MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.53 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh30-il-1000000.txt Download as CSV file: xf-mh30-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4660 0.08313 0.08156 -0.0215 1.0000 0.0075
-8.250 -0.4667 0.07880 0.07726 -0.0237 1.0000 0.0075
-8.000 -0.4681 0.07463 0.07311 -0.0260 1.0000 0.0075
-7.750 -0.4745 0.07025 0.06877 -0.0287 1.0000 0.0075
-7.500 -0.4763 0.06456 0.06308 -0.0345 1.0000 0.0075
-7.250 -0.4741 0.05849 0.05696 -0.0389 1.0000 0.0075
-7.000 -0.4731 0.05335 0.05173 -0.0405 1.0000 0.0075
-6.750 -0.4792 0.04942 0.04772 -0.0389 1.0000 0.0075
-6.500 -0.4741 0.03313 0.03072 -0.0487 0.9937 0.0084
-6.250 -0.4497 0.02940 0.02672 -0.0509 0.9896 0.0089
-6.000 -0.4210 0.02655 0.02363 -0.0530 0.9864 0.0095
-5.750 -0.3907 0.02408 0.02093 -0.0548 0.9838 0.0102
-5.500 -0.3597 0.02169 0.01824 -0.0564 0.9811 0.0112
-5.250 -0.3338 0.01974 0.01604 -0.0563 0.9749 0.0125
-5.000 -0.3053 0.01818 0.01424 -0.0564 0.9701 0.0140
-4.500 -0.2563 0.01220 0.00750 -0.0533 0.9567 0.0067
-4.250 -0.2334 0.01051 0.00560 -0.0519 0.9494 0.0060
-4.000 -0.2102 0.00937 0.00428 -0.0506 0.9425 0.0056
-3.750 -0.1857 0.00862 0.00338 -0.0496 0.9351 0.0053
-3.500 -0.1604 0.00812 0.00274 -0.0488 0.9285 0.0053
-3.250 -0.1342 0.00777 0.00229 -0.0482 0.9211 0.0055
-3.000 -0.1078 0.00755 0.00193 -0.0476 0.9146 0.0060
-2.750 -0.0812 0.00721 0.00162 -0.0472 0.9071 0.0246
-2.500 -0.0560 0.00669 0.00139 -0.0467 0.9002 0.1049
-2.250 -0.0298 0.00637 0.00126 -0.0465 0.8923 0.1627
-2.000 -0.0040 0.00600 0.00115 -0.0462 0.8848 0.2456
-1.750 0.0207 0.00544 0.00105 -0.0458 0.8762 0.3882
-1.500 0.0462 0.00506 0.00097 -0.0454 0.8665 0.4949
-1.250 0.0721 0.00481 0.00092 -0.0450 0.8566 0.5722
-1.000 0.0978 0.00458 0.00088 -0.0445 0.8465 0.6464
-0.750 0.1234 0.00438 0.00085 -0.0439 0.8354 0.7151
-0.500 0.1489 0.00422 0.00083 -0.0432 0.8234 0.7746
-0.250 0.1740 0.00409 0.00082 -0.0424 0.8103 0.8278
0.000 0.1987 0.00399 0.00082 -0.0415 0.7956 0.8779
0.250 0.2240 0.00393 0.00082 -0.0406 0.7789 0.9255
0.500 0.2580 0.00395 0.00082 -0.0417 0.7589 0.9612
0.750 0.2967 0.00403 0.00081 -0.0440 0.7342 0.9814
1.000 0.3351 0.00414 0.00080 -0.0463 0.7049 0.9925
1.250 0.3729 0.00430 0.00081 -0.0486 0.6702 0.9999
1.500 0.3975 0.00446 0.00084 -0.0479 0.6371 1.0000
1.750 0.4218 0.00464 0.00088 -0.0472 0.6039 1.0000
2.000 0.4464 0.00482 0.00094 -0.0466 0.5707 1.0000
2.250 0.4710 0.00502 0.00101 -0.0459 0.5374 1.0000
2.500 0.4958 0.00523 0.00109 -0.0453 0.5022 1.0000
2.750 0.5205 0.00546 0.00121 -0.0447 0.4662 1.0000
3.000 0.5454 0.00571 0.00132 -0.0442 0.4304 1.0000
3.250 0.5703 0.00597 0.00144 -0.0437 0.3935 1.0000
3.500 0.5951 0.00626 0.00158 -0.0432 0.3536 1.0000
3.750 0.6202 0.00655 0.00173 -0.0427 0.3174 1.0000
4.000 0.6453 0.00683 0.00192 -0.0423 0.2850 1.0000
4.250 0.6701 0.00717 0.00211 -0.0418 0.2470 1.0000
4.500 0.6946 0.00757 0.00232 -0.0413 0.2049 1.0000
4.750 0.7192 0.00795 0.00255 -0.0409 0.1685 1.0000
5.000 0.7430 0.00846 0.00283 -0.0404 0.1241 1.0000
5.250 0.7673 0.00889 0.00311 -0.0399 0.0917 1.0000
5.500 0.7921 0.00928 0.00339 -0.0394 0.0701 1.0000
5.750 0.8168 0.00967 0.00373 -0.0390 0.0516 1.0000
6.000 0.8412 0.01010 0.00408 -0.0385 0.0345 1.0000
6.250 0.8652 0.01060 0.00448 -0.0380 0.0186 1.0000
6.500 0.8880 0.01130 0.00509 -0.0372 0.0041 1.0000
6.750 0.9121 0.01184 0.00573 -0.0364 0.0030 1.0000
7.000 0.9360 0.01239 0.00637 -0.0357 0.0028 1.0000
7.250 0.9593 0.01301 0.00710 -0.0350 0.0027 1.0000
7.500 0.9814 0.01383 0.00805 -0.0339 0.0026 1.0000
7.750 1.0024 0.01475 0.00912 -0.0328 0.0026 1.0000
8.000 1.0213 0.01599 0.01054 -0.0313 0.0026 1.0000
8.250 1.0389 0.01743 0.01216 -0.0296 0.0026 1.0000
8.500 1.0548 0.01922 0.01422 -0.0277 0.0027 1.0000
8.750 1.0691 0.02140 0.01665 -0.0257 0.0028 1.0000
9.000 1.0809 0.02413 0.01968 -0.0234 0.0029 1.0000
9.250 1.0870 0.02775 0.02368 -0.0206 0.0031 1.0000
9.500 1.0892 0.03186 0.02809 -0.0176 0.0038 1.0000
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Polar data table (+)
Polar graphs
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