MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 500,000 Max Cl/Cd: 73.79 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh30-il-500000-n5.txt Download as CSV file: xf-mh30-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4851 0.08388 0.08168 -0.0212 1.0000 0.0078
-8.500 -0.4808 0.08059 0.07842 -0.0229 1.0000 0.0077
-8.250 -0.4879 0.07648 0.07432 -0.0243 1.0000 0.0068
-8.000 -0.4930 0.07220 0.07009 -0.0268 1.0000 0.0067
-7.750 -0.5028 0.06685 0.06478 -0.0314 1.0000 0.0065
-7.500 -0.5049 0.06045 0.05834 -0.0371 1.0000 0.0063
-7.250 -0.5061 0.05428 0.05209 -0.0405 1.0000 0.0062
-7.000 -0.5071 0.04889 0.04658 -0.0415 1.0000 0.0060
-6.750 -0.4971 0.04143 0.03882 -0.0448 0.9955 0.0056
-6.500 -0.4782 0.03272 0.02957 -0.0483 0.9883 0.0049
-6.250 -0.4564 0.02331 0.01918 -0.0499 0.9827 0.0041
-6.000 -0.4294 0.02032 0.01573 -0.0504 0.9780 0.0039
-5.750 -0.4014 0.01839 0.01346 -0.0508 0.9732 0.0038
-5.500 -0.3714 0.01673 0.01152 -0.0515 0.9693 0.0037
-5.250 -0.3440 0.01535 0.00986 -0.0515 0.9633 0.0037
-5.000 -0.3158 0.01410 0.00841 -0.0517 0.9575 0.0036
-4.750 -0.2892 0.01293 0.00706 -0.0514 0.9510 0.0036
-4.500 -0.2632 0.01193 0.00591 -0.0509 0.9443 0.0037
-4.250 -0.2375 0.01111 0.00496 -0.0504 0.9379 0.0037
-4.000 -0.2119 0.01041 0.00411 -0.0498 0.9311 0.0039
-3.750 -0.1857 0.00990 0.00347 -0.0493 0.9246 0.0041
-3.500 -0.1594 0.00953 0.00297 -0.0488 0.9175 0.0047
-3.250 -0.1329 0.00923 0.00261 -0.0484 0.9103 0.0062
-3.000 -0.1066 0.00893 0.00228 -0.0479 0.9027 0.0183
-2.750 -0.0809 0.00853 0.00203 -0.0475 0.8943 0.0568
-2.500 -0.0556 0.00805 0.00182 -0.0471 0.8862 0.1317
-2.250 -0.0301 0.00764 0.00167 -0.0468 0.8773 0.2083
-2.000 -0.0044 0.00725 0.00154 -0.0465 0.8684 0.2910
-1.750 0.0215 0.00695 0.00143 -0.0461 0.8594 0.3614
-1.500 0.0475 0.00669 0.00132 -0.0458 0.8493 0.4266
-1.250 0.0734 0.00644 0.00125 -0.0454 0.8385 0.4957
-1.000 0.0991 0.00622 0.00119 -0.0449 0.8263 0.5610
-0.750 0.1247 0.00603 0.00114 -0.0443 0.8118 0.6218
-0.500 0.1499 0.00587 0.00109 -0.0436 0.7957 0.6802
-0.250 0.1749 0.00573 0.00107 -0.0428 0.7785 0.7374
0.000 0.1995 0.00561 0.00106 -0.0419 0.7591 0.7924
0.250 0.2236 0.00552 0.00106 -0.0408 0.7376 0.8463
0.500 0.2487 0.00550 0.00107 -0.0398 0.7131 0.8976
0.750 0.2812 0.00556 0.00108 -0.0406 0.6840 0.9411
1.000 0.3203 0.00569 0.00107 -0.0430 0.6504 0.9705
1.250 0.3571 0.00586 0.00109 -0.0450 0.6158 0.9903
1.500 0.3898 0.00606 0.00114 -0.0461 0.5807 1.0000
1.750 0.4141 0.00626 0.00120 -0.0454 0.5488 1.0000
2.000 0.4385 0.00647 0.00127 -0.0448 0.5159 1.0000
2.250 0.4631 0.00670 0.00136 -0.0442 0.4826 1.0000
2.500 0.4877 0.00694 0.00146 -0.0436 0.4484 1.0000
2.750 0.5125 0.00719 0.00161 -0.0430 0.4151 1.0000
3.000 0.5374 0.00746 0.00175 -0.0425 0.3813 1.0000
3.250 0.5622 0.00774 0.00191 -0.0420 0.3475 1.0000
3.500 0.5871 0.00804 0.00208 -0.0416 0.3139 1.0000
3.750 0.6120 0.00835 0.00226 -0.0411 0.2814 1.0000
4.000 0.6369 0.00867 0.00250 -0.0407 0.2491 1.0000
4.250 0.6618 0.00900 0.00272 -0.0402 0.2197 1.0000
4.500 0.6870 0.00931 0.00295 -0.0398 0.1955 1.0000
4.750 0.7116 0.00968 0.00321 -0.0394 0.1666 1.0000
5.000 0.7357 0.01014 0.00352 -0.0389 0.1319 1.0000
5.250 0.7597 0.01061 0.00385 -0.0384 0.1002 1.0000
5.500 0.7843 0.01101 0.00418 -0.0379 0.0810 1.0000
5.750 0.8084 0.01148 0.00461 -0.0374 0.0601 1.0000
6.000 0.8320 0.01200 0.00503 -0.0369 0.0394 1.0000
6.250 0.8554 0.01257 0.00550 -0.0363 0.0226 1.0000
6.500 0.8793 0.01305 0.00596 -0.0357 0.0153 1.0000
6.750 0.9027 0.01360 0.00649 -0.0351 0.0083 1.0000
7.000 0.9260 0.01416 0.00707 -0.0345 0.0041 1.0000
7.250 0.9492 0.01474 0.00773 -0.0338 0.0029 1.0000
7.500 0.9719 0.01539 0.00848 -0.0330 0.0023 1.0000
7.750 0.9943 0.01606 0.00926 -0.0322 0.0021 1.0000
8.000 1.0156 0.01690 0.01023 -0.0312 0.0019 1.0000
8.250 1.0361 0.01781 0.01134 -0.0301 0.0018 1.0000
8.500 1.0551 0.01889 0.01258 -0.0289 0.0017 1.0000
8.750 1.0730 0.02008 0.01394 -0.0275 0.0017 1.0000
9.000 1.0895 0.02142 0.01547 -0.0260 0.0016 1.0000
9.250 1.1037 0.02304 0.01729 -0.0242 0.0016 1.0000
9.500 1.1171 0.02470 0.01917 -0.0223 0.0016 1.0000
9.750 1.1280 0.02662 0.02133 -0.0203 0.0016 1.0000
10.000 1.1368 0.02868 0.02364 -0.0181 0.0016 1.0000
10.250 1.1421 0.03093 0.02617 -0.0156 0.0015 1.0000
10.500 1.1438 0.03314 0.02863 -0.0128 0.0015 1.0000
10.750 1.1423 0.03505 0.03075 -0.0096 0.0016 1.0000
11.000 1.1352 0.03751 0.03344 -0.0065 0.0016 1.0000
11.250 1.1270 0.04018 0.03632 -0.0041 0.0016 1.0000
11.500 1.1135 0.04363 0.04001 -0.0024 0.0016 1.0000
11.750 1.1007 0.04738 0.04397 -0.0020 0.0016 1.0000
12.000 1.0929 0.05095 0.04770 -0.0026 0.0016 1.0000
12.250 1.0803 0.05577 0.05270 -0.0045 0.0016 1.0000
12.500 1.0635 0.06212 0.05924 -0.0081 0.0016 1.0000
12.750 1.0516 0.06854 0.06580 -0.0124 0.0016 1.0000
13.000 1.0316 0.07758 0.07501 -0.0186 0.0016 1.0000
13.250 1.0160 0.08638 0.08394 -0.0244 0.0016 1.0000
13.500 0.9970 0.09634 0.09401 -0.0304 0.0016 1.0000
13.750 0.9849 0.10462 0.10236 -0.0350 0.0016 1.0000
14.000 0.9661 0.11479 0.11261 -0.0404 0.0017 1.0000
14.250 0.9435 0.12632 0.12421 -0.0462 0.0017 1.0000
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Polar data table (+)
Polar graphs
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