0000
9.000 1.0699 0.06073 0.05660 -0.0561 0.0041 1.0000
9.250 1.0553 0.06436 0.06044 -0.0521 0.0042 1.0000
9.500 1.0388 0.06819 0.06446 -0.0489 0.0043 1.0000
9.750 1.0212 0.07231 0.06875 -0.0469 0.0043 1.0000
10.000 1.0024 0.07696 0.07357 -0.0460 0.0043 1.0000
10.250 0.9832 0.08225 0.07900 -0.0465 0.0043 1.0000
10.500 0.9645 0.08830 0.08518 -0.0487 0.0044 1.0000
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Polar data table (+)
Polar graphs
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