MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 100,000 Max Cl/Cd: 51.15 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh30-il-100000.txt Download as CSV file: xf-mh30-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4890 0.10597 0.10111 -0.0144 1.0000 0.0778
-9.000 -0.4791 0.10249 0.09764 -0.0139 1.0000 0.0810
-8.750 -0.4767 0.09918 0.09430 -0.0154 1.0000 0.0842
-8.500 -0.4852 0.09615 0.09144 -0.0198 1.0000 0.0876
-8.250 -0.5064 0.09321 0.08865 -0.0270 1.0000 0.0886
-8.000 -0.4834 0.08823 0.08357 -0.0220 1.0000 0.0914
-7.750 -0.4768 0.08502 0.08040 -0.0215 1.0000 0.0951
-7.500 -0.4827 0.08171 0.07717 -0.0240 1.0000 0.0987
-7.250 -0.5095 0.07739 0.07276 -0.0384 1.0000 0.1021
-7.000 -0.4868 0.07307 0.06861 -0.0314 1.0000 0.1047
-6.750 -0.4795 0.06993 0.06549 -0.0309 1.0000 0.1092
-6.500 -0.4856 0.06513 0.06057 -0.0365 1.0000 0.1168
-6.250 -0.4747 0.06220 0.05772 -0.0340 1.0000 0.1203
-6.000 -0.4742 0.05829 0.05365 -0.0363 1.0000 0.1305
-5.750 -0.4638 0.05534 0.05075 -0.0344 1.0000 0.1346
-5.500 -0.4581 0.05195 0.04724 -0.0346 1.0000 0.1454
-5.250 -0.4355 0.03765 0.03122 -0.0373 1.0000 0.0486
-5.000 -0.4215 0.03381 0.02715 -0.0360 1.0000 0.0448
-4.750 -0.4033 0.02956 0.02204 -0.0341 1.0000 0.0394
-4.500 -0.3819 0.02771 0.01964 -0.0322 1.0000 0.0376
-4.250 -0.3613 0.02518 0.01673 -0.0308 1.0000 0.0378
-4.000 -0.3414 0.02296 0.01441 -0.0299 1.0000 0.0430
-3.750 -0.3186 0.02144 0.01259 -0.0285 1.0000 0.0477
-3.500 -0.2950 0.01948 0.01044 -0.0270 1.0000 0.0515
-3.250 -0.2733 0.01792 0.00899 -0.0258 1.0000 0.0676
-3.000 -0.2516 0.01642 0.00770 -0.0245 1.0000 0.1114
-2.750 -0.2321 0.01391 0.00655 -0.0233 1.0000 0.3371
-2.500 -0.2168 0.01274 0.00651 -0.0207 1.0000 0.5908
-2.250 -0.2039 0.01211 0.00655 -0.0159 1.0000 0.8102
-2.000 -0.1359 0.01191 0.00610 -0.0230 1.0000 1.0000
-1.750 -0.1179 0.01196 0.00587 -0.0218 1.0000 1.0000
-1.500 -0.0989 0.01206 0.00571 -0.0208 1.0000 1.0000
-1.250 -0.0793 0.01219 0.00562 -0.0198 1.0000 1.0000
-1.000 -0.0595 0.01235 0.00560 -0.0190 1.0000 1.0000
-0.750 -0.0397 0.01255 0.00559 -0.0181 1.0000 1.0000
-0.500 -0.0198 0.01278 0.00567 -0.0174 1.0000 1.0000
-0.250 -0.0001 0.01305 0.00582 -0.0167 1.0000 1.0000
0.000 0.0193 0.01336 0.00601 -0.0160 1.0000 1.0000
0.250 0.0686 0.01389 0.00641 -0.0211 0.9894 1.0000
0.500 0.1196 0.01440 0.00683 -0.0264 0.9780 1.0000
0.750 0.1707 0.01480 0.00719 -0.0315 0.9660 1.0000
1.000 0.2218 0.01508 0.00747 -0.0364 0.9532 1.0000
1.250 0.2719 0.01523 0.00764 -0.0409 0.9396 1.0000
1.500 0.3220 0.01526 0.00771 -0.0452 0.9254 1.0000
1.750 0.3739 0.01515 0.00770 -0.0495 0.9115 1.0000
2.000 0.4196 0.01496 0.00760 -0.0524 0.8959 1.0000
2.250 0.4615 0.01470 0.00743 -0.0543 0.8793 1.0000
2.500 0.5005 0.01436 0.00718 -0.0552 0.8621 1.0000
2.750 0.5296 0.01412 0.00709 -0.0543 0.8400 1.0000
3.000 0.5584 0.01382 0.00687 -0.0531 0.8173 1.0000
3.250 0.5844 0.01357 0.00668 -0.0514 0.7912 1.0000
3.500 0.6088 0.01340 0.00654 -0.0495 0.7605 1.0000
3.750 0.6335 0.01326 0.00640 -0.0476 0.7270 1.0000
4.000 0.6569 0.01327 0.00644 -0.0456 0.6869 1.0000
4.250 0.6796 0.01343 0.00652 -0.0437 0.6408 1.0000
4.500 0.7018 0.01372 0.00666 -0.0418 0.5912 1.0000
4.750 0.7232 0.01416 0.00693 -0.0400 0.5372 1.0000
5.000 0.7438 0.01471 0.00730 -0.0382 0.4798 1.0000
5.250 0.7638 0.01537 0.00775 -0.0366 0.4218 1.0000
5.500 0.7831 0.01615 0.00828 -0.0349 0.3642 1.0000
5.750 0.8022 0.01704 0.00894 -0.0334 0.3075 1.0000
6.000 0.8207 0.01806 0.00984 -0.0319 0.2523 1.0000
6.250 0.8386 0.01924 0.01077 -0.0304 0.1995 1.0000
6.500 0.8555 0.02061 0.01186 -0.0289 0.1498 1.0000
6.750 0.8726 0.02234 0.01337 -0.0273 0.1110 1.0000
7.000 0.8906 0.02416 0.01504 -0.0258 0.0848 1.0000
7.250 0.9122 0.02665 0.01750 -0.0245 0.0706 1.0000
7.500 0.9335 0.02911 0.02003 -0.0234 0.0586 1.0000
7.750 0.9545 0.03124 0.02250 -0.0218 0.0495 1.0000
8.000 0.9716 0.03393 0.02553 -0.0202 0.0404 1.0000
8.250 0.9884 0.03730 0.02908 -0.0189 0.0364 1.0000
8.500 0.9984 0.04313 0.03536 -0.0172 0.0352 1.0000
8.750 1.0057 0.04634 0.03918 -0.0147 0.0346 1.0000
9.000 1.0085 0.04998 0.04337 -0.0123 0.0339 1.0000
9.250 1.0063 0.05389 0.04775 -0.0100 0.0333 1.0000
9.500 0.9991 0.05791 0.05218 -0.0078 0.0330 1.0000
9.750 0.9872 0.06197 0.05654 -0.0058 0.0330 1.0000
10.000 0.9698 0.06550 0.06030 -0.0037 0.0329 1.0000
10.250 0.9517 0.06971 0.06466 -0.0029 0.0334 1.0000
10.500 0.9331 0.07429 0.06939 -0.0037 0.0338 1.0000
10.750 0.9201 0.07984 0.07497 -0.0053 0.0347 1.0000
11.000 0.9107 0.08538 0.08061 -0.0072 0.0355 1.0000
11.250 0.7609 0.09790 0.09372 -0.0182 0.0443 1.0000
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Polar data table (+)
Polar graphs
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