MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 500,000 Max Cl/Cd: 85.05 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh30-il-500000.txt Download as CSV file: xf-mh30-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 30 7.84%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4677 0.08494 0.08275 -0.0230 1.0000 0.0156
-8.250 -0.4679 0.08061 0.07845 -0.0254 1.0000 0.0157
-8.000 -0.4692 0.07637 0.07425 -0.0281 1.0000 0.0157
-7.750 -0.4747 0.07169 0.06961 -0.0318 1.0000 0.0157
-7.500 -0.4736 0.06568 0.06357 -0.0375 1.0000 0.0157
-7.250 -0.4724 0.06034 0.05815 -0.0405 1.0000 0.0157
-7.000 -0.4719 0.05589 0.05359 -0.0416 1.0000 0.0157
-6.750 -0.4729 0.05196 0.04953 -0.0412 1.0000 0.0157
-6.500 -0.4754 0.04873 0.04616 -0.0393 1.0000 0.0157
-6.250 -0.4775 0.04582 0.04310 -0.0369 1.0000 0.0157
-6.000 -0.4846 0.03615 0.03304 -0.0381 0.9982 0.0170
-5.750 -0.4560 0.03266 0.02934 -0.0409 0.9953 0.0178
-5.500 -0.4260 0.02963 0.02603 -0.0432 0.9924 0.0189
-5.250 -0.3957 0.02666 0.02276 -0.0448 0.9886 0.0203
-5.000 -0.3629 0.02382 0.01955 -0.0464 0.9855 0.0218
-4.750 -0.3289 0.01820 0.01317 -0.0464 0.9831 0.0127
-4.500 -0.2946 0.01458 0.00902 -0.0469 0.9815 0.0097
-4.250 -0.2646 0.01312 0.00734 -0.0470 0.9774 0.0088
-4.000 -0.2313 0.01200 0.00608 -0.0480 0.9743 0.0085
-3.750 -0.1964 0.01097 0.00493 -0.0494 0.9718 0.0086
-3.500 -0.1609 0.01007 0.00388 -0.0508 0.9694 0.0093
-3.250 -0.1296 0.00950 0.00319 -0.0513 0.9647 0.0130
-3.000 -0.1001 0.00864 0.00264 -0.0517 0.9593 0.0989
-2.750 -0.0690 0.00804 0.00241 -0.0527 0.9552 0.1975
-2.500 -0.0452 0.00743 0.00227 -0.0521 0.9473 0.3234
-2.250 -0.0187 0.00689 0.00214 -0.0519 0.9417 0.4452
-2.000 0.0037 0.00643 0.00207 -0.0507 0.9332 0.5630
-1.750 0.0277 0.00609 0.00198 -0.0497 0.9264 0.6524
-1.500 0.0507 0.00581 0.00193 -0.0483 0.9180 0.7290
-1.250 0.0736 0.00558 0.00190 -0.0468 0.9098 0.7989
-1.000 0.0968 0.00540 0.00184 -0.0452 0.9017 0.8593
-0.750 0.1223 0.00527 0.00181 -0.0441 0.8917 0.9113
-0.500 0.1581 0.00522 0.00173 -0.0454 0.8828 0.9503
-0.250 0.1997 0.00519 0.00163 -0.0481 0.8744 0.9733
0.000 0.2415 0.00516 0.00156 -0.0510 0.8635 0.9885
0.250 0.2836 0.00514 0.00149 -0.0540 0.8516 1.0000
0.500 0.3068 0.00515 0.00143 -0.0529 0.8371 1.0000
0.750 0.3304 0.00517 0.00138 -0.0519 0.8214 1.0000
1.000 0.3544 0.00521 0.00135 -0.0510 0.8035 1.0000
1.250 0.3786 0.00526 0.00132 -0.0501 0.7833 1.0000
1.500 0.4029 0.00533 0.00132 -0.0492 0.7599 1.0000
1.750 0.4271 0.00544 0.00132 -0.0483 0.7330 1.0000
2.000 0.4513 0.00558 0.00134 -0.0474 0.7023 1.0000
2.250 0.4754 0.00575 0.00138 -0.0465 0.6688 1.0000
2.750 0.5237 0.00620 0.00157 -0.0449 0.5957 1.0000
3.000 0.5480 0.00646 0.00169 -0.0442 0.5582 1.0000
3.250 0.5724 0.00673 0.00182 -0.0435 0.5190 1.0000
3.500 0.5967 0.00703 0.00197 -0.0429 0.4783 1.0000
3.750 0.6210 0.00736 0.00215 -0.0422 0.4354 1.0000
4.000 0.6451 0.00772 0.00237 -0.0416 0.3914 1.0000
4.250 0.6694 0.00809 0.00259 -0.0411 0.3495 1.0000
4.500 0.6938 0.00847 0.00282 -0.0405 0.3102 1.0000
4.750 0.7179 0.00889 0.00309 -0.0400 0.2684 1.0000
5.000 0.7416 0.00937 0.00338 -0.0394 0.2224 1.0000
5.250 0.7654 0.00987 0.00370 -0.0389 0.1806 1.0000
5.500 0.7894 0.01033 0.00404 -0.0384 0.1489 1.0000
5.750 0.8132 0.01083 0.00446 -0.0378 0.1161 1.0000
6.000 0.8363 0.01143 0.00488 -0.0372 0.0827 1.0000
6.250 0.8593 0.01204 0.00535 -0.0366 0.0535 1.0000
6.500 0.8822 0.01267 0.00588 -0.0359 0.0338 1.0000
6.750 0.9053 0.01328 0.00643 -0.0353 0.0203 1.0000
7.000 0.9246 0.01461 0.00780 -0.0337 0.0069 1.0000
7.250 0.9462 0.01549 0.00882 -0.0326 0.0059 1.0000
7.500 0.9665 0.01654 0.01001 -0.0313 0.0052 1.0000
7.750 0.9857 0.01771 0.01133 -0.0299 0.0050 1.0000
8.000 1.0035 0.01913 0.01293 -0.0283 0.0048 1.0000
8.250 1.0205 0.02074 0.01473 -0.0266 0.0047 1.0000
8.500 1.0365 0.02269 0.01697 -0.0248 0.0047 1.0000
8.750 1.0511 0.02513 0.01971 -0.0228 0.0049 1.0000
9.000 1.0625 0.02838 0.02334 -0.0205 0.0051 1.0000
9.250 1.0679 0.03250 0.02794 -0.0176 0.0055 1.0000
9.500 1.0664 0.03697 0.03287 -0.0144 0.0059 1.0000
9.750 1.0586 0.04132 0.03761 -0.0110 0.0063 1.0000
10.000 1.0446 0.04514 0.04174 -0.0073 0.0066 1.0000
10.250 1.0250 0.04859 0.04541 -0.0036 0.0068 1.0000
10.500 1.0057 0.05225 0.04927 -0.0017 0.0069 1.0000
10.750 0.9882 0.05620 0.05339 -0.0013 0.0069 1.0000
11.000 0.9687 0.06115 0.05850 -0.0028 0.0070 1.0000
11.250 0.9509 0.06689 0.06440 -0.0061 0.0070 1.0000
11.500 0.9318 0.07426 0.07192 -0.0115 0.0070 1.0000
11.750 0.9147 0.08295 0.08073 -0.0183 0.0069 1.0000
12.000 0.9027 0.09172 0.08959 -0.0248 0.0068 1.0000
12.250 0.8855 0.10308 0.10103 -0.0318 0.0067 1.0000
12.500 0.8620 0.11646 0.11436 -0.0382 0.0068 1.0000
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Polar data table (+)
Polar graphs
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