MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 500,000 Max Cl/Cd: 120.36 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh115-il-500000-n5.txt Download as CSV file: xf-mh115-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0447 0.08205 0.07972 -0.0867 0.9490 0.0075
-9.500 -0.0316 0.07810 0.07577 -0.0899 0.9462 0.0073
-9.250 -0.1266 0.09077 0.08836 -0.0810 0.9612 0.0075
-9.000 -0.1153 0.08773 0.08533 -0.0833 0.9554 0.0073
-8.750 -0.1025 0.08403 0.08163 -0.0867 0.9498 0.0071
-8.500 -0.0869 0.07964 0.07723 -0.0916 0.9455 0.0068
-8.250 -0.0730 0.07463 0.07221 -0.0970 0.9381 0.0064
-8.000 -0.0647 0.06361 0.06116 -0.1091 0.9293 0.0055
-7.750 -0.0550 0.05643 0.05394 -0.1188 0.9145 0.0054
-7.500 -0.0947 0.02167 0.01778 -0.1575 0.8769 0.0048
-7.250 -0.0715 0.01872 0.01430 -0.1592 0.8680 0.0048
-7.000 -0.0461 0.01695 0.01216 -0.1600 0.8594 0.0048
-6.750 -0.0199 0.01559 0.01049 -0.1605 0.8512 0.0049
-6.500 0.0071 0.01455 0.00920 -0.1609 0.8431 0.0050
-6.250 0.0341 0.01368 0.00812 -0.1611 0.8350 0.0051
-6.000 0.0617 0.01298 0.00723 -0.1613 0.8271 0.0052
-5.750 0.0892 0.01238 0.00649 -0.1614 0.8190 0.0053
-5.500 0.1170 0.01183 0.00576 -0.1616 0.8112 0.0056
-5.250 0.1447 0.01132 0.00515 -0.1617 0.8032 0.0060
-4.750 0.2005 0.01064 0.00425 -0.1619 0.7876 0.0072
-4.250 0.2565 0.01006 0.00350 -0.1620 0.7723 0.0106
-3.750 0.3124 0.00964 0.00303 -0.1621 0.7572 0.0221
-3.250 0.3682 0.00931 0.00268 -0.1622 0.7422 0.0411
-3.000 0.3961 0.00917 0.00252 -0.1622 0.7347 0.0541
-2.750 0.4241 0.00903 0.00239 -0.1622 0.7270 0.0696
-2.500 0.4519 0.00892 0.00228 -0.1622 0.7194 0.0887
-2.250 0.4799 0.00881 0.00218 -0.1623 0.7116 0.1099
-2.000 0.5076 0.00872 0.00211 -0.1623 0.7040 0.1360
-1.750 0.5356 0.00861 0.00205 -0.1623 0.6962 0.1666
-1.250 0.5911 0.00843 0.00199 -0.1624 0.6805 0.2447
-0.750 0.6465 0.00831 0.00198 -0.1624 0.6646 0.3246
-0.500 0.6739 0.00828 0.00200 -0.1624 0.6567 0.3681
-0.250 0.7017 0.00822 0.00203 -0.1624 0.6482 0.4153
0.000 0.7290 0.00820 0.00207 -0.1624 0.6401 0.4639
0.250 0.7564 0.00816 0.00213 -0.1623 0.6313 0.5131
0.500 0.7835 0.00815 0.00219 -0.1622 0.6228 0.5626
0.750 0.8104 0.00815 0.00227 -0.1620 0.6136 0.6124
1.000 0.8372 0.00814 0.00235 -0.1618 0.6046 0.6617
1.250 0.8631 0.00816 0.00245 -0.1613 0.5953 0.7125
1.500 0.8887 0.00815 0.00255 -0.1608 0.5852 0.7650
1.750 0.9125 0.00815 0.00265 -0.1598 0.5757 0.8234
2.250 0.9567 0.00811 0.00273 -0.1570 0.5549 1.0000
2.500 0.9830 0.00827 0.00282 -0.1568 0.5438 1.0000
2.750 1.0089 0.00845 0.00294 -0.1564 0.5320 1.0000
3.250 1.0603 0.00882 0.00318 -0.1557 0.5069 1.0000
3.500 1.0856 0.00902 0.00332 -0.1553 0.4936 1.0000
3.750 1.1105 0.00923 0.00349 -0.1548 0.4798 1.0000
4.000 1.1352 0.00947 0.00366 -0.1542 0.4656 1.0000
4.250 1.1595 0.00972 0.00385 -0.1536 0.4508 1.0000
4.500 1.1834 0.00998 0.00406 -0.1530 0.4356 1.0000
4.750 1.2070 0.01026 0.00427 -0.1523 0.4204 1.0000
5.000 1.2301 0.01057 0.00451 -0.1515 0.4041 1.0000
5.250 1.2529 0.01088 0.00477 -0.1506 0.3882 1.0000
5.500 1.2752 0.01122 0.00504 -0.1497 0.3717 1.0000
5.750 1.2970 0.01158 0.00534 -0.1487 0.3549 1.0000
6.000 1.3182 0.01196 0.00565 -0.1476 0.3383 1.0000
6.250 1.3389 0.01236 0.00599 -0.1465 0.3218 1.0000
6.500 1.3595 0.01276 0.00633 -0.1453 0.3057 1.0000
6.750 1.3795 0.01316 0.00668 -0.1440 0.2912 1.0000
7.000 1.3981 0.01357 0.00705 -0.1425 0.2769 1.0000
7.250 1.4161 0.01399 0.00744 -0.1408 0.2627 1.0000
7.500 1.4339 0.01442 0.00784 -0.1392 0.2496 1.0000
7.750 1.4511 0.01489 0.00828 -0.1375 0.2359 1.0000
8.000 1.4677 0.01539 0.00875 -0.1357 0.2230 1.0000
8.250 1.4842 0.01589 0.00923 -0.1339 0.2115 1.0000
8.500 1.4998 0.01645 0.00977 -0.1320 0.1991 1.0000
8.750 1.5146 0.01705 0.01034 -0.1301 0.1868 1.0000
9.250 1.5431 0.01835 0.01161 -0.1261 0.1636 1.0000
9.500 1.5563 0.01906 0.01232 -0.1241 0.1521 1.0000
9.750 1.5690 0.01984 0.01308 -0.1221 0.1413 1.0000
10.000 1.5798 0.02074 0.01394 -0.1199 0.1286 1.0000
10.250 1.5891 0.02176 0.01493 -0.1175 0.1148 1.0000
10.500 1.5978 0.02286 0.01598 -0.1153 0.1021 1.0000
10.750 1.6067 0.02398 0.01708 -0.1131 0.0922 1.0000
11.000 1.6155 0.02515 0.01825 -0.1111 0.0838 1.0000
11.250 1.6256 0.02625 0.01938 -0.1093 0.0772 1.0000
11.500 1.6336 0.02756 0.02070 -0.1073 0.0706 1.0000
11.750 1.6423 0.02885 0.02203 -0.1056 0.0643 1.0000
12.000 1.6491 0.03033 0.02353 -0.1038 0.0580 1.0000
12.250 1.6541 0.03201 0.02521 -0.1019 0.0510 1.0000
12.500 1.6593 0.03375 0.02696 -0.1003 0.0440 1.0000
12.750 1.6620 0.03576 0.02898 -0.0986 0.0364 1.0000
13.000 1.6622 0.03809 0.03129 -0.0969 0.0286 1.0000
13.250 1.6617 0.04058 0.03379 -0.0954 0.0221 1.0000
13.500 1.6619 0.04311 0.03635 -0.0941 0.0175 1.0000
13.750 1.6622 0.04572 0.03901 -0.0930 0.0143 1.0000
14.000 1.6640 0.04827 0.04164 -0.0921 0.0122 1.0000
14.250 1.6649 0.05100 0.04445 -0.0914 0.0106 1.0000
14.500 1.6657 0.05384 0.04738 -0.0908 0.0091 1.0000
14.750 1.6658 0.05684 0.05047 -0.0903 0.0081 1.0000
15.000 1.6658 0.05997 0.05370 -0.0901 0.0071 1.0000
15.250 1.6641 0.06341 0.05723 -0.0899 0.0064 1.0000
15.500 1.6634 0.06680 0.06074 -0.0900 0.0057 1.0000
15.750 1.6608 0.07056 0.06461 -0.0902 0.0050 1.0000
16.000 1.6572 0.07456 0.06873 -0.0906 0.0046 1.0000
16.250 1.6544 0.07858 0.07286 -0.0912 0.0041 1.0000
16.500 1.6498 0.08293 0.07734 -0.0920 0.0036 1.0000
16.750 1.6435 0.08766 0.08219 -0.0931 0.0032 1.0000
17.000 1.6386 0.09229 0.08695 -0.0942 0.0029 1.0000
17.250 1.6323 0.09724 0.09203 -0.0956 0.0026 1.0000
17.500 1.6247 0.10250 0.09741 -0.0973 0.0024 1.0000
17.750 1.6162 0.10802 0.10307 -0.0993 0.0022 1.0000
18.000 1.6075 0.11366 0.10884 -0.1014 0.0020 1.0000
18.250 1.5997 0.11923 0.11454 -0.1037 0.0019 1.0000
18.500 1.5914 0.12494 0.12039 -0.1062 0.0018 1.0000
18.750 1.5821 0.13089 0.12648 -0.1089 0.0016 1.0000
19.000 1.5731 0.13686 0.13258 -0.1119 0.0015 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 115 11.06% (mh115-il)