MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 50,000 Max Cl/Cd: 32.97 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh61-il-50000-n5.txt Download as CSV file: xf-mh61-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5610 0.09825 0.09218 0.0007 1.0000 0.0326
-9.250 -0.5634 0.09255 0.08655 -0.0030 1.0000 0.0319
-9.000 -0.5676 0.08611 0.08019 -0.0078 1.0000 0.0311
-8.750 -0.5762 0.07824 0.07235 -0.0147 1.0000 0.0302
-8.500 -0.5938 0.07135 0.06542 -0.0208 1.0000 0.0292
-8.250 -0.6084 0.06578 0.05963 -0.0240 1.0000 0.0285
-8.000 -0.6129 0.06109 0.05466 -0.0256 1.0000 0.0281
-7.750 -0.6113 0.05688 0.05012 -0.0264 1.0000 0.0278
-7.500 -0.6057 0.05285 0.04573 -0.0268 1.0000 0.0277
-7.250 -0.5964 0.04903 0.04151 -0.0268 1.0000 0.0276
-7.000 -0.5850 0.04518 0.03727 -0.0267 1.0000 0.0278
-6.750 -0.5705 0.04167 0.03338 -0.0263 1.0000 0.0281
-6.500 -0.5541 0.03847 0.02972 -0.0258 1.0000 0.0287
-6.250 -0.5362 0.03576 0.02671 -0.0251 1.0000 0.0297
-6.000 -0.5183 0.03367 0.02437 -0.0242 1.0000 0.0317
-5.750 -0.5016 0.03189 0.02231 -0.0228 1.0000 0.0354
-5.500 -0.4865 0.03038 0.02047 -0.0207 1.0000 0.0380
-5.250 -0.4747 0.02867 0.01867 -0.0183 1.0000 0.0407
-5.000 -0.4637 0.02732 0.01722 -0.0157 1.0000 0.0439
-4.750 -0.4325 0.02563 0.01531 -0.0168 0.9885 0.0539
-4.500 -0.3991 0.02377 0.01339 -0.0183 0.9785 0.0777
-4.250 -0.3678 0.02097 0.01179 -0.0206 0.9698 0.2385
-4.000 -0.3422 0.02005 0.01158 -0.0209 0.9588 0.4096
-3.750 -0.3144 0.01966 0.01125 -0.0208 0.9487 0.5005
-3.500 -0.2832 0.01932 0.01091 -0.0210 0.9397 0.5643
-3.250 -0.2521 0.01905 0.01062 -0.0211 0.9307 0.6228
-3.000 -0.2217 0.01883 0.01040 -0.0209 0.9215 0.6806
-2.750 -0.1851 0.01869 0.01023 -0.0215 0.9140 0.7418
-2.500 -0.1438 0.01865 0.01004 -0.0231 0.9061 0.8025
-2.250 -0.0916 0.01869 0.00987 -0.0268 0.8999 0.8572
-2.000 -0.0381 0.01875 0.00967 -0.0312 0.8926 0.9019
-1.750 0.0172 0.01878 0.00937 -0.0362 0.8853 0.9382
-1.500 0.0701 0.01875 0.00910 -0.0412 0.8771 0.9705
-1.250 0.1244 0.01860 0.00873 -0.0470 0.8685 1.0000
-1.000 0.1428 0.01871 0.00865 -0.0459 0.8563 1.0000
-0.750 0.1617 0.01886 0.00865 -0.0448 0.8447 1.0000
-0.500 0.1811 0.01901 0.00867 -0.0435 0.8337 1.0000
-0.250 0.2007 0.01921 0.00875 -0.0423 0.8222 1.0000
0.000 0.2207 0.01942 0.00886 -0.0412 0.8106 1.0000
0.250 0.2410 0.01964 0.00899 -0.0400 0.7993 1.0000
0.500 0.2616 0.01986 0.00913 -0.0388 0.7884 1.0000
0.750 0.2826 0.02006 0.00926 -0.0375 0.7780 1.0000
1.000 0.3037 0.02027 0.00942 -0.0362 0.7672 1.0000
1.250 0.3250 0.02052 0.00964 -0.0351 0.7555 1.0000
1.500 0.3466 0.02076 0.00989 -0.0340 0.7440 1.0000
1.750 0.3683 0.02100 0.01011 -0.0329 0.7327 1.0000
2.000 0.3903 0.02121 0.01031 -0.0316 0.7217 1.0000
2.250 0.4124 0.02136 0.01047 -0.0302 0.7113 1.0000
2.500 0.4345 0.02160 0.01079 -0.0291 0.6991 1.0000
2.750 0.4566 0.02184 0.01107 -0.0280 0.6867 1.0000
3.000 0.4789 0.02207 0.01137 -0.0268 0.6741 1.0000
3.250 0.5013 0.02228 0.01165 -0.0256 0.6615 1.0000
3.500 0.5238 0.02249 0.01194 -0.0245 0.6486 1.0000
3.750 0.5464 0.02268 0.01227 -0.0232 0.6354 1.0000
4.000 0.5692 0.02286 0.01255 -0.0220 0.6219 1.0000
4.250 0.5921 0.02303 0.01284 -0.0208 0.6080 1.0000
4.500 0.6151 0.02318 0.01312 -0.0195 0.5936 1.0000
4.750 0.6382 0.02331 0.01338 -0.0182 0.5786 1.0000
5.000 0.6614 0.02340 0.01367 -0.0168 0.5632 1.0000
5.250 0.6842 0.02358 0.01400 -0.0155 0.5457 1.0000
5.500 0.7068 0.02375 0.01434 -0.0142 0.5264 1.0000
5.750 0.7300 0.02376 0.01447 -0.0126 0.5071 1.0000
6.000 0.7519 0.02398 0.01485 -0.0112 0.4834 1.0000
6.250 0.7735 0.02417 0.01518 -0.0097 0.4577 1.0000
6.500 0.7945 0.02439 0.01561 -0.0081 0.4288 1.0000
6.750 0.8141 0.02473 0.01602 -0.0065 0.3955 1.0000
7.000 0.8319 0.02523 0.01652 -0.0048 0.3569 1.0000
7.250 0.8471 0.02600 0.01729 -0.0032 0.3112 1.0000
7.500 0.8589 0.02708 0.01823 -0.0014 0.2594 1.0000
7.750 0.8668 0.02862 0.01952 0.0003 0.2040 1.0000
8.000 0.8714 0.03059 0.02116 0.0020 0.1564 1.0000
8.250 0.8752 0.03278 0.02312 0.0037 0.1231 1.0000
8.500 0.8776 0.03508 0.02522 0.0055 0.0990 1.0000
8.750 0.8807 0.03728 0.02736 0.0072 0.0813 1.0000
9.000 0.8844 0.03954 0.02965 0.0092 0.0706 1.0000
9.250 0.8886 0.04179 0.03190 0.0107 0.0610 1.0000
9.500 0.8923 0.04405 0.03416 0.0119 0.0529 1.0000
9.750 0.9084 0.04644 0.03685 0.0137 0.0466 1.0000
10.000 0.9177 0.04886 0.03947 0.0149 0.0418 1.0000
10.250 0.9255 0.05169 0.04254 0.0159 0.0376 1.0000
10.500 0.9304 0.05465 0.04583 0.0167 0.0346 1.0000
10.750 0.9334 0.05799 0.04945 0.0174 0.0328 1.0000
11.000 0.9325 0.06157 0.05325 0.0176 0.0317 1.0000
11.250 0.9282 0.06547 0.05738 0.0175 0.0309 1.0000
11.500 0.9211 0.06970 0.06182 0.0167 0.0305 1.0000
11.750 0.9112 0.07437 0.06669 0.0154 0.0302 1.0000
12.000 0.8979 0.07967 0.07221 0.0132 0.0301 1.0000
12.250 0.8821 0.08565 0.07838 0.0102 0.0302 1.0000
12.500 0.8605 0.09327 0.08624 0.0055 0.0308 1.0000
12.750 0.8367 0.10239 0.09553 -0.0004 0.0316 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 61 10.26% (mh61-il)