MH 115 11.06% (mh115-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 115 11.06% (mh115-il) Reynolds number: 50,000 Max Cl/Cd: 37.51 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh115-il-50000-n5.txt Download as CSV file: xf-mh115-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3097 0.12316 0.11698 -0.0326 1.0000 0.0939
-8.250 -0.3246 0.12252 0.11647 -0.0314 1.0000 0.0942
-8.000 -0.3383 0.12161 0.11568 -0.0299 1.0000 0.0944
-7.750 -0.3392 0.11934 0.11347 -0.0327 0.9955 0.0946
-7.250 -0.3116 0.11082 0.10499 -0.0391 0.9835 0.0951
-7.000 -0.2887 0.10231 0.09632 -0.0409 0.9792 0.0545
-6.750 -0.2759 0.09838 0.09241 -0.0438 0.9728 0.0510
-6.500 -0.2716 0.09300 0.08704 -0.0514 0.9620 0.0457
-6.250 -0.2589 0.08920 0.08325 -0.0545 0.9543 0.0451
-6.000 -0.2415 0.08458 0.07862 -0.0603 0.9469 0.0447
-5.750 -0.2294 0.08027 0.07431 -0.0649 0.9376 0.0445
-5.500 -0.2064 0.07439 0.06836 -0.0736 0.9309 0.0447
-5.250 -0.1895 0.06924 0.06314 -0.0796 0.9218 0.0446
-5.000 -0.1574 0.06249 0.05615 -0.0894 0.9164 0.0446
-4.750 -0.1334 0.05672 0.05011 -0.0960 0.9081 0.0444
-4.500 -0.0902 0.04963 0.04242 -0.1061 0.9037 0.0445
-4.250 -0.0481 0.04371 0.03562 -0.1136 0.8987 0.0459
-4.000 -0.0174 0.04149 0.03320 -0.1162 0.8925 0.0497
-3.750 0.0279 0.03787 0.02876 -0.1211 0.8889 0.0546
-3.500 0.0608 0.03603 0.02659 -0.1230 0.8832 0.0610
-3.250 0.0951 0.03422 0.02430 -0.1247 0.8774 0.0698
-3.000 0.1339 0.03276 0.02254 -0.1268 0.8733 0.0824
-2.750 0.1607 0.03188 0.02147 -0.1269 0.8662 0.0961
-2.500 0.1939 0.03101 0.02053 -0.1280 0.8606 0.1160
-2.250 0.2339 0.03010 0.01953 -0.1303 0.8568 0.1494
-2.000 0.2580 0.02974 0.01918 -0.1300 0.8482 0.1875
-1.750 0.2958 0.02908 0.01867 -0.1321 0.8435 0.2542
-1.500 0.3246 0.02875 0.01855 -0.1327 0.8365 0.3322
-1.250 0.3557 0.02837 0.01847 -0.1334 0.8302 0.4313
-1.000 0.3907 0.02782 0.01824 -0.1340 0.8263 0.5537
-0.750 0.4042 0.02784 0.01853 -0.1311 0.8164 0.6526
-0.500 0.4251 0.02721 0.01817 -0.1281 0.8116 0.8003
-0.250 0.4428 0.02725 0.01812 -0.1263 0.8010 1.0000
0.000 0.4836 0.02726 0.01773 -0.1286 0.7965 1.0000
0.250 0.5062 0.02775 0.01798 -0.1282 0.7867 1.0000
0.500 0.5449 0.02776 0.01770 -0.1300 0.7817 1.0000
0.750 0.5671 0.02826 0.01801 -0.1294 0.7719 1.0000
1.000 0.6048 0.02826 0.01780 -0.1309 0.7667 1.0000
1.250 0.6265 0.02877 0.01817 -0.1302 0.7568 1.0000
1.500 0.6641 0.02873 0.01797 -0.1316 0.7513 1.0000
1.750 0.6849 0.02926 0.01841 -0.1307 0.7412 1.0000
2.000 0.7230 0.02918 0.01820 -0.1321 0.7357 1.0000
2.250 0.7426 0.02974 0.01870 -0.1310 0.7251 1.0000
2.500 0.7817 0.02956 0.01843 -0.1324 0.7198 1.0000
2.750 0.8000 0.03018 0.01902 -0.1311 0.7086 1.0000
3.000 0.8406 0.02986 0.01864 -0.1326 0.7036 1.0000
3.250 0.8577 0.03053 0.01930 -0.1311 0.6918 1.0000
3.500 0.8827 0.03086 0.01962 -0.1306 0.6824 1.0000
3.750 0.9161 0.03077 0.01954 -0.1310 0.6748 1.0000
4.000 0.9359 0.03131 0.02010 -0.1299 0.6636 1.0000
4.250 0.9764 0.03085 0.01964 -0.1311 0.6575 1.0000
4.500 0.9933 0.03150 0.02032 -0.1295 0.6452 1.0000
4.750 1.0148 0.03193 0.02083 -0.1285 0.6340 1.0000
5.000 1.0544 0.03145 0.02038 -0.1295 0.6269 1.0000
5.250 1.0714 0.03206 0.02106 -0.1279 0.6142 1.0000
5.500 1.0917 0.03251 0.02161 -0.1266 0.6022 1.0000
5.750 1.1189 0.03260 0.02177 -0.1261 0.5915 1.0000
6.000 1.1514 0.03241 0.02164 -0.1262 0.5814 1.0000
6.250 1.1690 0.03295 0.02230 -0.1246 0.5682 1.0000
6.500 1.1881 0.03341 0.02285 -0.1231 0.5552 1.0000
6.750 1.2094 0.03374 0.02327 -0.1219 0.5424 1.0000
7.000 1.2328 0.03396 0.02359 -0.1209 0.5297 1.0000
7.250 1.2573 0.03413 0.02386 -0.1200 0.5167 1.0000
7.500 1.2817 0.03430 0.02412 -0.1190 0.5034 1.0000
7.750 1.3015 0.03470 0.02461 -0.1176 0.4892 1.0000
8.000 1.3177 0.03528 0.02531 -0.1157 0.4745 1.0000
8.250 1.3338 0.03589 0.02601 -0.1139 0.4597 1.0000
8.500 1.3494 0.03653 0.02675 -0.1121 0.4446 1.0000
8.750 1.3642 0.03724 0.02754 -0.1102 0.4294 1.0000
9.000 1.3782 0.03800 0.02841 -0.1082 0.4141 1.0000
9.250 1.3910 0.03886 0.02935 -0.1062 0.3987 1.0000
9.500 1.4026 0.03982 0.03039 -0.1042 0.3833 1.0000
9.750 1.4128 0.04091 0.03155 -0.1021 0.3680 1.0000
10.000 1.4216 0.04212 0.03285 -0.1000 0.3528 1.0000
10.250 1.4289 0.04348 0.03432 -0.0978 0.3380 1.0000
10.500 1.4350 0.04499 0.03593 -0.0958 0.3234 1.0000
10.750 1.4400 0.04664 0.03769 -0.0938 0.3091 1.0000
11.000 1.4440 0.04844 0.03960 -0.0918 0.2952 1.0000
11.250 1.4476 0.05037 0.04164 -0.0900 0.2818 1.0000
11.500 1.4506 0.05240 0.04378 -0.0883 0.2686 1.0000
11.750 1.4537 0.05451 0.04601 -0.0868 0.2561 1.0000
12.000 1.4574 0.05662 0.04820 -0.0854 0.2440 1.0000
12.250 1.4613 0.05872 0.05034 -0.0840 0.2322 1.0000
12.500 1.4589 0.06163 0.05346 -0.0828 0.2209 1.0000
12.750 1.4580 0.06452 0.05650 -0.0818 0.2104 1.0000
13.000 1.4589 0.06720 0.05926 -0.0809 0.2001 1.0000
13.250 1.4599 0.06988 0.06203 -0.0801 0.1903 1.0000
13.500 1.4543 0.07367 0.06607 -0.0797 0.1813 1.0000
13.750 1.4543 0.07665 0.06913 -0.0792 0.1724 1.0000
14.000 1.4498 0.08035 0.07299 -0.0790 0.1640 1.0000
14.250 1.4447 0.08434 0.07715 -0.0791 0.1563 1.0000
14.500 1.4449 0.08739 0.08025 -0.0790 0.1482 1.0000
14.750 1.4325 0.09280 0.08593 -0.0801 0.1417 1.0000
15.000 1.4362 0.09531 0.08838 -0.0800 0.1338 1.0000
15.250 1.4179 0.10210 0.09555 -0.0821 0.1285 1.0000
15.500 1.4209 0.10477 0.09818 -0.0823 0.1209 1.0000
15.750 1.4012 0.11225 0.10598 -0.0853 0.1165 1.0000
16.000 1.3922 0.11761 0.11150 -0.0874 0.1107 1.0000
16.250 1.3849 0.12279 0.11678 -0.0895 0.1053 1.0000
16.500 1.3615 0.13197 0.12622 -0.0943 0.1022 1.0000
16.750 1.3720 0.13306 0.12722 -0.0942 0.0944 1.0000
17.000 1.3425 0.14435 0.13881 -0.1008 0.0929 1.0000
17.250 1.3011 0.15989 0.15449 -0.1105 0.0925 1.0000
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Polar data table (+)
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