MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 500,000 Max Cl/Cd: 78.81 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh25-il-500000.txt Download as CSV file: xf-mh25-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 25 9.98%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3933 0.11411 0.11202 -0.0287 1.0000 0.0120
-11.000 -0.3996 0.11010 0.10802 -0.0287 1.0000 0.0123
-10.750 -0.4032 0.10680 0.10473 -0.0285 1.0000 0.0125
-4.250 -0.3513 0.01850 0.01246 -0.0273 0.9494 0.0099
-4.000 -0.3222 0.01666 0.01041 -0.0270 0.9477 0.0088
-3.750 -0.2923 0.01528 0.00886 -0.0271 0.9461 0.0081
-3.500 -0.2604 0.01435 0.00782 -0.0278 0.9448 0.0079
-3.250 -0.2264 0.01362 0.00698 -0.0290 0.9437 0.0083
-3.000 -0.2140 0.01326 0.00654 -0.0256 0.9369 0.0087
-2.750 -0.1823 0.01284 0.00602 -0.0263 0.9344 0.0106
-2.500 -0.1538 0.01172 0.00548 -0.0267 0.9325 0.1545
-2.000 -0.1412 0.00883 0.00522 -0.0182 0.9219 0.7880
-1.750 -0.1057 0.00898 0.00559 -0.0188 0.9206 0.8973
-1.500 -0.0667 0.00922 0.00578 -0.0204 0.9195 0.9200
-1.250 -0.0251 0.00937 0.00585 -0.0229 0.9187 0.9308
-1.000 0.0268 0.00958 0.00600 -0.0277 0.9186 0.9363
-0.750 0.0706 0.00963 0.00600 -0.0307 0.9178 0.9432
-0.500 0.1446 0.00989 0.00620 -0.0404 0.9193 0.9455
-0.250 0.2012 0.00986 0.00613 -0.0464 0.9190 0.9476
0.000 0.2480 0.00970 0.00595 -0.0503 0.9177 0.9498
0.250 0.2698 0.00966 0.00590 -0.0489 0.9112 0.9565
0.500 0.3164 0.00947 0.00571 -0.0528 0.9081 0.9580
0.750 0.3620 0.00924 0.00547 -0.0565 0.9051 0.9597
1.000 0.3996 0.00905 0.00530 -0.0585 0.8995 0.9626
1.250 0.4303 0.00887 0.00513 -0.0589 0.8922 0.9668
1.500 0.4585 0.00870 0.00497 -0.0589 0.8828 0.9705
1.750 0.4950 0.00844 0.00472 -0.0607 0.8726 0.9723
2.000 0.5277 0.00823 0.00456 -0.0617 0.8570 0.9748
2.250 0.5590 0.00803 0.00435 -0.0623 0.8356 0.9775
2.500 0.5873 0.00791 0.00413 -0.0622 0.7981 0.9803
2.750 0.6132 0.00799 0.00400 -0.0617 0.7474 0.9828
3.000 0.6415 0.00816 0.00390 -0.0619 0.6817 0.9845
3.250 0.6667 0.00846 0.00392 -0.0615 0.6176 0.9868
3.500 0.6895 0.00884 0.00401 -0.0608 0.5481 0.9895
3.750 0.7124 0.00920 0.00414 -0.0601 0.4902 0.9921
4.000 0.7347 0.00963 0.00431 -0.0594 0.4288 0.9942
4.250 0.7611 0.01000 0.00443 -0.0596 0.3669 0.9959
4.750 0.8118 0.01092 0.00486 -0.0598 0.2468 0.9994
5.000 0.8315 0.01142 0.00513 -0.0586 0.1969 1.0000
5.250 0.8475 0.01190 0.00543 -0.0566 0.1559 1.0000
5.500 0.8640 0.01235 0.00575 -0.0547 0.1230 1.0000
5.750 0.8801 0.01280 0.00609 -0.0527 0.0959 1.0000
6.000 0.8956 0.01328 0.00647 -0.0505 0.0713 1.0000
6.250 0.9102 0.01383 0.00692 -0.0482 0.0503 1.0000
6.500 0.9236 0.01444 0.00749 -0.0455 0.0356 1.0000
6.750 0.9362 0.01509 0.00821 -0.0426 0.0287 1.0000
7.000 0.9508 0.01551 0.00869 -0.0402 0.0245 1.0000
7.250 0.9583 0.01642 0.00966 -0.0365 0.0199 1.0000
7.500 0.9760 0.01651 0.00978 -0.0348 0.0179 1.0000
7.750 0.9890 0.01690 0.01024 -0.0321 0.0156 1.0000
8.000 0.9942 0.01780 0.01120 -0.0279 0.0113 1.0000
8.250 1.0042 0.01831 0.01177 -0.0246 0.0086 1.0000
8.500 1.0083 0.01909 0.01263 -0.0203 0.0076 1.0000
8.750 0.9923 0.02123 0.01498 -0.0121 0.0064 1.0000
9.000 0.9913 0.02210 0.01598 -0.0067 0.0064 1.0000
9.250 0.9933 0.02275 0.01674 -0.0019 0.0060 1.0000
9.500 0.9951 0.02392 0.01807 0.0026 0.0059 1.0000
9.750 0.9996 0.02502 0.01932 0.0065 0.0058 1.0000
10.000 1.0042 0.02648 0.02095 0.0102 0.0055 1.0000
10.250 1.0085 0.02795 0.02264 0.0138 0.0052 1.0000
10.500 1.0148 0.02886 0.02367 0.0168 0.0049 1.0000
10.750 1.0231 0.02924 0.02410 0.0193 0.0044 1.0000
11.000 1.0324 0.02951 0.02437 0.0214 0.0039 1.0000
11.250 1.0291 0.03213 0.02729 0.0253 0.0040 1.0000
11.500 1.0329 0.03315 0.02838 0.0277 0.0037 1.0000
11.750 1.0289 0.03542 0.03087 0.0308 0.0037 1.0000
12.000 1.0200 0.03819 0.03389 0.0340 0.0037 1.0000
12.250 1.0088 0.04113 0.03704 0.0367 0.0036 1.0000
12.500 0.9993 0.04398 0.04008 0.0387 0.0036 1.0000
12.750 0.9835 0.04775 0.04406 0.0401 0.0035 1.0000
13.000 0.9680 0.05181 0.04832 0.0404 0.0035 1.0000
13.250 0.9539 0.05630 0.05303 0.0399 0.0036 1.0000
13.500 0.9377 0.06143 0.05832 0.0380 0.0035 1.0000
13.750 0.9140 0.06863 0.06570 0.0344 0.0034 1.0000
14.000 0.9041 0.07435 0.07156 0.0310 0.0035 1.0000
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Polar data table (+)
Polar graphs
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