MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 50,000 Max Cl/Cd: 39.39 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh116-il-50000-n5.txt Download as CSV file: xf-mh116-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3442 0.09962 0.09305 -0.0434 1.0000 0.0403
-8.250 -0.3477 0.09707 0.09060 -0.0422 1.0000 0.0398
-8.000 -0.3542 0.09478 0.08842 -0.0408 1.0000 0.0393
-7.750 -0.3640 0.09264 0.08640 -0.0390 1.0000 0.0389
-7.500 -0.3764 0.09077 0.08465 -0.0369 1.0000 0.0385
-7.250 -0.3895 0.08891 0.08292 -0.0349 1.0000 0.0381
-7.000 -0.4005 0.08646 0.08057 -0.0341 1.0000 0.0377
-6.750 -0.4099 0.08371 0.07792 -0.0339 1.0000 0.0373
-6.500 -0.4177 0.08048 0.07476 -0.0344 1.0000 0.0370
-6.250 -0.4224 0.07699 0.07132 -0.0356 1.0000 0.0364
-6.000 -0.4105 0.07118 0.06546 -0.0419 0.9957 0.0359
-5.750 -0.3869 0.06363 0.05773 -0.0512 0.9883 0.0353
-5.500 -0.3593 0.05603 0.04978 -0.0602 0.9818 0.0349
-5.250 -0.3313 0.04952 0.04277 -0.0670 0.9751 0.0358
-5.000 -0.2962 0.04348 0.03598 -0.0734 0.9701 0.0380
-4.750 -0.2623 0.03853 0.02990 -0.0773 0.9646 0.0410
-4.500 -0.2306 0.03560 0.02670 -0.0798 0.9597 0.0440
-4.250 -0.1945 0.03306 0.02358 -0.0821 0.9555 0.0505
-4.000 -0.1646 0.03122 0.02143 -0.0831 0.9494 0.0597
-3.750 -0.1297 0.02963 0.01951 -0.0848 0.9447 0.0757
-3.500 -0.0981 0.02827 0.01796 -0.0856 0.9392 0.0959
-3.250 -0.0666 0.02729 0.01684 -0.0866 0.9333 0.1243
-3.000 -0.0298 0.02651 0.01602 -0.0887 0.9290 0.1666
-2.750 -0.0026 0.02595 0.01545 -0.0890 0.9217 0.2087
-2.500 0.0327 0.02541 0.01496 -0.0908 0.9167 0.2645
-2.250 0.0611 0.02501 0.01468 -0.0913 0.9098 0.3249
-2.000 0.0933 0.02459 0.01440 -0.0924 0.9042 0.4039
-1.750 0.1215 0.02419 0.01431 -0.0925 0.8980 0.4982
-1.500 0.1458 0.02379 0.01430 -0.0914 0.8914 0.6157
-1.250 0.1665 0.02333 0.01426 -0.0888 0.8854 0.7763
-0.750 0.2383 0.02334 0.01376 -0.0920 0.8724 1.0000
-0.250 0.3009 0.02385 0.01370 -0.0940 0.8587 1.0000
0.250 0.3607 0.02440 0.01383 -0.0954 0.8444 1.0000
0.500 0.3867 0.02473 0.01401 -0.0954 0.8359 1.0000
0.750 0.4179 0.02499 0.01412 -0.0962 0.8292 1.0000
1.000 0.4465 0.02529 0.01430 -0.0966 0.8214 1.0000
1.250 0.4742 0.02561 0.01453 -0.0968 0.8135 1.0000
1.500 0.5063 0.02582 0.01468 -0.0976 0.8066 1.0000
1.750 0.5308 0.02620 0.01501 -0.0973 0.7975 1.0000
2.000 0.5661 0.02629 0.01506 -0.0984 0.7915 1.0000
2.250 0.5884 0.02672 0.01547 -0.0977 0.7812 1.0000
2.500 0.6188 0.02691 0.01565 -0.0981 0.7736 1.0000
2.750 0.6477 0.02711 0.01589 -0.0982 0.7650 1.0000
3.000 0.6716 0.02747 0.01627 -0.0976 0.7547 1.0000
3.250 0.7066 0.02743 0.01627 -0.0984 0.7478 1.0000
3.500 0.7312 0.02771 0.01661 -0.0978 0.7371 1.0000
3.750 0.7551 0.02802 0.01704 -0.0971 0.7261 1.0000
4.000 0.7829 0.02816 0.01727 -0.0968 0.7159 1.0000
4.250 0.8182 0.02795 0.01716 -0.0973 0.7076 1.0000
4.750 0.8670 0.02833 0.01782 -0.0955 0.6827 1.0000
5.000 0.8930 0.02840 0.01803 -0.0947 0.6698 1.0000
5.250 0.9197 0.02840 0.01818 -0.0940 0.6564 1.0000
5.500 0.9468 0.02834 0.01827 -0.0931 0.6422 1.0000
5.750 0.9743 0.02820 0.01835 -0.0923 0.6270 1.0000
6.000 1.0030 0.02796 0.01828 -0.0914 0.6107 1.0000
6.250 1.0234 0.02810 0.01859 -0.0897 0.5911 1.0000
6.500 1.0482 0.02798 0.01863 -0.0883 0.5706 1.0000
6.750 1.0686 0.02808 0.01888 -0.0864 0.5472 1.0000
7.000 1.0899 0.02813 0.01913 -0.0846 0.5217 1.0000
7.250 1.1092 0.02831 0.01941 -0.0826 0.4932 1.0000
7.500 1.1269 0.02861 0.01978 -0.0804 0.4618 1.0000
7.750 1.1435 0.02903 0.02018 -0.0781 0.4280 1.0000
8.000 1.1553 0.02974 0.02088 -0.0754 0.3930 1.0000
8.250 1.1651 0.03063 0.02166 -0.0725 0.3583 1.0000
8.500 1.1720 0.03179 0.02276 -0.0696 0.3244 1.0000
8.750 1.1776 0.03314 0.02409 -0.0667 0.2927 1.0000
9.000 1.1820 0.03468 0.02555 -0.0640 0.2632 1.0000
9.250 1.1857 0.03637 0.02719 -0.0615 0.2360 1.0000
9.500 1.1888 0.03822 0.02900 -0.0592 0.2104 1.0000
9.750 1.1919 0.04019 0.03095 -0.0571 0.1876 1.0000
10.000 1.1936 0.04233 0.03303 -0.0551 0.1671 1.0000
10.250 1.1961 0.04459 0.03532 -0.0533 0.1472 1.0000
10.500 1.1971 0.04702 0.03775 -0.0517 0.1295 1.0000
10.750 1.1976 0.04961 0.04032 -0.0503 0.1141 1.0000
11.000 1.1973 0.05237 0.04308 -0.0491 0.1001 1.0000
11.250 1.1976 0.05526 0.04602 -0.0480 0.0875 1.0000
11.500 1.1980 0.05825 0.04913 -0.0471 0.0763 1.0000
11.750 1.2011 0.06131 0.05235 -0.0460 0.0667 1.0000
12.000 1.2017 0.06455 0.05577 -0.0453 0.0594 1.0000
12.250 1.2010 0.06791 0.05927 -0.0449 0.0532 1.0000
12.500 1.2058 0.07130 0.06287 -0.0440 0.0482 1.0000
12.750 1.2054 0.07510 0.06695 -0.0438 0.0439 1.0000
13.000 1.2018 0.07886 0.07073 -0.0440 0.0408 1.0000
13.250 1.1978 0.08339 0.07554 -0.0444 0.0382 1.0000
13.500 1.1912 0.08851 0.08104 -0.0451 0.0364 1.0000
13.750 1.1821 0.09405 0.08690 -0.0465 0.0353 1.0000
14.000 1.1704 0.10010 0.09322 -0.0486 0.0346 1.0000
14.250 1.1563 0.10678 0.10017 -0.0515 0.0342 1.0000
14.500 1.1403 0.11429 0.10792 -0.0553 0.0342 1.0000
14.750 1.1219 0.12291 0.11676 -0.0602 0.0346 1.0000
15.000 1.1014 0.13285 0.12691 -0.0664 0.0354 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 116 9.84% (mh116-il)