MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 500,000 Max Cl/Cd: 95.05 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh70-il-500000.txt Download as CSV file: xf-mh70-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 70 11.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3766 0.09219 0.09000 -0.0253 1.0000 0.0174
-9.000 -0.3844 0.08489 0.08275 -0.0307 1.0000 0.0183
-8.750 -0.3884 0.07907 0.07697 -0.0346 1.0000 0.0184
-7.750 -0.3959 0.04970 0.04741 -0.0644 0.9477 0.0189
-7.500 -0.3836 0.04722 0.04481 -0.0659 0.9229 0.0191
-7.250 -0.3778 0.04424 0.04163 -0.0660 0.9024 0.0194
-7.000 -0.3699 0.04132 0.03850 -0.0658 0.8869 0.0199
-6.750 -0.3601 0.03806 0.03498 -0.0656 0.8741 0.0206
-6.500 -0.3709 0.02412 0.01923 -0.0623 0.8618 0.0119
-6.250 -0.3523 0.02105 0.01593 -0.0614 0.8525 0.0113
-6.000 -0.3306 0.01882 0.01331 -0.0604 0.8440 0.0112
-5.750 -0.3069 0.01723 0.01137 -0.0595 0.8357 0.0114
-5.500 -0.2818 0.01606 0.00996 -0.0588 0.8277 0.0116
-5.250 -0.2567 0.01499 0.00868 -0.0581 0.8200 0.0119
-5.000 -0.2320 0.01391 0.00754 -0.0575 0.8123 0.0124
-4.750 -0.2062 0.01326 0.00681 -0.0570 0.8047 0.0129
-4.500 -0.1796 0.01286 0.00634 -0.0567 0.7974 0.0140
-4.250 -0.1528 0.01246 0.00584 -0.0563 0.7898 0.0148
-4.000 -0.1275 0.01167 0.00501 -0.0557 0.7829 0.0158
-3.750 -0.1008 0.01120 0.00449 -0.0554 0.7752 0.0173
-3.500 -0.0742 0.01072 0.00392 -0.0549 0.7685 0.0194
-3.250 -0.0470 0.01026 0.00345 -0.0546 0.7606 0.0258
-3.000 -0.0207 0.00969 0.00297 -0.0542 0.7539 0.0563
-2.750 0.0054 0.00908 0.00272 -0.0540 0.7460 0.1378
-2.500 0.0318 0.00869 0.00255 -0.0538 0.7388 0.2122
-2.250 0.0586 0.00834 0.00243 -0.0537 0.7309 0.2839
-2.000 0.0853 0.00805 0.00232 -0.0534 0.7234 0.3559
-1.750 0.1123 0.00778 0.00224 -0.0532 0.7153 0.4210
-1.500 0.1386 0.00752 0.00216 -0.0529 0.7075 0.4967
-1.250 0.1644 0.00718 0.00212 -0.0524 0.6991 0.5909
-1.000 0.1896 0.00691 0.00208 -0.0516 0.6911 0.6784
-0.750 0.2141 0.00663 0.00209 -0.0506 0.6821 0.7670
-0.500 0.2376 0.00647 0.00209 -0.0491 0.6738 0.8450
-0.250 0.2627 0.00637 0.00210 -0.0479 0.6642 0.9069
0.000 0.2957 0.00637 0.00208 -0.0485 0.6547 0.9484
0.250 0.3351 0.00641 0.00202 -0.0507 0.6442 0.9727
0.500 0.3784 0.00644 0.00198 -0.0538 0.6325 0.9867
0.750 0.4221 0.00647 0.00192 -0.0571 0.6204 0.9970
1.000 0.4534 0.00652 0.00189 -0.0578 0.6087 1.0000
1.500 0.5027 0.00667 0.00189 -0.0564 0.5842 1.0000
1.750 0.5277 0.00676 0.00190 -0.0558 0.5709 1.0000
2.000 0.5528 0.00686 0.00194 -0.0552 0.5572 1.0000
2.250 0.5780 0.00698 0.00198 -0.0546 0.5433 1.0000
2.500 0.6033 0.00710 0.00203 -0.0540 0.5286 1.0000
2.750 0.6287 0.00724 0.00210 -0.0535 0.5135 1.0000
3.000 0.6543 0.00740 0.00218 -0.0530 0.4980 1.0000
3.250 0.6800 0.00756 0.00227 -0.0526 0.4821 1.0000
3.500 0.7057 0.00773 0.00238 -0.0521 0.4661 1.0000
3.750 0.7314 0.00792 0.00249 -0.0517 0.4494 1.0000
4.000 0.7572 0.00812 0.00263 -0.0514 0.4332 1.0000
4.250 0.7829 0.00833 0.00278 -0.0510 0.4162 1.0000
4.500 0.8085 0.00856 0.00293 -0.0506 0.3992 1.0000
4.750 0.8340 0.00881 0.00311 -0.0502 0.3822 1.0000
5.000 0.8594 0.00906 0.00330 -0.0498 0.3651 1.0000
5.250 0.8849 0.00931 0.00349 -0.0495 0.3487 1.0000
5.500 0.9103 0.00958 0.00371 -0.0491 0.3321 1.0000
5.750 0.9354 0.00987 0.00394 -0.0487 0.3155 1.0000
6.000 0.9604 0.01016 0.00418 -0.0483 0.2999 1.0000
6.250 0.9853 0.01047 0.00444 -0.0479 0.2844 1.0000
6.500 1.0100 0.01079 0.00472 -0.0475 0.2699 1.0000
6.750 1.0344 0.01113 0.00501 -0.0471 0.2559 1.0000
7.000 1.0587 0.01148 0.00532 -0.0466 0.2425 1.0000
7.250 1.0825 0.01185 0.00564 -0.0461 0.2296 1.0000
7.500 1.1065 0.01221 0.00597 -0.0456 0.2172 1.0000
7.750 1.1305 0.01256 0.00632 -0.0451 0.2058 1.0000
8.000 1.1539 0.01294 0.00668 -0.0446 0.1949 1.0000
8.250 1.1767 0.01336 0.00708 -0.0440 0.1847 1.0000
8.500 1.1993 0.01378 0.00747 -0.0433 0.1745 1.0000
8.750 1.2222 0.01416 0.00788 -0.0427 0.1651 1.0000
9.000 1.2438 0.01463 0.00833 -0.0420 0.1561 1.0000
9.250 1.2652 0.01509 0.00878 -0.0412 0.1472 1.0000
9.500 1.2866 0.01553 0.00925 -0.0404 0.1392 1.0000
9.750 1.3057 0.01611 0.00980 -0.0393 0.1309 1.0000
10.000 1.3267 0.01653 0.01026 -0.0385 0.1234 1.0000
10.250 1.3448 0.01711 0.01085 -0.0373 0.1161 1.0000
10.500 1.3630 0.01765 0.01140 -0.0361 0.1088 1.0000
10.750 1.3798 0.01824 0.01202 -0.0348 0.1022 1.0000
11.000 1.3935 0.01886 0.01265 -0.0329 0.0960 1.0000
11.250 1.4056 0.01952 0.01334 -0.0309 0.0904 1.0000
11.500 1.4168 0.02025 0.01409 -0.0289 0.0846 1.0000
11.750 1.4271 0.02108 0.01496 -0.0269 0.0793 1.0000
12.000 1.4374 0.02196 0.01586 -0.0252 0.0739 1.0000
12.250 1.4455 0.02303 0.01697 -0.0234 0.0690 1.0000
12.500 1.4554 0.02406 0.01804 -0.0219 0.0644 1.0000
12.750 1.4601 0.02550 0.01950 -0.0203 0.0600 1.0000
13.000 1.4701 0.02663 0.02072 -0.0191 0.0562 1.0000
13.250 1.4742 0.02828 0.02239 -0.0178 0.0523 1.0000
13.500 1.4803 0.02984 0.02403 -0.0168 0.0492 1.0000
13.750 1.4854 0.03155 0.02579 -0.0158 0.0460 1.0000
14.000 1.4838 0.03394 0.02822 -0.0149 0.0431 1.0000
14.250 1.4900 0.03570 0.03009 -0.0143 0.0408 1.0000
14.500 1.4922 0.03791 0.03237 -0.0138 0.0384 1.0000
14.750 1.4882 0.04083 0.03534 -0.0135 0.0363 1.0000
15.000 1.4876 0.04354 0.03816 -0.0134 0.0345 1.0000
15.250 1.4882 0.04620 0.04093 -0.0134 0.0328 1.0000
15.500 1.4843 0.04947 0.04428 -0.0138 0.0311 1.0000
15.750 1.4746 0.05362 0.04850 -0.0145 0.0298 1.0000
16.000 1.4701 0.05731 0.05232 -0.0153 0.0286 1.0000
16.250 1.4677 0.06088 0.05602 -0.0163 0.0273 1.0000
16.500 1.4615 0.06509 0.06033 -0.0176 0.0262 1.0000
16.750 1.4522 0.06990 0.06521 -0.0193 0.0251 1.0000
17.000 1.4370 0.07580 0.07121 -0.0216 0.0242 1.0000
17.250 1.4276 0.08093 0.07647 -0.0236 0.0236 1.0000
17.500 1.4201 0.08592 0.08160 -0.0257 0.0227 1.0000
17.750 1.4112 0.09126 0.08706 -0.0281 0.0220 1.0000
18.000 1.4002 0.09707 0.09297 -0.0308 0.0211 1.0000
18.250 1.3862 0.10350 0.09950 -0.0339 0.0206 1.0000
18.500 1.3714 0.11020 0.10629 -0.0373 0.0201 1.0000
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Polar data table (+)
Polar graphs
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