MH 25 9.98% (mh25-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 25 9.98% (mh25-il) Reynolds number: 100,000 Max Cl/Cd: 51.87 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh25-il-100000.txt Download as CSV file: xf-mh25-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4942 0.09455 0.08992 -0.0325 1.0000 0.0889
-8.500 -0.5098 0.09132 0.08677 -0.0331 1.0000 0.0913
-8.250 -0.5305 0.08834 0.08385 -0.0336 1.0000 0.0922
-8.000 -0.5580 0.08611 0.08167 -0.0315 1.0000 0.0929
-7.750 -0.5866 0.08375 0.07926 -0.0299 1.0000 0.0939
-7.500 -0.6201 0.08227 0.07756 -0.0272 1.0000 0.0947
-7.250 -0.6001 0.07650 0.07204 -0.0257 1.0000 0.0974
-7.000 -0.5989 0.07365 0.06921 -0.0231 1.0000 0.1007
-6.750 -0.6075 0.07084 0.06631 -0.0211 1.0000 0.1050
-6.250 -0.6152 0.06435 0.05969 -0.0166 1.0000 0.1137
-4.750 -0.5760 0.03954 0.03244 -0.0009 1.0000 0.0576
-4.500 -0.5546 0.03688 0.02894 0.0028 1.0000 0.0428
-4.250 -0.5377 0.03290 0.02478 0.0044 1.0000 0.0400
-4.000 -0.5182 0.03025 0.02173 0.0064 1.0000 0.0378
-3.750 -0.4968 0.02813 0.01919 0.0083 1.0000 0.0378
-3.500 -0.4745 0.02644 0.01710 0.0099 1.0000 0.0388
-3.250 -0.4520 0.02551 0.01580 0.0116 1.0000 0.0424
-3.000 -0.4284 0.02328 0.01350 0.0129 1.0000 0.0446
-2.750 -0.1534 0.01915 0.01276 -0.0273 1.0000 1.0000
-2.500 -0.1446 0.01897 0.01237 -0.0246 1.0000 1.0000
-2.250 -0.1350 0.01883 0.01204 -0.0219 1.0000 1.0000
-2.000 -0.1250 0.01874 0.01178 -0.0193 1.0000 1.0000
-1.750 -0.1147 0.01869 0.01157 -0.0167 1.0000 1.0000
-1.500 -0.1041 0.01867 0.01141 -0.0142 1.0000 1.0000
-1.250 -0.0933 0.01868 0.01129 -0.0116 1.0000 1.0000
-1.000 -0.0824 0.01872 0.01122 -0.0091 1.0000 1.0000
-0.750 -0.0715 0.01879 0.01116 -0.0067 1.0000 1.0000
-0.500 -0.0607 0.01889 0.01117 -0.0042 1.0000 1.0000
-0.250 -0.0497 0.01902 0.01121 -0.0018 1.0000 1.0000
0.000 -0.0389 0.01918 0.01130 0.0006 1.0000 1.0000
0.250 -0.0281 0.01938 0.01143 0.0029 1.0000 1.0000
0.500 -0.0172 0.01961 0.01160 0.0051 1.0000 1.0000
0.750 -0.0051 0.01988 0.01181 0.0070 0.9997 1.0000
1.000 0.0498 0.02062 0.01250 0.0005 0.9885 1.0000
1.250 0.1006 0.02127 0.01313 -0.0051 0.9769 1.0000
1.500 0.1494 0.02179 0.01365 -0.0102 0.9646 1.0000
1.750 0.1969 0.02220 0.01408 -0.0148 0.9520 1.0000
2.000 0.2442 0.02249 0.01441 -0.0191 0.9391 1.0000
2.250 0.2911 0.02264 0.01465 -0.0232 0.9260 1.0000
2.500 0.3378 0.02264 0.01474 -0.0271 0.9125 1.0000
2.750 0.3840 0.02250 0.01471 -0.0306 0.8988 1.0000
3.000 0.4299 0.02218 0.01452 -0.0338 0.8842 1.0000
3.250 0.4766 0.02168 0.01423 -0.0369 0.8693 1.0000
3.500 0.5260 0.02093 0.01369 -0.0402 0.8542 1.0000
3.750 0.5793 0.01990 0.01293 -0.0438 0.8390 1.0000
4.000 0.6275 0.01869 0.01196 -0.0461 0.8208 1.0000
4.250 0.6744 0.01737 0.01089 -0.0478 0.7971 1.0000
4.500 0.7163 0.01630 0.01000 -0.0487 0.7590 1.0000
4.750 0.7668 0.01543 0.00921 -0.0512 0.6938 1.0000
5.000 0.7998 0.01542 0.00892 -0.0508 0.6076 1.0000
5.250 0.8154 0.01597 0.00910 -0.0477 0.5253 1.0000
5.500 0.8244 0.01672 0.00948 -0.0438 0.4477 1.0000
5.750 0.8308 0.01758 0.00997 -0.0396 0.3765 1.0000
6.000 0.8357 0.01853 0.01056 -0.0353 0.3094 1.0000
6.250 0.8401 0.01959 0.01125 -0.0310 0.2481 1.0000
6.500 0.8443 0.02079 0.01210 -0.0269 0.1945 1.0000
6.750 0.8495 0.02209 0.01310 -0.0228 0.1504 1.0000
7.000 0.8558 0.02344 0.01421 -0.0191 0.1187 1.0000
7.250 0.8683 0.02509 0.01578 -0.0161 0.0973 1.0000
7.500 0.8817 0.02652 0.01724 -0.0136 0.0816 1.0000
7.750 0.9020 0.02839 0.01918 -0.0122 0.0706 1.0000
8.000 0.9309 0.03128 0.02215 -0.0122 0.0633 1.0000
8.250 0.9476 0.03312 0.02427 -0.0100 0.0570 1.0000
8.500 0.9631 0.03605 0.02739 -0.0080 0.0515 1.0000
8.750 0.9722 0.03884 0.03073 -0.0043 0.0489 1.0000
9.000 0.9794 0.04056 0.03256 -0.0012 0.0437 1.0000
9.250 0.9786 0.04435 0.03662 0.0026 0.0406 1.0000
9.500 0.9754 0.04723 0.03993 0.0074 0.0402 1.0000
9.750 0.9689 0.05039 0.04348 0.0122 0.0401 1.0000
10.000 0.9588 0.05366 0.04709 0.0170 0.0401 1.0000
10.250 0.9439 0.05694 0.05068 0.0220 0.0401 1.0000
10.500 0.9313 0.06032 0.05424 0.0261 0.0406 1.0000
10.750 0.9143 0.06385 0.05794 0.0302 0.0409 1.0000
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Polar data table (+)
Polar graphs
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