MH 30 7.84% (mh30-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 30 7.84% (mh30-il) Reynolds number: 100,000 Max Cl/Cd: 48.5 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh30-il-100000-n5.txt Download as CSV file: xf-mh30-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4912 0.11182 0.10670 -0.0100 1.0000 0.0224
-9.750 -0.4879 0.10791 0.10282 -0.0114 1.0000 0.0210
-9.500 -0.4861 0.10370 0.09866 -0.0131 1.0000 0.0200
-8.500 -0.4842 0.08481 0.07996 -0.0236 1.0000 0.0156
-8.250 -0.4864 0.08046 0.07568 -0.0256 1.0000 0.0153
-8.000 -0.4896 0.07633 0.07162 -0.0279 1.0000 0.0151
-7.750 -0.4945 0.07150 0.06686 -0.0315 1.0000 0.0149
-7.500 -0.4954 0.06622 0.06157 -0.0354 1.0000 0.0147
-7.250 -0.4953 0.06114 0.05644 -0.0382 1.0000 0.0145
-7.000 -0.4940 0.05638 0.05156 -0.0400 1.0000 0.0143
-6.750 -0.4919 0.05161 0.04663 -0.0409 1.0000 0.0141
-6.500 -0.4880 0.04722 0.04202 -0.0410 1.0000 0.0139
-6.250 -0.4819 0.04313 0.03764 -0.0405 1.0000 0.0137
-6.000 -0.4735 0.03920 0.03334 -0.0396 1.0000 0.0135
-5.750 -0.4626 0.03564 0.02937 -0.0383 1.0000 0.0134
-5.500 -0.4494 0.03238 0.02565 -0.0368 1.0000 0.0133
-5.250 -0.4337 0.02948 0.02227 -0.0353 1.0000 0.0133
-5.000 -0.4160 0.02695 0.01919 -0.0337 1.0000 0.0134
-4.750 -0.3966 0.02469 0.01650 -0.0322 1.0000 0.0137
-4.500 -0.3762 0.02281 0.01427 -0.0307 1.0000 0.0143
-4.250 -0.3552 0.02159 0.01278 -0.0293 1.0000 0.0155
-4.000 -0.3355 0.02007 0.01118 -0.0282 1.0000 0.0192
-3.750 -0.3145 0.01898 0.00995 -0.0270 1.0000 0.0226
-3.500 -0.2933 0.01776 0.00854 -0.0256 1.0000 0.0263
-3.250 -0.2720 0.01677 0.00755 -0.0246 1.0000 0.0419
-3.000 -0.2410 0.01554 0.00654 -0.0255 0.9962 0.0920
-2.750 -0.2086 0.01452 0.00607 -0.0271 0.9911 0.2150
-2.500 -0.1769 0.01366 0.00579 -0.0285 0.9855 0.3765
-2.250 -0.1446 0.01304 0.00568 -0.0296 0.9803 0.5278
-2.000 -0.1156 0.01258 0.00563 -0.0294 0.9737 0.6649
-1.750 -0.0826 0.01229 0.00563 -0.0295 0.9689 0.7956
-1.500 -0.0314 0.01215 0.00552 -0.0334 0.9668 0.9239
-1.250 0.0252 0.01210 0.00522 -0.0394 0.9637 1.0000
-1.000 0.0653 0.01213 0.00506 -0.0421 0.9566 1.0000
-0.750 0.1022 0.01214 0.00493 -0.0441 0.9479 1.0000
-0.500 0.1424 0.01214 0.00476 -0.0467 0.9405 1.0000
-0.250 0.1768 0.01214 0.00467 -0.0481 0.9304 1.0000
0.000 0.2098 0.01214 0.00459 -0.0491 0.9196 1.0000
0.250 0.2427 0.01213 0.00452 -0.0500 0.9086 1.0000
0.500 0.2747 0.01210 0.00446 -0.0507 0.8967 1.0000
0.750 0.3049 0.01208 0.00440 -0.0509 0.8833 1.0000
1.000 0.3334 0.01205 0.00434 -0.0507 0.8683 1.0000
1.250 0.3612 0.01202 0.00430 -0.0503 0.8521 1.0000
1.500 0.3888 0.01199 0.00425 -0.0498 0.8353 1.0000
1.750 0.4144 0.01199 0.00427 -0.0489 0.8157 1.0000
2.000 0.4407 0.01198 0.00425 -0.0482 0.7953 1.0000
2.250 0.4660 0.01200 0.00426 -0.0472 0.7718 1.0000
2.500 0.4916 0.01203 0.00428 -0.0463 0.7460 1.0000
2.750 0.5170 0.01209 0.00437 -0.0453 0.7171 1.0000
3.000 0.5421 0.01219 0.00442 -0.0443 0.6847 1.0000
3.250 0.5668 0.01235 0.00451 -0.0432 0.6487 1.0000
3.500 0.5911 0.01258 0.00464 -0.0421 0.6097 1.0000
3.750 0.6149 0.01288 0.00483 -0.0410 0.5688 1.0000
4.000 0.6382 0.01323 0.00513 -0.0399 0.5263 1.0000
4.250 0.6612 0.01364 0.00543 -0.0388 0.4821 1.0000
4.500 0.6838 0.01410 0.00577 -0.0377 0.4368 1.0000
4.750 0.7061 0.01463 0.00616 -0.0367 0.3913 1.0000
5.000 0.7283 0.01519 0.00661 -0.0357 0.3461 1.0000
5.250 0.7502 0.01581 0.00711 -0.0348 0.3019 1.0000
5.500 0.7718 0.01648 0.00767 -0.0338 0.2588 1.0000
5.750 0.7934 0.01720 0.00829 -0.0329 0.2184 1.0000
6.000 0.8147 0.01799 0.00909 -0.0320 0.1789 1.0000
6.250 0.8356 0.01886 0.00985 -0.0312 0.1406 1.0000
6.500 0.8559 0.01985 0.01072 -0.0302 0.1049 1.0000
6.750 0.8756 0.02096 0.01177 -0.0292 0.0779 1.0000
7.000 0.8944 0.02220 0.01292 -0.0280 0.0562 1.0000
7.250 0.9122 0.02363 0.01441 -0.0266 0.0446 1.0000
7.500 0.9293 0.02516 0.01609 -0.0250 0.0371 1.0000
7.750 0.9466 0.02671 0.01780 -0.0235 0.0296 1.0000
8.000 0.9598 0.02895 0.02008 -0.0218 0.0241 1.0000
8.250 0.9786 0.03036 0.02181 -0.0205 0.0188 1.0000
8.500 0.9924 0.03238 0.02398 -0.0190 0.0158 1.0000
8.750 1.0032 0.03580 0.02766 -0.0171 0.0144 1.0000
9.000 1.0167 0.03838 0.03078 -0.0154 0.0133 1.0000
9.250 1.0268 0.04102 0.03383 -0.0136 0.0119 1.0000
9.500 1.0333 0.04351 0.03668 -0.0118 0.0106 1.0000
9.750 1.0363 0.04596 0.03942 -0.0099 0.0097 1.0000
10.000 1.0348 0.04833 0.04202 -0.0079 0.0090 1.0000
10.250 1.0264 0.05133 0.04529 -0.0054 0.0088 1.0000
10.500 1.0152 0.05468 0.04889 -0.0037 0.0087 1.0000
10.750 1.0011 0.05867 0.05317 -0.0031 0.0088 1.0000
11.000 0.9848 0.06330 0.05804 -0.0038 0.0088 1.0000
11.250 0.9668 0.06886 0.06382 -0.0062 0.0089 1.0000
11.500 0.9462 0.07594 0.07110 -0.0107 0.0090 1.0000
11.750 0.9235 0.08500 0.08036 -0.0172 0.0093 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 30 7.84% (mh30-il)