MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 200,000 Max Cl/Cd: 59.84 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh30-il-200000-n5.txt Download as CSV file: xf-mh30-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4835 0.08474 0.08129 -0.0207 1.0000 0.0112
-8.250 -0.4867 0.08011 0.07672 -0.0231 1.0000 0.0108
-8.000 -0.4911 0.07564 0.07231 -0.0257 1.0000 0.0104
-7.750 -0.4996 0.07062 0.06736 -0.0293 1.0000 0.0101
-7.500 -0.5029 0.06415 0.06089 -0.0352 1.0000 0.0097
-7.250 -0.5063 0.05633 0.05297 -0.0400 1.0000 0.0091
-7.000 -0.5077 0.04836 0.04476 -0.0420 1.0000 0.0083
-6.750 -0.5028 0.04364 0.03979 -0.0416 1.0000 0.0080
-6.500 -0.4952 0.04050 0.03642 -0.0404 1.0000 0.0078
-6.000 -0.4774 0.03521 0.03059 -0.0372 1.0000 0.0075
-5.750 -0.4703 0.03148 0.02649 -0.0354 1.0000 0.0074
-5.500 -0.4474 0.02753 0.02200 -0.0361 0.9969 0.0073
-5.250 -0.4179 0.02418 0.01810 -0.0374 0.9930 0.0072
-5.000 -0.3885 0.02159 0.01498 -0.0381 0.9888 0.0072
-4.750 -0.3571 0.01943 0.01242 -0.0390 0.9851 0.0073
-4.500 -0.3241 0.01767 0.01037 -0.0401 0.9821 0.0074
-4.250 -0.2935 0.01630 0.00881 -0.0407 0.9776 0.0075
-4.000 -0.2629 0.01462 0.00693 -0.0413 0.9731 0.0084
-3.750 -0.2285 0.01368 0.00582 -0.0427 0.9697 0.0102
-3.500 -0.1962 0.01302 0.00503 -0.0436 0.9651 0.0172
-3.250 -0.1662 0.01197 0.00441 -0.0445 0.9599 0.0847
-3.000 -0.1329 0.01140 0.00398 -0.0459 0.9560 0.1517
-2.750 -0.1041 0.01085 0.00373 -0.0464 0.9498 0.2378
-2.500 -0.0743 0.01023 0.00353 -0.0472 0.9443 0.3531
-2.250 -0.0454 0.00979 0.00336 -0.0475 0.9380 0.4428
-2.000 -0.0175 0.00937 0.00324 -0.0474 0.9310 0.5362
-1.750 0.0088 0.00901 0.00315 -0.0468 0.9234 0.6238
-1.500 0.0357 0.00871 0.00305 -0.0462 0.9161 0.7030
-1.250 0.0603 0.00848 0.00300 -0.0449 0.9071 0.7743
-1.000 0.0888 0.00830 0.00293 -0.0443 0.8997 0.8404
-0.750 0.1231 0.00819 0.00286 -0.0451 0.8912 0.8990
-0.500 0.1664 0.00810 0.00273 -0.0480 0.8834 0.9436
-0.250 0.2094 0.00802 0.00258 -0.0509 0.8745 0.9742
0.000 0.2506 0.00796 0.00246 -0.0536 0.8623 0.9966
0.250 0.2770 0.00794 0.00237 -0.0532 0.8475 1.0000
0.500 0.3005 0.00795 0.00231 -0.0521 0.8310 1.0000
0.750 0.3243 0.00797 0.00225 -0.0511 0.8135 1.0000
1.000 0.3485 0.00800 0.00221 -0.0501 0.7949 1.0000
1.250 0.3728 0.00805 0.00218 -0.0491 0.7733 1.0000
1.500 0.3972 0.00811 0.00217 -0.0482 0.7494 1.0000
1.750 0.4216 0.00820 0.00216 -0.0472 0.7221 1.0000
2.000 0.4459 0.00833 0.00217 -0.0463 0.6917 1.0000
2.250 0.4701 0.00851 0.00221 -0.0454 0.6586 1.0000
2.500 0.4941 0.00872 0.00228 -0.0444 0.6232 1.0000
2.750 0.5181 0.00897 0.00243 -0.0436 0.5866 1.0000
3.000 0.5419 0.00925 0.00257 -0.0427 0.5494 1.0000
3.250 0.5657 0.00956 0.00274 -0.0419 0.5113 1.0000
3.500 0.5895 0.00989 0.00293 -0.0411 0.4719 1.0000
3.750 0.6132 0.01025 0.00315 -0.0403 0.4317 1.0000
4.000 0.6367 0.01064 0.00345 -0.0396 0.3915 1.0000
4.250 0.6603 0.01105 0.00373 -0.0389 0.3518 1.0000
4.500 0.6838 0.01149 0.00405 -0.0382 0.3120 1.0000
4.750 0.7072 0.01196 0.00439 -0.0376 0.2735 1.0000
5.000 0.7306 0.01245 0.00477 -0.0369 0.2377 1.0000
5.250 0.7541 0.01294 0.00518 -0.0363 0.2050 1.0000
5.500 0.7772 0.01349 0.00563 -0.0357 0.1709 1.0000
5.750 0.8000 0.01411 0.00620 -0.0351 0.1370 1.0000
6.000 0.8225 0.01477 0.00674 -0.0344 0.1040 1.0000
6.250 0.8446 0.01548 0.00734 -0.0337 0.0750 1.0000
6.500 0.8669 0.01620 0.00802 -0.0329 0.0553 1.0000
6.750 0.8888 0.01697 0.00881 -0.0321 0.0406 1.0000
7.000 0.9100 0.01789 0.00979 -0.0310 0.0309 1.0000
7.250 0.9304 0.01887 0.01080 -0.0300 0.0223 1.0000
7.500 0.9511 0.01977 0.01170 -0.0292 0.0136 1.0000
7.750 0.9714 0.02071 0.01271 -0.0282 0.0089 1.0000
8.000 0.9884 0.02220 0.01440 -0.0267 0.0065 1.0000
8.250 1.0055 0.02361 0.01602 -0.0251 0.0056 1.0000
8.500 1.0218 0.02511 0.01772 -0.0236 0.0050 1.0000
8.750 1.0374 0.02668 0.01959 -0.0220 0.0046 1.0000
9.000 1.0516 0.02843 0.02156 -0.0204 0.0044 1.0000
9.250 1.0640 0.03038 0.02374 -0.0187 0.0042 1.0000
9.500 1.0737 0.03265 0.02629 -0.0167 0.0040 1.0000
9.750 1.0801 0.03522 0.02916 -0.0145 0.0039 1.0000
10.000 1.0821 0.03803 0.03229 -0.0121 0.0038 1.0000
10.250 1.0779 0.04085 0.03541 -0.0091 0.0038 1.0000
10.500 1.0700 0.04373 0.03858 -0.0062 0.0037 1.0000
10.750 1.0623 0.04659 0.04169 -0.0041 0.0038 1.0000
11.000 1.0501 0.05011 0.04546 -0.0029 0.0038 1.0000
11.250 1.0366 0.05409 0.04968 -0.0028 0.0038 1.0000
11.500 1.0200 0.05905 0.05487 -0.0041 0.0037 1.0000
11.750 1.0033 0.06483 0.06086 -0.0070 0.0038 1.0000
12.000 0.9920 0.07062 0.06683 -0.0107 0.0038 1.0000
12.250 0.9767 0.07811 0.07450 -0.0160 0.0039 1.0000
12.500 0.9583 0.08735 0.08390 -0.0225 0.0039 1.0000
12.750 0.9351 0.09912 0.09583 -0.0301 0.0041 1.0000
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Polar data table (+)
Polar graphs
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