MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 500,000 Max Cl/Cd: 113.57 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh116-il-500000-n5.txt Download as CSV file: xf-mh116-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3148 0.09774 0.09549 -0.0456 0.9970 0.0081
-9.250 -0.2135 0.07398 0.07184 -0.0617 0.9743 0.0055
-9.000 -0.2098 0.06850 0.06637 -0.0651 0.9701 0.0054
-8.500 -0.2887 0.07563 0.07343 -0.0631 0.9751 0.0054
-8.250 -0.2828 0.06968 0.06749 -0.0693 0.9660 0.0052
-8.000 -0.2735 0.06222 0.06004 -0.0791 0.9555 0.0051
-7.750 -0.2803 0.03331 0.03061 -0.1143 0.9286 0.0045
-7.500 -0.2751 0.02497 0.02141 -0.1186 0.9128 0.0043
-7.250 -0.2579 0.02111 0.01694 -0.1193 0.9022 0.0042
-7.000 -0.2370 0.01868 0.01406 -0.1193 0.8929 0.0042
-6.750 -0.2136 0.01691 0.01193 -0.1192 0.8848 0.0042
-6.500 -0.1893 0.01554 0.01026 -0.1190 0.8767 0.0042
-6.250 -0.1642 0.01447 0.00897 -0.1187 0.8692 0.0042
-6.000 -0.1386 0.01355 0.00784 -0.1185 0.8616 0.0043
-5.750 -0.1127 0.01277 0.00690 -0.1183 0.8543 0.0043
-5.500 -0.0863 0.01212 0.00607 -0.1182 0.8471 0.0044
-5.250 -0.0598 0.01155 0.00537 -0.1180 0.8399 0.0045
-5.000 -0.0329 0.01108 0.00475 -0.1178 0.8330 0.0047
-4.750 -0.0058 0.01065 0.00421 -0.1177 0.8260 0.0050
-4.500 0.0215 0.01032 0.00375 -0.1176 0.8193 0.0054
-4.250 0.0489 0.00996 0.00329 -0.1175 0.8124 0.0065
-4.000 0.0762 0.00961 0.00289 -0.1173 0.8057 0.0131
-3.750 0.1034 0.00931 0.00262 -0.1173 0.7990 0.0271
-3.500 0.1305 0.00897 0.00241 -0.1173 0.7923 0.0603
-3.250 0.1579 0.00874 0.00225 -0.1173 0.7857 0.0865
-3.000 0.1854 0.00857 0.00210 -0.1173 0.7789 0.1091
-2.750 0.2130 0.00842 0.00196 -0.1173 0.7725 0.1318
-2.500 0.2405 0.00827 0.00185 -0.1173 0.7656 0.1604
-2.250 0.2680 0.00814 0.00176 -0.1173 0.7591 0.1874
-2.000 0.2956 0.00802 0.00168 -0.1173 0.7522 0.2154
-1.750 0.3232 0.00792 0.00160 -0.1173 0.7457 0.2454
-1.500 0.3508 0.00783 0.00155 -0.1173 0.7386 0.2749
-1.250 0.3783 0.00772 0.00151 -0.1172 0.7320 0.3125
-1.000 0.4057 0.00761 0.00148 -0.1172 0.7245 0.3543
-0.750 0.4331 0.00751 0.00147 -0.1172 0.7173 0.3993
-0.500 0.4604 0.00741 0.00147 -0.1171 0.7093 0.4484
-0.250 0.4876 0.00731 0.00148 -0.1170 0.7012 0.5019
0.000 0.5144 0.00722 0.00150 -0.1169 0.6929 0.5586
0.250 0.5412 0.00710 0.00154 -0.1167 0.6840 0.6217
0.500 0.5674 0.00700 0.00160 -0.1163 0.6756 0.6866
0.750 0.5928 0.00690 0.00166 -0.1157 0.6667 0.7538
1.000 0.6167 0.00679 0.00173 -0.1147 0.6575 0.8235
1.250 0.6380 0.00670 0.00178 -0.1130 0.6485 0.8949
1.500 0.6708 0.00666 0.00176 -0.1139 0.6383 0.9876
1.750 0.6984 0.00675 0.00181 -0.1139 0.6277 1.0000
2.000 0.7252 0.00686 0.00187 -0.1137 0.6170 1.0000
2.250 0.7518 0.00698 0.00194 -0.1134 0.6055 1.0000
2.500 0.7782 0.00711 0.00202 -0.1132 0.5930 1.0000
2.750 0.8044 0.00725 0.00210 -0.1129 0.5796 1.0000
3.000 0.8304 0.00740 0.00222 -0.1125 0.5642 1.0000
3.250 0.8562 0.00757 0.00233 -0.1122 0.5476 1.0000
3.500 0.8814 0.00777 0.00246 -0.1117 0.5288 1.0000
3.750 0.9063 0.00798 0.00262 -0.1112 0.5081 1.0000
4.000 0.9307 0.00823 0.00279 -0.1106 0.4853 1.0000
4.250 0.9545 0.00853 0.00298 -0.1099 0.4583 1.0000
4.500 0.9777 0.00887 0.00320 -0.1091 0.4291 1.0000
4.750 1.0004 0.00925 0.00346 -0.1083 0.3975 1.0000
5.000 1.0223 0.00969 0.00377 -0.1073 0.3631 1.0000
5.250 1.0442 0.01014 0.00409 -0.1064 0.3318 1.0000
5.500 1.0661 0.01059 0.00441 -0.1055 0.3026 1.0000
5.750 1.0875 0.01108 0.00477 -0.1045 0.2713 1.0000
6.000 1.1087 0.01157 0.00514 -0.1035 0.2425 1.0000
6.250 1.1295 0.01207 0.00556 -0.1024 0.2149 1.0000
6.500 1.1503 0.01257 0.00596 -0.1014 0.1911 1.0000
6.750 1.1700 0.01314 0.00641 -0.1001 0.1646 1.0000
7.000 1.1887 0.01376 0.00690 -0.0988 0.1375 1.0000
7.250 1.2068 0.01440 0.00741 -0.0973 0.1130 1.0000
7.500 1.2256 0.01497 0.00791 -0.0960 0.0945 1.0000
7.750 1.2420 0.01568 0.00850 -0.0943 0.0727 1.0000
8.000 1.2584 0.01633 0.00910 -0.0926 0.0561 1.0000
8.250 1.2709 0.01711 0.00976 -0.0902 0.0379 1.0000
8.500 1.2828 0.01791 0.01047 -0.0877 0.0235 1.0000
8.750 1.2947 0.01872 0.01122 -0.0853 0.0144 1.0000
9.000 1.3093 0.01936 0.01190 -0.0834 0.0112 1.0000
9.250 1.3222 0.02013 0.01269 -0.0813 0.0075 1.0000
9.500 1.3332 0.02104 0.01361 -0.0789 0.0040 1.0000
9.750 1.3449 0.02192 0.01455 -0.0768 0.0029 1.0000
10.000 1.3566 0.02282 0.01555 -0.0748 0.0023 1.0000
10.250 1.3667 0.02387 0.01668 -0.0726 0.0019 1.0000
10.500 1.3759 0.02501 0.01793 -0.0704 0.0017 1.0000
10.750 1.3860 0.02611 0.01914 -0.0685 0.0016 1.0000
11.000 1.3949 0.02733 0.02048 -0.0665 0.0015 1.0000
11.250 1.4036 0.02860 0.02186 -0.0647 0.0015 1.0000
11.500 1.4107 0.03005 0.02342 -0.0628 0.0014 1.0000
11.750 1.4168 0.03162 0.02512 -0.0611 0.0013 1.0000
12.000 1.4219 0.03334 0.02696 -0.0593 0.0013 1.0000
12.250 1.4268 0.03514 0.02888 -0.0578 0.0013 1.0000
12.500 1.4292 0.03723 0.03110 -0.0562 0.0012 1.0000
12.750 1.4311 0.03945 0.03349 -0.0549 0.0012 1.0000
13.000 1.4320 0.04185 0.03602 -0.0537 0.0012 1.0000
13.250 1.4322 0.04442 0.03873 -0.0527 0.0012 1.0000
13.500 1.4307 0.04729 0.04174 -0.0519 0.0011 1.0000
13.750 1.4280 0.05041 0.04501 -0.0513 0.0011 1.0000
14.000 1.4255 0.05366 0.04840 -0.0509 0.0011 1.0000
14.250 1.4210 0.05729 0.05218 -0.0509 0.0011 1.0000
14.500 1.4167 0.06107 0.05611 -0.0511 0.0011 1.0000
14.750 1.4104 0.06533 0.06052 -0.0517 0.0011 1.0000
15.000 1.4035 0.06985 0.06520 -0.0526 0.0011 1.0000
15.250 1.3943 0.07495 0.07047 -0.0539 0.0011 1.0000
15.500 1.3859 0.08017 0.07585 -0.0556 0.0011 1.0000
15.750 1.3763 0.08580 0.08165 -0.0576 0.0011 1.0000
16.000 1.3653 0.09192 0.08793 -0.0600 0.0011 1.0000
16.250 1.3537 0.09843 0.09460 -0.0629 0.0011 1.0000
16.500 1.3413 0.10532 0.10166 -0.0662 0.0011 1.0000
16.750 1.3285 0.11251 0.10901 -0.0698 0.0011 1.0000
17.000 1.3152 0.12005 0.11672 -0.0738 0.0011 1.0000
17.250 1.3020 0.12782 0.12464 -0.0781 0.0011 1.0000
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Polar data table (+)
Polar graphs
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