MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 200,000 Max Cl/Cd: 89.47 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh116-il-200000.txt Download as CSV file: xf-mh116-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3578 0.10032 0.09718 -0.0387 1.0000 0.0407
-8.250 -0.3733 0.09914 0.09609 -0.0362 1.0000 0.0408
-8.000 -0.3899 0.09810 0.09513 -0.0334 1.0000 0.0408
-7.750 -0.3830 0.09403 0.09108 -0.0389 0.9957 0.0409
-7.500 -0.3745 0.08743 0.08451 -0.0408 0.9925 0.0421
-7.250 -0.3554 0.08412 0.08119 -0.0424 0.9883 0.0434
-7.000 -0.3338 0.08003 0.07707 -0.0476 0.9836 0.0451
-6.750 -0.3144 0.07519 0.07221 -0.0546 0.9758 0.0469
-6.500 -0.2840 0.06776 0.06474 -0.0692 0.9698 0.0509
-6.250 -0.2592 0.05565 0.05227 -0.0894 0.9584 0.0543
-6.000 -0.2319 0.05222 0.04888 -0.0920 0.9562 0.0558
-5.750 -0.2125 0.03620 0.03175 -0.1016 0.9458 0.0311
-5.500 -0.1784 0.02800 0.02261 -0.1059 0.9432 0.0226
-5.250 -0.1513 0.02598 0.02006 -0.1059 0.9360 0.0212
-5.000 -0.1155 0.02330 0.01691 -0.1079 0.9328 0.0208
-4.750 -0.0770 0.02042 0.01358 -0.1103 0.9308 0.0213
-4.500 -0.0376 0.01807 0.01104 -0.1127 0.9293 0.0231
-4.250 -0.0124 0.01716 0.01005 -0.1122 0.9217 0.0272
-4.000 0.0252 0.01582 0.00867 -0.1142 0.9187 0.0497
-3.750 0.0641 0.01495 0.00792 -0.1165 0.9163 0.0982
-3.500 0.0918 0.01449 0.00748 -0.1166 0.9096 0.1333
-3.250 0.1259 0.01393 0.00703 -0.1179 0.9053 0.1747
-3.000 0.1626 0.01337 0.00662 -0.1197 0.9023 0.2258
-2.750 0.1887 0.01308 0.00642 -0.1195 0.8949 0.2758
-2.500 0.2213 0.01262 0.00615 -0.1205 0.8904 0.3394
-2.250 0.2530 0.01221 0.00594 -0.1212 0.8859 0.4122
-2.000 0.2784 0.01191 0.00588 -0.1207 0.8785 0.4922
-1.750 0.3092 0.01145 0.00571 -0.1210 0.8744 0.5942
-1.500 0.3301 0.01121 0.00578 -0.1192 0.8662 0.6922
-1.250 0.3539 0.01086 0.00568 -0.1174 0.8612 0.7991
-1.000 0.3749 0.01068 0.00565 -0.1150 0.8538 0.9076
-0.750 0.4243 0.01046 0.00532 -0.1192 0.8493 1.0000
-0.500 0.4525 0.01049 0.00522 -0.1193 0.8428 1.0000
-0.250 0.4801 0.01053 0.00514 -0.1192 0.8354 1.0000
0.000 0.5080 0.01058 0.00507 -0.1191 0.8285 1.0000
0.250 0.5358 0.01061 0.00501 -0.1190 0.8212 1.0000
0.500 0.5629 0.01068 0.00500 -0.1188 0.8135 1.0000
0.750 0.5914 0.01069 0.00493 -0.1187 0.8063 1.0000
1.000 0.6176 0.01078 0.00497 -0.1183 0.7978 1.0000
1.250 0.6471 0.01078 0.00489 -0.1184 0.7911 1.0000
1.500 0.6724 0.01089 0.00497 -0.1179 0.7818 1.0000
1.750 0.7006 0.01093 0.00495 -0.1178 0.7742 1.0000
2.000 0.7274 0.01099 0.00500 -0.1174 0.7653 1.0000
2.250 0.7537 0.01108 0.00507 -0.1170 0.7561 1.0000
2.500 0.7826 0.01111 0.00503 -0.1170 0.7483 1.0000
2.750 0.8081 0.01119 0.00513 -0.1164 0.7379 1.0000
3.000 0.8342 0.01128 0.00524 -0.1159 0.7278 1.0000
3.250 0.8614 0.01133 0.00528 -0.1156 0.7181 1.0000
3.500 0.8886 0.01139 0.00530 -0.1152 0.7077 1.0000
3.750 0.9138 0.01147 0.00543 -0.1146 0.6956 1.0000
4.000 0.9393 0.01154 0.00553 -0.1139 0.6831 1.0000
4.250 0.9647 0.01162 0.00562 -0.1133 0.6699 1.0000
4.500 0.9899 0.01171 0.00572 -0.1126 0.6558 1.0000
4.750 1.0149 0.01180 0.00583 -0.1118 0.6409 1.0000
5.000 1.0397 0.01191 0.00597 -0.1110 0.6249 1.0000
5.250 1.0634 0.01205 0.00614 -0.1101 0.6068 1.0000
5.500 1.0866 0.01220 0.00632 -0.1090 0.5866 1.0000
5.750 1.1092 0.01240 0.00651 -0.1079 0.5642 1.0000
6.000 1.1309 0.01264 0.00673 -0.1066 0.5392 1.0000
6.250 1.1514 0.01293 0.00703 -0.1051 0.5098 1.0000
6.500 1.1706 0.01332 0.00735 -0.1034 0.4759 1.0000
6.750 1.1879 0.01382 0.00774 -0.1014 0.4372 1.0000
7.000 1.2032 0.01446 0.00822 -0.0992 0.3953 1.0000
7.250 1.2168 0.01522 0.00881 -0.0968 0.3525 1.0000
7.500 1.2292 0.01606 0.00948 -0.0943 0.3106 1.0000
7.750 1.2401 0.01700 0.01022 -0.0917 0.2685 1.0000
8.000 1.2497 0.01800 0.01107 -0.0889 0.2283 1.0000
8.250 1.2574 0.01904 0.01192 -0.0859 0.1936 1.0000
8.500 1.2654 0.02005 0.01281 -0.0829 0.1642 1.0000
8.750 1.2728 0.02115 0.01379 -0.0800 0.1394 1.0000
9.000 1.2813 0.02225 0.01482 -0.0773 0.1159 1.0000
9.250 1.2886 0.02347 0.01598 -0.0746 0.0951 1.0000
9.500 1.2923 0.02498 0.01735 -0.0717 0.0746 1.0000
9.750 1.2968 0.02655 0.01884 -0.0690 0.0534 1.0000
10.000 1.2966 0.02854 0.02076 -0.0659 0.0385 1.0000
10.250 1.2968 0.03062 0.02285 -0.0631 0.0279 1.0000
10.500 1.2925 0.03316 0.02542 -0.0601 0.0213 1.0000
10.750 1.2986 0.03493 0.02735 -0.0582 0.0170 1.0000
11.000 1.2945 0.03767 0.03014 -0.0560 0.0144 1.0000
11.250 1.2938 0.04038 0.03299 -0.0539 0.0135 1.0000
11.500 1.2981 0.04270 0.03548 -0.0523 0.0125 1.0000
11.750 1.3022 0.04521 0.03814 -0.0507 0.0118 1.0000
12.000 1.3066 0.04777 0.04086 -0.0494 0.0112 1.0000
12.250 1.3113 0.05044 0.04369 -0.0482 0.0108 1.0000
12.500 1.3143 0.05333 0.04673 -0.0471 0.0104 1.0000
12.750 1.3167 0.05645 0.05004 -0.0462 0.0101 1.0000
13.000 1.3174 0.05987 0.05367 -0.0453 0.0100 1.0000
13.250 1.3155 0.06364 0.05768 -0.0447 0.0099 1.0000
13.500 1.3103 0.06781 0.06212 -0.0444 0.0099 1.0000
13.750 1.3022 0.07241 0.06698 -0.0445 0.0099 1.0000
14.000 1.2915 0.07744 0.07230 -0.0451 0.0100 1.0000
14.250 1.2779 0.08308 0.07822 -0.0463 0.0101 1.0000
14.500 1.2622 0.08934 0.08477 -0.0482 0.0102 1.0000
14.750 1.2448 0.09621 0.09191 -0.0508 0.0104 1.0000
15.000 1.2252 0.10393 0.09990 -0.0545 0.0105 1.0000
15.250 1.2042 0.11245 0.10867 -0.0592 0.0107 1.0000
15.500 1.1825 0.12182 0.11829 -0.0649 0.0109 1.0000
15.750 1.1608 0.13197 0.12864 -0.0715 0.0111 1.0000
16.000 1.1389 0.14314 0.14000 -0.0791 0.0114 1.0000
16.250 1.1155 0.15596 0.15297 -0.0877 0.0117 1.0000
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Polar data table (+)
Polar graphs
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