MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 200,000 Max Cl/Cd: 90 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh115-il-200000-n5.txt Download as CSV file: xf-mh115-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 115 11.06%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1413 0.08859 0.08503 -0.0769 0.9610 0.0130
-8.250 -0.1298 0.08545 0.08190 -0.0792 0.9546 0.0128
-8.000 -0.1165 0.08188 0.07833 -0.0825 0.9490 0.0124
-7.750 -0.1046 0.07780 0.07426 -0.0864 0.9431 0.0121
-7.500 -0.0940 0.07371 0.07018 -0.0902 0.9355 0.0117
-7.250 -0.0838 0.06892 0.06540 -0.0951 0.9278 0.0113
-7.000 -0.0777 0.05795 0.05442 -0.1082 0.9175 0.0102
-6.750 -0.0639 0.05017 0.04659 -0.1194 0.9057 0.0101
-6.500 -0.0444 0.03414 0.03001 -0.1395 0.8936 0.0097
-6.250 -0.0128 0.02500 0.01971 -0.1493 0.8875 0.0097
-6.000 0.0136 0.02171 0.01576 -0.1510 0.8795 0.0099
-5.750 0.0462 0.01955 0.01315 -0.1530 0.8743 0.0104
-5.500 0.0765 0.01844 0.01184 -0.1541 0.8681 0.0111
-5.250 0.1062 0.01737 0.01053 -0.1548 0.8613 0.0119
-4.750 0.1664 0.01594 0.00876 -0.1561 0.8482 0.0161
-4.500 0.1983 0.01518 0.00788 -0.1571 0.8425 0.0185
-4.250 0.2267 0.01453 0.00712 -0.1573 0.8349 0.0220
-4.000 0.2573 0.01404 0.00656 -0.1580 0.8284 0.0286
-3.750 0.2865 0.01362 0.00605 -0.1583 0.8213 0.0375
-3.500 0.3160 0.01321 0.00561 -0.1587 0.8141 0.0485
-3.250 0.3454 0.01286 0.00524 -0.1590 0.8073 0.0621
-3.000 0.3743 0.01257 0.00491 -0.1593 0.7997 0.0796
-2.750 0.4038 0.01228 0.00463 -0.1596 0.7930 0.1041
-2.500 0.4320 0.01206 0.00444 -0.1598 0.7852 0.1345
-2.250 0.4614 0.01184 0.00427 -0.1601 0.7785 0.1739
-2.000 0.4891 0.01166 0.00416 -0.1602 0.7705 0.2188
-1.750 0.5183 0.01149 0.00405 -0.1605 0.7636 0.2682
-1.500 0.5458 0.01134 0.00401 -0.1605 0.7553 0.3191
-1.250 0.5745 0.01121 0.00394 -0.1607 0.7483 0.3743
-1.000 0.6017 0.01110 0.00395 -0.1606 0.7400 0.4319
-0.750 0.6297 0.01100 0.00394 -0.1606 0.7328 0.4932
-0.500 0.6562 0.01092 0.00398 -0.1602 0.7244 0.5539
-0.250 0.6829 0.01084 0.00400 -0.1598 0.7170 0.6152
0.000 0.7080 0.01078 0.00406 -0.1591 0.7084 0.6754
0.250 0.7324 0.01072 0.00409 -0.1581 0.7008 0.7368
0.500 0.7542 0.01065 0.00413 -0.1564 0.6924 0.8019
0.750 0.7732 0.01053 0.00409 -0.1541 0.6844 0.8859
1.000 0.8015 0.01050 0.00402 -0.1540 0.6758 1.0000
1.250 0.8290 0.01062 0.00406 -0.1540 0.6672 1.0000
1.500 0.8567 0.01076 0.00409 -0.1539 0.6586 1.0000
1.750 0.8835 0.01090 0.00417 -0.1537 0.6492 1.0000
2.000 0.9107 0.01105 0.00423 -0.1536 0.6404 1.0000
2.250 0.9371 0.01120 0.00433 -0.1533 0.6305 1.0000
2.500 0.9636 0.01135 0.00443 -0.1531 0.6208 1.0000
2.750 0.9900 0.01153 0.00453 -0.1528 0.6111 1.0000
3.000 1.0157 0.01169 0.00467 -0.1524 0.6003 1.0000
3.250 1.0414 0.01187 0.00481 -0.1520 0.5896 1.0000
3.500 1.0669 0.01207 0.00495 -0.1515 0.5788 1.0000
3.750 1.0919 0.01227 0.00513 -0.1510 0.5671 1.0000
4.000 1.1167 0.01248 0.00531 -0.1505 0.5549 1.0000
4.250 1.1412 0.01271 0.00551 -0.1499 0.5426 1.0000
4.500 1.1653 0.01295 0.00573 -0.1492 0.5299 1.0000
4.750 1.1889 0.01321 0.00595 -0.1484 0.5165 1.0000
5.000 1.2121 0.01349 0.00619 -0.1476 0.5027 1.0000
5.250 1.2347 0.01379 0.00646 -0.1467 0.4881 1.0000
5.500 1.2568 0.01411 0.00676 -0.1457 0.4732 1.0000
5.750 1.2784 0.01445 0.00707 -0.1446 0.4578 1.0000
6.000 1.2993 0.01481 0.00740 -0.1434 0.4418 1.0000
6.250 1.3196 0.01520 0.00778 -0.1421 0.4255 1.0000
6.500 1.3390 0.01562 0.00817 -0.1407 0.4087 1.0000
6.750 1.3577 0.01608 0.00859 -0.1392 0.3918 1.0000
7.000 1.3754 0.01656 0.00904 -0.1376 0.3749 1.0000
7.250 1.3920 0.01707 0.00952 -0.1357 0.3584 1.0000
7.500 1.4069 0.01760 0.01003 -0.1336 0.3421 1.0000
7.750 1.4215 0.01816 0.01057 -0.1314 0.3267 1.0000
8.000 1.4357 0.01875 0.01115 -0.1293 0.3117 1.0000
8.250 1.4495 0.01938 0.01179 -0.1271 0.2971 1.0000
8.500 1.4627 0.02006 0.01246 -0.1249 0.2829 1.0000
8.750 1.4753 0.02078 0.01318 -0.1227 0.2686 1.0000
9.000 1.4874 0.02155 0.01396 -0.1205 0.2550 1.0000
9.250 1.4988 0.02238 0.01481 -0.1183 0.2416 1.0000
9.500 1.5095 0.02328 0.01572 -0.1161 0.2287 1.0000
9.750 1.5195 0.02425 0.01670 -0.1139 0.2161 1.0000
10.250 1.5383 0.02639 0.01889 -0.1096 0.1913 1.0000
10.500 1.5473 0.02755 0.02010 -0.1076 0.1796 1.0000
10.750 1.5552 0.02883 0.02141 -0.1055 0.1682 1.0000
11.000 1.5620 0.03023 0.02284 -0.1035 0.1572 1.0000
11.250 1.5676 0.03178 0.02440 -0.1016 0.1464 1.0000
11.500 1.5733 0.03339 0.02604 -0.0997 0.1353 1.0000
11.750 1.5787 0.03508 0.02777 -0.0980 0.1247 1.0000
12.000 1.5829 0.03694 0.02967 -0.0964 0.1147 1.0000
12.250 1.5857 0.03898 0.03174 -0.0948 0.1055 1.0000
12.500 1.5886 0.04110 0.03389 -0.0934 0.0967 1.0000
12.750 1.5923 0.04320 0.03607 -0.0921 0.0889 1.0000
13.000 1.5933 0.04564 0.03855 -0.0909 0.0822 1.0000
13.250 1.5964 0.04796 0.04095 -0.0899 0.0754 1.0000
13.500 1.5973 0.05059 0.04366 -0.0890 0.0696 1.0000
13.750 1.5986 0.05326 0.04642 -0.0883 0.0636 1.0000
14.000 1.5986 0.05617 0.04943 -0.0877 0.0581 1.0000
14.250 1.5977 0.05929 0.05263 -0.0873 0.0525 1.0000
14.500 1.5969 0.06250 0.05593 -0.0870 0.0472 1.0000
14.750 1.5928 0.06622 0.05971 -0.0869 0.0421 1.0000
15.000 1.5904 0.06984 0.06343 -0.0870 0.0369 1.0000
15.250 1.5855 0.07392 0.06761 -0.0873 0.0326 1.0000
15.500 1.5791 0.07834 0.07210 -0.0878 0.0286 1.0000
15.750 1.5732 0.08281 0.07669 -0.0885 0.0253 1.0000
16.250 1.5579 0.09268 0.08679 -0.0908 0.0202 1.0000
16.500 1.5486 0.09808 0.09229 -0.0924 0.0184 1.0000
16.750 1.5403 0.10343 0.09780 -0.0941 0.0167 1.0000
17.000 1.5315 0.10897 0.10348 -0.0960 0.0154 1.0000
17.250 1.5208 0.11500 0.10962 -0.0984 0.0144 1.0000
17.500 1.5121 0.12074 0.11553 -0.1008 0.0134 1.0000
17.750 1.5033 0.12659 0.12153 -0.1035 0.0124 1.0000
18.000 1.4932 0.13278 0.12785 -0.1065 0.0116 1.0000
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Polar data table (+)
Polar graphs
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