MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 1,000,000 Max Cl/Cd: 130.96 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh116-il-1000000-n5.txt Download as CSV file: xf-mh116-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3275 0.02716 0.02461 -0.1192 0.8943 0.0031
-8.000 -0.3202 0.02285 0.01980 -0.1198 0.8806 0.0030
-7.750 -0.3052 0.01990 0.01640 -0.1198 0.8700 0.0030
-7.500 -0.2860 0.01779 0.01393 -0.1195 0.8606 0.0030
-7.250 -0.2642 0.01613 0.01196 -0.1193 0.8522 0.0030
-7.000 -0.2412 0.01474 0.01029 -0.1189 0.8444 0.0029
-6.750 -0.2169 0.01361 0.00894 -0.1187 0.8365 0.0029
-6.500 -0.1921 0.01264 0.00775 -0.1184 0.8291 0.0029
-6.250 -0.1664 0.01187 0.00681 -0.1182 0.8217 0.0029
-6.000 -0.1405 0.01118 0.00596 -0.1180 0.8148 0.0029
-5.750 -0.1141 0.01059 0.00524 -0.1179 0.8076 0.0029
-5.500 -0.0874 0.01009 0.00461 -0.1177 0.8010 0.0030
-5.250 -0.0604 0.00966 0.00406 -0.1176 0.7940 0.0030
-5.000 -0.0332 0.00929 0.00360 -0.1175 0.7876 0.0030
-4.750 -0.0058 0.00896 0.00318 -0.1174 0.7807 0.0031
-4.500 0.0216 0.00870 0.00283 -0.1174 0.7743 0.0032
-4.250 0.0493 0.00847 0.00252 -0.1173 0.7675 0.0033
-4.000 0.0769 0.00825 0.00221 -0.1172 0.7612 0.0036
-3.750 0.1047 0.00805 0.00196 -0.1172 0.7544 0.0048
-3.500 0.1322 0.00780 0.00173 -0.1172 0.7481 0.0163
-3.250 0.1599 0.00759 0.00157 -0.1172 0.7413 0.0327
-3.000 0.1874 0.00742 0.00143 -0.1172 0.7348 0.0522
-2.750 0.2152 0.00724 0.00132 -0.1173 0.7282 0.0760
-2.250 0.2706 0.00694 0.00116 -0.1174 0.7147 0.1343
-2.000 0.2982 0.00684 0.00109 -0.1174 0.7078 0.1615
-1.750 0.3262 0.00676 0.00104 -0.1174 0.7006 0.1807
-1.500 0.3538 0.00670 0.00100 -0.1174 0.6931 0.2060
-1.250 0.3816 0.00663 0.00097 -0.1174 0.6848 0.2308
-1.000 0.4092 0.00658 0.00094 -0.1174 0.6764 0.2547
-0.750 0.4368 0.00652 0.00093 -0.1174 0.6674 0.2876
-0.500 0.4644 0.00645 0.00093 -0.1174 0.6587 0.3233
-0.250 0.4919 0.00641 0.00094 -0.1174 0.6500 0.3579
0.000 0.5194 0.00635 0.00095 -0.1174 0.6406 0.3974
0.250 0.5469 0.00630 0.00097 -0.1174 0.6314 0.4399
0.500 0.5741 0.00626 0.00101 -0.1173 0.6216 0.4837
0.750 0.6013 0.00621 0.00106 -0.1173 0.6111 0.5346
1.000 0.6285 0.00616 0.00111 -0.1172 0.6007 0.5874
1.250 0.6555 0.00612 0.00118 -0.1171 0.5898 0.6426
1.500 0.6820 0.00609 0.00126 -0.1169 0.5780 0.7014
1.750 0.7081 0.00605 0.00135 -0.1165 0.5651 0.7628
2.000 0.7331 0.00603 0.00145 -0.1159 0.5513 0.8237
2.250 0.7559 0.00601 0.00154 -0.1147 0.5365 0.8882
2.750 0.8093 0.00618 0.00169 -0.1142 0.4992 1.0000
3.000 0.8350 0.00638 0.00181 -0.1139 0.4761 1.0000
3.250 0.8604 0.00662 0.00195 -0.1135 0.4516 1.0000
3.500 0.8854 0.00689 0.00210 -0.1130 0.4244 1.0000
3.750 0.9099 0.00720 0.00228 -0.1125 0.3948 1.0000
4.000 0.9344 0.00751 0.00247 -0.1120 0.3672 1.0000
4.250 0.9583 0.00786 0.00269 -0.1114 0.3367 1.0000
4.500 0.9820 0.00822 0.00292 -0.1108 0.3071 1.0000
4.750 1.0060 0.00856 0.00314 -0.1102 0.2816 1.0000
5.000 1.0296 0.00893 0.00340 -0.1095 0.2554 1.0000
5.250 1.0530 0.00930 0.00367 -0.1089 0.2301 1.0000
5.500 1.0759 0.00971 0.00395 -0.1081 0.2042 1.0000
5.750 1.0988 0.01010 0.00424 -0.1074 0.1814 1.0000
6.000 1.1220 0.01046 0.00453 -0.1067 0.1634 1.0000
6.250 1.1422 0.01104 0.00494 -0.1055 0.1299 1.0000
6.500 1.1613 0.01170 0.00540 -0.1042 0.0951 1.0000
6.750 1.1811 0.01227 0.00583 -0.1030 0.0707 1.0000
7.000 1.2013 0.01280 0.00626 -0.1018 0.0530 1.0000
7.250 1.2224 0.01325 0.00665 -0.1008 0.0423 1.0000
7.500 1.2422 0.01377 0.00711 -0.0996 0.0304 1.0000
7.750 1.2597 0.01443 0.00769 -0.0980 0.0160 1.0000
8.000 1.2784 0.01498 0.00821 -0.0966 0.0100 1.0000
8.250 1.2969 0.01552 0.00873 -0.0951 0.0059 1.0000
8.500 1.3136 0.01607 0.00929 -0.0933 0.0027 1.0000
8.750 1.3288 0.01663 0.00987 -0.0913 0.0014 1.0000
9.000 1.3452 0.01710 0.01039 -0.0894 0.0013 1.0000
9.250 1.3597 0.01770 0.01103 -0.0873 0.0010 1.0000
9.500 1.3728 0.01840 0.01182 -0.0850 0.0008 1.0000
9.750 1.3871 0.01901 0.01251 -0.0830 0.0007 1.0000
10.000 1.4009 0.01968 0.01323 -0.0810 0.0007 1.0000
10.250 1.4139 0.02041 0.01403 -0.0790 0.0007 1.0000
10.500 1.4260 0.02121 0.01491 -0.0769 0.0007 1.0000
10.750 1.4376 0.02207 0.01585 -0.0748 0.0007 1.0000
11.000 1.4480 0.02303 0.01689 -0.0727 0.0007 1.0000
11.250 1.4584 0.02402 0.01795 -0.0707 0.0007 1.0000
11.500 1.4671 0.02516 0.01919 -0.0687 0.0006 1.0000
11.750 1.4754 0.02638 0.02050 -0.0666 0.0006 1.0000
12.000 1.4823 0.02774 0.02196 -0.0646 0.0006 1.0000
12.250 1.4894 0.02913 0.02345 -0.0628 0.0006 1.0000
12.500 1.4938 0.03080 0.02524 -0.0609 0.0006 1.0000
12.750 1.4982 0.03254 0.02708 -0.0592 0.0006 1.0000
13.000 1.5016 0.03442 0.02907 -0.0575 0.0006 1.0000
13.250 1.5039 0.03648 0.03125 -0.0560 0.0006 1.0000
13.500 1.5048 0.03876 0.03365 -0.0547 0.0006 1.0000
13.750 1.5038 0.04134 0.03636 -0.0534 0.0006 1.0000
14.000 1.5037 0.04393 0.03906 -0.0525 0.0006 1.0000
14.250 1.5013 0.04688 0.04214 -0.0517 0.0006 1.0000
14.500 1.4993 0.04991 0.04530 -0.0512 0.0006 1.0000
14.750 1.4946 0.05345 0.04897 -0.0510 0.0006 1.0000
15.000 1.4899 0.05713 0.05279 -0.0511 0.0006 1.0000
15.250 1.4806 0.06166 0.05748 -0.0515 0.0006 1.0000
15.500 1.4745 0.06597 0.06192 -0.0523 0.0006 1.0000
15.750 1.4660 0.07082 0.06691 -0.0534 0.0006 1.0000
16.000 1.4561 0.07614 0.07238 -0.0550 0.0006 1.0000
16.250 1.4449 0.08194 0.07833 -0.0570 0.0006 1.0000
16.500 1.4328 0.08817 0.08471 -0.0595 0.0006 1.0000
16.750 1.4196 0.09485 0.09154 -0.0624 0.0006 1.0000
17.000 1.4048 0.10214 0.09900 -0.0658 0.0006 1.0000
17.250 1.3901 0.10970 0.10671 -0.0696 0.0006 1.0000
17.500 1.3752 0.11751 0.11467 -0.0737 0.0006 1.0000
17.750 1.3596 0.12572 0.12302 -0.0782 0.0006 1.0000
18.000 1.3439 0.13414 0.13157 -0.0830 0.0006 1.0000
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Polar data table (+)
Polar graphs
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