MH 113 14.62% (mh113-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 113 14.62% (mh113-il) Reynolds number: 100,000 Max Cl/Cd: 55.98 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh113-il-100000-n5.txt Download as CSV file: xf-mh113-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 113 14.62%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0178 0.10873 0.10344 -0.1041 0.9220 0.0609
-9.500 0.0245 0.10535 0.10006 -0.1091 0.9178 0.0620
-9.250 0.0382 0.10146 0.09616 -0.1142 0.9150 0.0623
-8.750 0.0590 0.09207 0.08671 -0.1166 0.9038 0.0401
-8.500 0.0736 0.08831 0.08293 -0.1202 0.9002 0.0397
-8.250 0.0816 0.08514 0.07976 -0.1222 0.8941 0.0393
-8.000 0.0869 0.08199 0.07662 -0.1239 0.8870 0.0392
-7.750 0.0989 0.07809 0.07270 -0.1276 0.8828 0.0389
-7.500 0.0958 0.07544 0.07009 -0.1276 0.8736 0.0382
-7.250 0.0788 0.06820 0.06283 -0.1326 0.8653 0.0358
-7.000 0.0693 0.06635 0.06103 -0.1307 0.8548 0.0356
-6.750 0.0770 0.06216 0.05682 -0.1349 0.8493 0.0353
-6.500 0.0680 0.05848 0.05315 -0.1364 0.8391 0.0349
-6.000 0.0650 0.04205 0.03598 -0.1534 0.8217 0.0335
-5.750 0.0898 0.03672 0.02999 -0.1592 0.8170 0.0336
-5.500 0.1251 0.03287 0.02547 -0.1639 0.8144 0.0342
-5.250 0.1437 0.03095 0.02313 -0.1638 0.8075 0.0348
-5.000 0.1713 0.02918 0.02093 -0.1648 0.8024 0.0361
-4.750 0.2051 0.02814 0.01980 -0.1665 0.7992 0.0382
-4.500 0.2428 0.02666 0.01798 -0.1686 0.7968 0.0405
-4.250 0.2596 0.02602 0.01720 -0.1670 0.7893 0.0417
-4.000 0.2887 0.02521 0.01634 -0.1675 0.7846 0.0436
-3.750 0.3241 0.02424 0.01520 -0.1689 0.7814 0.0467
-3.500 0.3621 0.02340 0.01430 -0.1708 0.7789 0.0520
-3.250 0.3760 0.02328 0.01418 -0.1686 0.7704 0.0563
-3.000 0.4090 0.02261 0.01346 -0.1697 0.7662 0.0647
-2.750 0.4463 0.02191 0.01272 -0.1715 0.7631 0.0820
-2.500 0.4693 0.02167 0.01258 -0.1709 0.7566 0.1034
-2.250 0.4969 0.02134 0.01233 -0.1711 0.7508 0.1368
-2.000 0.5323 0.02083 0.01194 -0.1726 0.7471 0.1816
-1.750 0.5642 0.02049 0.01168 -0.1734 0.7426 0.2286
-1.500 0.5837 0.02053 0.01183 -0.1721 0.7350 0.2695
-1.250 0.6169 0.02021 0.01159 -0.1730 0.7306 0.3239
-1.000 0.6533 0.01986 0.01130 -0.1744 0.7271 0.3825
-0.750 0.6683 0.02010 0.01166 -0.1722 0.7183 0.4252
-0.500 0.7003 0.01988 0.01150 -0.1727 0.7136 0.4800
-0.250 0.7315 0.01972 0.01137 -0.1730 0.7089 0.5327
0.000 0.7491 0.01991 0.01165 -0.1711 0.7007 0.5761
0.250 0.7801 0.01970 0.01148 -0.1712 0.6959 0.6268
0.500 0.8025 0.01974 0.01157 -0.1700 0.6894 0.6736
0.750 0.8223 0.01975 0.01166 -0.1681 0.6823 0.7219
1.000 0.8499 0.01946 0.01140 -0.1674 0.6777 0.7808
1.250 0.8570 0.01955 0.01163 -0.1631 0.6694 0.8527
1.500 0.8842 0.01933 0.01137 -0.1626 0.6631 1.0000
1.750 0.9148 0.01942 0.01131 -0.1632 0.6570 1.0000
2.000 0.9371 0.01971 0.01150 -0.1624 0.6489 1.0000
2.250 0.9728 0.01964 0.01127 -0.1637 0.6436 1.0000
2.500 0.9901 0.02005 0.01164 -0.1621 0.6347 1.0000
2.750 1.0215 0.02008 0.01155 -0.1626 0.6283 1.0000
3.000 1.0433 0.02039 0.01179 -0.1617 0.6204 1.0000
3.250 1.0698 0.02054 0.01186 -0.1615 0.6129 1.0000
3.500 1.0956 0.02074 0.01198 -0.1612 0.6057 1.0000
3.750 1.1173 0.02102 0.01222 -0.1602 0.5973 1.0000
4.000 1.1458 0.02114 0.01225 -0.1603 0.5903 1.0000
4.250 1.1631 0.02152 0.01262 -0.1586 0.5814 1.0000
4.500 1.1931 0.02162 0.01262 -0.1589 0.5745 1.0000
4.750 1.2073 0.02208 0.01310 -0.1567 0.5652 1.0000
5.000 1.2377 0.02218 0.01309 -0.1571 0.5583 1.0000
5.250 1.2502 0.02272 0.01367 -0.1547 0.5487 1.0000
5.500 1.2792 0.02285 0.01371 -0.1549 0.5415 1.0000
5.750 1.2914 0.02344 0.01434 -0.1525 0.5321 1.0000
6.000 1.3185 0.02362 0.01445 -0.1524 0.5245 1.0000
6.250 1.3305 0.02425 0.01512 -0.1500 0.5150 1.0000
6.500 1.3561 0.02449 0.01529 -0.1497 0.5075 1.0000
6.750 1.3676 0.02517 0.01602 -0.1474 0.4980 1.0000
7.000 1.3913 0.02548 0.01628 -0.1468 0.4903 1.0000
7.250 1.4027 0.02620 0.01706 -0.1446 0.4810 1.0000
7.500 1.4241 0.02660 0.01741 -0.1437 0.4731 1.0000
7.750 1.4356 0.02737 0.01823 -0.1416 0.4640 1.0000
8.000 1.4553 0.02785 0.01869 -0.1405 0.4561 1.0000
8.250 1.4661 0.02869 0.01958 -0.1384 0.4469 1.0000
8.500 1.4841 0.02926 0.02013 -0.1372 0.4391 1.0000
8.750 1.4943 0.03018 0.02111 -0.1351 0.4301 1.0000
9.000 1.5110 0.03083 0.02177 -0.1338 0.4223 1.0000
9.250 1.5202 0.03185 0.02285 -0.1318 0.4134 1.0000
9.500 1.5357 0.03260 0.02359 -0.1304 0.4056 1.0000
9.750 1.5439 0.03374 0.02482 -0.1284 0.3969 1.0000
10.000 1.5583 0.03457 0.02565 -0.1270 0.3892 1.0000
10.250 1.5651 0.03586 0.02702 -0.1250 0.3806 1.0000
10.500 1.5788 0.03676 0.02792 -0.1237 0.3731 1.0000
10.750 1.5840 0.03823 0.02951 -0.1217 0.3645 1.0000
11.000 1.5973 0.03920 0.03046 -0.1204 0.3572 1.0000
11.250 1.6005 0.04088 0.03228 -0.1184 0.3487 1.0000
11.500 1.6132 0.04191 0.03328 -0.1171 0.3414 1.0000
11.750 1.6146 0.04385 0.03537 -0.1152 0.3331 1.0000
12.250 1.6261 0.04716 0.03883 -0.1122 0.3177 1.0000
12.500 1.6359 0.04849 0.04016 -0.1110 0.3106 1.0000
12.750 1.6355 0.05083 0.04265 -0.1095 0.3025 1.0000
13.000 1.6424 0.05249 0.04434 -0.1083 0.2953 1.0000
13.250 1.6427 0.05492 0.04690 -0.1070 0.2876 1.0000
13.500 1.6469 0.05694 0.04897 -0.1059 0.2802 1.0000
13.750 1.6474 0.05946 0.05160 -0.1048 0.2728 1.0000
14.000 1.6490 0.06188 0.05410 -0.1039 0.2654 1.0000
14.250 1.6504 0.06443 0.05673 -0.1031 0.2583 1.0000
14.500 1.6492 0.06733 0.05975 -0.1023 0.2509 1.0000
14.750 1.6516 0.06985 0.06231 -0.1017 0.2442 1.0000
15.000 1.6473 0.07330 0.06591 -0.1012 0.2368 1.0000
15.250 1.6510 0.07571 0.06833 -0.1007 0.2302 1.0000
15.500 1.6438 0.07974 0.07255 -0.1006 0.2230 1.0000
15.750 1.6480 0.08212 0.07493 -0.1003 0.2167 1.0000
16.000 1.6390 0.08661 0.07961 -0.1005 0.2098 1.0000
16.250 1.6390 0.08972 0.08276 -0.1005 0.2034 1.0000
16.500 1.6340 0.09371 0.08689 -0.1009 0.1971 1.0000
16.750 1.6295 0.09765 0.09094 -0.1014 0.1907 1.0000
17.000 1.6293 0.10094 0.09427 -0.1018 0.1849 1.0000
17.250 1.6205 0.10573 0.09923 -0.1028 0.1787 1.0000
17.500 1.6247 0.10827 0.10175 -0.1031 0.1732 1.0000
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