MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 500,000 Max Cl/Cd: 107.77 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh121-il-500000-n5.txt Download as CSV file: xf-mh121-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.4433 0.14787 0.14536 -0.0274 1.0000 0.0047
-12.500 -0.4393 0.14456 0.14206 -0.0281 1.0000 0.0048
-12.250 -0.4357 0.14116 0.13867 -0.0289 1.0000 0.0050
-7.750 -0.3486 0.06393 0.06172 -0.0749 0.9715 0.0022
-7.500 -0.3390 0.05365 0.05137 -0.0907 0.9599 0.0021
-7.250 -0.3280 0.04613 0.04363 -0.0993 0.9522 0.0020
-7.000 -0.3107 0.03916 0.03636 -0.1055 0.9465 0.0020
-6.750 -0.2868 0.03248 0.02927 -0.1105 0.9427 0.0020
-6.500 -0.2645 0.02663 0.02294 -0.1128 0.9369 0.0020
-6.250 -0.2368 0.02173 0.01747 -0.1148 0.9335 0.0020
-6.000 -0.2057 0.01899 0.01429 -0.1165 0.9311 0.0022
-5.750 -0.1801 0.01627 0.01112 -0.1167 0.9260 0.0024
-5.500 -0.1516 0.01426 0.00880 -0.1175 0.9222 0.0029
-5.250 -0.1207 0.01358 0.00795 -0.1187 0.9193 0.0035
-5.000 -0.0915 0.01320 0.00752 -0.1194 0.9158 0.0046
-4.750 -0.0634 0.01278 0.00701 -0.1197 0.9118 0.0056
-4.500 -0.0349 0.01166 0.00573 -0.1200 0.9080 0.0057
-4.250 -0.0054 0.01070 0.00462 -0.1206 0.9050 0.0057
-4.000 0.0212 0.01001 0.00380 -0.1206 0.9006 0.0058
-3.750 0.0496 0.00948 0.00312 -0.1208 0.8969 0.0060
-3.500 0.0792 0.00907 0.00251 -0.1212 0.8938 0.0070
-3.250 0.1080 0.00850 0.00210 -0.1217 0.8906 0.0625
-3.000 0.1335 0.00725 0.00176 -0.1225 0.8867 0.3239
-2.750 0.1615 0.00701 0.00166 -0.1228 0.8834 0.3920
-2.500 0.1903 0.00687 0.00159 -0.1232 0.8805 0.4382
-2.250 0.2190 0.00680 0.00154 -0.1235 0.8777 0.4683
-2.000 0.2463 0.00674 0.00153 -0.1235 0.8742 0.4994
-1.750 0.2741 0.00668 0.00152 -0.1236 0.8710 0.5272
-1.500 0.3027 0.00666 0.00145 -0.1239 0.8681 0.5438
-1.000 0.3589 0.00663 0.00143 -0.1242 0.8622 0.5643
-0.750 0.3866 0.00663 0.00144 -0.1243 0.8588 0.5733
-0.250 0.4437 0.00663 0.00147 -0.1247 0.8528 0.5926
0.000 0.4706 0.00662 0.00151 -0.1246 0.8484 0.6026
0.250 0.4980 0.00662 0.00154 -0.1246 0.8435 0.6129
0.500 0.5263 0.00662 0.00156 -0.1247 0.8385 0.6240
0.750 0.5526 0.00661 0.00161 -0.1244 0.8314 0.6358
1.000 0.5800 0.00661 0.00167 -0.1243 0.8242 0.6478
1.250 0.6065 0.00660 0.00171 -0.1240 0.8150 0.6609
1.500 0.6326 0.00659 0.00175 -0.1236 0.8039 0.6746
1.750 0.6583 0.00659 0.00179 -0.1231 0.7892 0.6894
2.000 0.6830 0.00660 0.00182 -0.1223 0.7677 0.7052
2.250 0.7071 0.00664 0.00187 -0.1214 0.7391 0.7224
2.500 0.7296 0.00677 0.00199 -0.1201 0.6973 0.7413
2.750 0.7445 0.00728 0.00215 -0.1173 0.6044 0.7617
3.000 0.7491 0.00852 0.00265 -0.1127 0.4357 0.7852
3.250 0.7494 0.01046 0.00341 -0.1080 0.1779 0.8129
3.500 0.7612 0.01157 0.00395 -0.1052 0.0473 0.8489
3.750 0.7778 0.01178 0.00421 -0.1028 0.0262 0.9077
4.000 0.8007 0.01224 0.00459 -0.1019 0.0031 1.0000
4.250 0.8250 0.01260 0.00501 -0.1012 0.0020 1.0000
4.500 0.8489 0.01301 0.00552 -0.1004 0.0018 1.0000
4.750 0.8721 0.01351 0.00619 -0.0995 0.0017 1.0000
5.000 0.8942 0.01414 0.00694 -0.0984 0.0017 1.0000
5.250 0.9153 0.01489 0.00781 -0.0971 0.0016 1.0000
5.500 0.9352 0.01583 0.00888 -0.0955 0.0016 1.0000
5.750 0.9544 0.01696 0.01014 -0.0938 0.0016 1.0000
6.000 0.9742 0.01829 0.01162 -0.0923 0.0016 1.0000
6.250 0.9955 0.01989 0.01340 -0.0909 0.0017 1.0000
6.500 1.0185 0.02192 0.01566 -0.0899 0.0017 1.0000
6.750 1.0416 0.02422 0.01823 -0.0888 0.0017 1.0000
7.000 1.0625 0.02708 0.02146 -0.0874 0.0018 1.0000
7.250 1.0789 0.03045 0.02523 -0.0852 0.0019 1.0000
7.500 1.0893 0.03443 0.02966 -0.0821 0.0019 1.0000
8.000 1.1080 0.04022 0.03600 -0.0767 0.0022 1.0000
8.250 1.1186 0.04238 0.03838 -0.0743 0.0023 1.0000
8.500 1.1267 0.04550 0.04185 -0.0713 0.0025 1.0000
8.750 1.1023 0.05764 0.05460 -0.0634 0.0037 1.0000
9.000 1.0881 0.06213 0.05932 -0.0590 0.0039 1.0000
9.250 1.0694 0.06580 0.06316 -0.0544 0.0041 1.0000
9.500 1.0495 0.06962 0.06714 -0.0509 0.0042 1.0000
9.750 1.0306 0.07368 0.07134 -0.0487 0.0042 1.0000
10.000 1.0104 0.07837 0.07616 -0.0479 0.0043 1.0000
10.250 0.9909 0.08367 0.08158 -0.0486 0.0042 1.0000
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Polar data table (+)
Polar graphs
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