MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 500,000 Max Cl/Cd: 125.59 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh116-il-500000.txt Download as CSV file: xf-mh116-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 116 9.84%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3310 0.10266 0.10049 -0.0388 1.0000 0.0158
-9.250 -0.3346 0.10053 0.09840 -0.0376 1.0000 0.0160
-9.000 -0.3404 0.09849 0.09640 -0.0362 0.9999 0.0163
-8.750 -0.3255 0.09417 0.09208 -0.0409 0.9979 0.0168
-8.500 -0.3104 0.08963 0.08755 -0.0460 0.9954 0.0174
-8.250 -0.2961 0.08489 0.08281 -0.0515 0.9921 0.0183
-8.000 -0.2817 0.07982 0.07775 -0.0576 0.9875 0.0191
-7.750 -0.2618 0.07376 0.07170 -0.0668 0.9832 0.0204
-7.500 -0.2454 0.06845 0.06640 -0.0745 0.9745 0.0208
-7.250 -0.2171 0.06010 0.05803 -0.0891 0.9700 0.0209
-7.000 -0.1925 0.04855 0.04625 -0.1059 0.9606 0.0210
-6.750 -0.1862 0.03679 0.03411 -0.1175 0.9502 0.0223
-6.500 -0.1612 0.03377 0.03095 -0.1204 0.9445 0.0231
-6.000 -0.1258 0.01897 0.01451 -0.1230 0.9251 0.0115
-5.750 -0.1008 0.01571 0.01055 -0.1224 0.9175 0.0097
-5.500 -0.0743 0.01467 0.00930 -0.1221 0.9103 0.0094
-5.250 -0.0476 0.01364 0.00808 -0.1219 0.9034 0.0093
-5.000 -0.0219 0.01258 0.00686 -0.1215 0.8959 0.0093
-4.750 0.0042 0.01142 0.00552 -0.1212 0.8891 0.0095
-4.500 0.0304 0.01064 0.00461 -0.1209 0.8816 0.0101
-4.250 0.0580 0.01012 0.00395 -0.1208 0.8750 0.0117
-4.000 0.0846 0.00932 0.00320 -0.1204 0.8676 0.0403
-3.750 0.1121 0.00903 0.00295 -0.1204 0.8611 0.0681
-3.500 0.1389 0.00875 0.00281 -0.1204 0.8538 0.1055
-3.250 0.1665 0.00852 0.00264 -0.1203 0.8473 0.1379
-3.000 0.1937 0.00832 0.00249 -0.1203 0.8402 0.1712
-2.750 0.2213 0.00814 0.00236 -0.1203 0.8336 0.2068
-2.500 0.2485 0.00795 0.00226 -0.1202 0.8265 0.2498
-2.250 0.2761 0.00778 0.00217 -0.1202 0.8200 0.2925
-2.000 0.3034 0.00761 0.00210 -0.1201 0.8129 0.3404
-1.750 0.3308 0.00745 0.00203 -0.1201 0.8062 0.3931
-1.500 0.3580 0.00728 0.00200 -0.1200 0.7992 0.4508
-1.250 0.3851 0.00710 0.00198 -0.1199 0.7924 0.5209
-1.000 0.4117 0.00691 0.00198 -0.1196 0.7851 0.5974
-0.750 0.4379 0.00674 0.00199 -0.1192 0.7781 0.6765
-0.500 0.4628 0.00656 0.00203 -0.1185 0.7704 0.7568
-0.250 0.4861 0.00642 0.00205 -0.1171 0.7633 0.8344
0.000 0.5067 0.00628 0.00206 -0.1151 0.7550 0.9103
0.250 0.5459 0.00620 0.00195 -0.1173 0.7480 0.9983
0.500 0.5731 0.00625 0.00195 -0.1172 0.7395 1.0000
0.750 0.6005 0.00633 0.00196 -0.1171 0.7318 1.0000
1.000 0.6276 0.00639 0.00197 -0.1169 0.7234 1.0000
1.250 0.6548 0.00647 0.00200 -0.1168 0.7148 1.0000
1.500 0.6820 0.00656 0.00201 -0.1166 0.7067 1.0000
1.750 0.7089 0.00663 0.00207 -0.1164 0.6974 1.0000
2.000 0.7359 0.00671 0.00212 -0.1163 0.6884 1.0000
2.500 0.7895 0.00690 0.00223 -0.1158 0.6689 1.0000
2.750 0.8162 0.00699 0.00232 -0.1156 0.6585 1.0000
3.000 0.8427 0.00710 0.00240 -0.1153 0.6475 1.0000
3.250 0.8690 0.00722 0.00248 -0.1150 0.6360 1.0000
3.500 0.8950 0.00735 0.00258 -0.1146 0.6234 1.0000
4.250 0.9720 0.00777 0.00296 -0.1133 0.5802 1.0000
4.500 0.9972 0.00794 0.00310 -0.1128 0.5627 1.0000
4.750 1.0217 0.00815 0.00328 -0.1122 0.5431 1.0000
5.000 1.0457 0.00838 0.00347 -0.1115 0.5200 1.0000
5.250 1.0689 0.00866 0.00368 -0.1106 0.4943 1.0000
5.500 1.0913 0.00900 0.00392 -0.1097 0.4639 1.0000
6.000 1.1325 0.00994 0.00458 -0.1072 0.3895 1.0000
6.250 1.1524 0.01047 0.00497 -0.1059 0.3520 1.0000
6.500 1.1717 0.01105 0.00539 -0.1046 0.3161 1.0000
6.750 1.1897 0.01172 0.00587 -0.1030 0.2742 1.0000
7.000 1.2071 0.01243 0.00638 -0.1014 0.2337 1.0000
7.250 1.2244 0.01314 0.00690 -0.0998 0.1967 1.0000
7.500 1.2411 0.01386 0.00746 -0.0981 0.1639 1.0000
7.750 1.2570 0.01463 0.00808 -0.0963 0.1316 1.0000
8.000 1.2727 0.01537 0.00868 -0.0945 0.1060 1.0000
8.250 1.2865 0.01617 0.00933 -0.0924 0.0804 1.0000
8.500 1.2988 0.01694 0.00998 -0.0900 0.0608 1.0000
8.750 1.3117 0.01768 0.01064 -0.0877 0.0460 1.0000
9.000 1.3236 0.01847 0.01139 -0.0853 0.0336 1.0000
9.250 1.3324 0.01949 0.01231 -0.0825 0.0197 1.0000
9.500 1.3308 0.02128 0.01403 -0.0782 0.0065 1.0000
9.750 1.3372 0.02259 0.01546 -0.0752 0.0052 1.0000
10.000 1.3466 0.02368 0.01666 -0.0729 0.0046 1.0000
10.250 1.3549 0.02488 0.01800 -0.0705 0.0043 1.0000
10.500 1.3618 0.02621 0.01943 -0.0681 0.0040 1.0000
10.750 1.3675 0.02769 0.02102 -0.0658 0.0038 1.0000
11.000 1.3700 0.02948 0.02292 -0.0634 0.0036 1.0000
11.250 1.3729 0.03130 0.02487 -0.0612 0.0036 1.0000
11.500 1.3718 0.03358 0.02728 -0.0589 0.0035 1.0000
11.750 1.3712 0.03593 0.02976 -0.0569 0.0034 1.0000
12.000 1.3686 0.03863 0.03260 -0.0549 0.0034 1.0000
12.250 1.3697 0.04104 0.03515 -0.0535 0.0034 1.0000
12.500 1.3652 0.04427 0.03853 -0.0519 0.0033 1.0000
12.750 1.3642 0.04719 0.04161 -0.0508 0.0033 1.0000
13.000 1.3633 0.05022 0.04479 -0.0499 0.0033 1.0000
13.250 1.3621 0.05337 0.04810 -0.0492 0.0033 1.0000
13.500 1.3603 0.05672 0.05160 -0.0487 0.0033 1.0000
13.750 1.3570 0.06038 0.05546 -0.0484 0.0034 1.0000
14.000 1.3537 0.06412 0.05937 -0.0485 0.0034 1.0000
14.250 1.3487 0.06824 0.06367 -0.0488 0.0034 1.0000
14.500 1.3434 0.07254 0.06815 -0.0495 0.0034 1.0000
14.750 1.3360 0.07737 0.07317 -0.0507 0.0034 1.0000
15.000 1.3275 0.08256 0.07855 -0.0522 0.0035 1.0000
15.250 1.3161 0.08854 0.08475 -0.0542 0.0035 1.0000
15.500 1.3035 0.09503 0.09146 -0.0569 0.0036 1.0000
15.750 1.2870 0.10263 0.09931 -0.0603 0.0037 1.0000
16.000 1.2672 0.11133 0.10826 -0.0647 0.0038 1.0000
16.250 1.2459 0.12090 0.11807 -0.0700 0.0040 1.0000
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Polar data table (+)
Polar graphs
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