MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 500,000 Max Cl/Cd: 87.91 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh70-il-500000-n5.txt Download as CSV file: xf-mh70-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5376 0.04082 0.03820 -0.0625 0.9116 0.0046
-8.750 -0.5588 0.03324 0.02997 -0.0631 0.8829 0.0046
-8.500 -0.5627 0.02772 0.02374 -0.0621 0.8663 0.0046
-8.250 -0.5518 0.02452 0.02004 -0.0611 0.8539 0.0047
-8.000 -0.5347 0.02239 0.01749 -0.0602 0.8436 0.0048
-7.750 -0.5155 0.02059 0.01534 -0.0593 0.8340 0.0048
-7.500 -0.4947 0.01907 0.01357 -0.0587 0.8250 0.0051
-7.250 -0.4716 0.01811 0.01243 -0.0581 0.8166 0.0052
-7.000 -0.4472 0.01733 0.01150 -0.0577 0.8081 0.0054
-6.750 -0.4227 0.01656 0.01056 -0.0572 0.8003 0.0056
-6.500 -0.3977 0.01580 0.00966 -0.0568 0.7923 0.0057
-6.250 -0.3726 0.01510 0.00879 -0.0563 0.7850 0.0060
-6.000 -0.3470 0.01444 0.00802 -0.0559 0.7773 0.0062
-5.500 -0.2951 0.01330 0.00663 -0.0551 0.7628 0.0066
-5.250 -0.2688 0.01284 0.00607 -0.0548 0.7556 0.0069
-5.000 -0.2423 0.01241 0.00559 -0.0545 0.7487 0.0075
-4.750 -0.2155 0.01206 0.00518 -0.0543 0.7414 0.0081
-4.500 -0.1885 0.01171 0.00474 -0.0540 0.7346 0.0087
-4.250 -0.1614 0.01134 0.00429 -0.0538 0.7272 0.0092
-4.000 -0.1344 0.01098 0.00386 -0.0535 0.7205 0.0100
-3.750 -0.1068 0.01069 0.00351 -0.0533 0.7131 0.0115
-3.500 -0.0795 0.01042 0.00319 -0.0531 0.7061 0.0135
-3.250 -0.0518 0.01017 0.00292 -0.0529 0.6984 0.0182
-3.000 -0.0245 0.00993 0.00268 -0.0527 0.6911 0.0280
-2.750 0.0029 0.00964 0.00247 -0.0526 0.6833 0.0487
-2.500 0.0299 0.00932 0.00227 -0.0524 0.6754 0.0872
-2.250 0.0570 0.00898 0.00211 -0.0523 0.6672 0.1412
-2.000 0.0840 0.00871 0.00198 -0.0522 0.6588 0.1967
-1.750 0.1115 0.00849 0.00188 -0.0521 0.6498 0.2413
-1.500 0.1388 0.00829 0.00180 -0.0520 0.6410 0.2952
-1.250 0.1659 0.00805 0.00173 -0.0519 0.6313 0.3601
-1.000 0.1932 0.00789 0.00168 -0.0517 0.6218 0.4096
-0.750 0.2204 0.00775 0.00163 -0.0515 0.6115 0.4606
-0.500 0.2475 0.00760 0.00160 -0.0513 0.6004 0.5135
-0.250 0.2743 0.00745 0.00158 -0.0511 0.5891 0.5721
0.000 0.3007 0.00730 0.00158 -0.0507 0.5775 0.6356
0.250 0.3265 0.00716 0.00159 -0.0501 0.5649 0.7030
0.500 0.3516 0.00703 0.00162 -0.0493 0.5519 0.7702
0.750 0.3762 0.00693 0.00167 -0.0483 0.5388 0.8333
1.000 0.4009 0.00691 0.00172 -0.0473 0.5247 0.8894
1.250 0.4304 0.00695 0.00175 -0.0473 0.5103 0.9328
1.500 0.4663 0.00705 0.00178 -0.0489 0.4948 0.9617
1.750 0.5033 0.00718 0.00181 -0.0508 0.4783 0.9814
2.000 0.5403 0.00731 0.00186 -0.0528 0.4613 0.9952
2.250 0.5705 0.00747 0.00192 -0.0534 0.4458 1.0000
2.500 0.5957 0.00763 0.00199 -0.0528 0.4306 1.0000
2.750 0.6211 0.00780 0.00208 -0.0523 0.4154 1.0000
3.000 0.6466 0.00798 0.00219 -0.0519 0.4000 1.0000
3.250 0.6722 0.00817 0.00230 -0.0515 0.3845 1.0000
3.500 0.6979 0.00837 0.00242 -0.0511 0.3691 1.0000
3.750 0.7236 0.00858 0.00256 -0.0507 0.3530 1.0000
4.000 0.7494 0.00879 0.00271 -0.0503 0.3387 1.0000
4.250 0.7750 0.00902 0.00287 -0.0500 0.3235 1.0000
4.500 0.8007 0.00926 0.00304 -0.0497 0.3086 1.0000
4.750 0.8263 0.00950 0.00323 -0.0493 0.2945 1.0000
5.000 0.8518 0.00975 0.00342 -0.0490 0.2802 1.0000
5.250 0.8774 0.01000 0.00363 -0.0486 0.2679 1.0000
5.500 0.9028 0.01027 0.00385 -0.0483 0.2554 1.0000
5.750 0.9279 0.01056 0.00408 -0.0479 0.2425 1.0000
6.250 0.9782 0.01113 0.00458 -0.0472 0.2192 1.0000
6.500 1.0031 0.01142 0.00485 -0.0468 0.2087 1.0000
6.750 1.0277 0.01174 0.00513 -0.0464 0.1986 1.0000
7.000 1.0522 0.01206 0.00543 -0.0460 0.1882 1.0000
7.250 1.0767 0.01237 0.00574 -0.0456 0.1788 1.0000
7.500 1.1006 0.01273 0.00606 -0.0451 0.1696 1.0000
7.750 1.1243 0.01309 0.00641 -0.0446 0.1603 1.0000
8.000 1.1481 0.01343 0.00676 -0.0441 0.1520 1.0000
8.250 1.1710 0.01384 0.00714 -0.0435 0.1439 1.0000
8.500 1.1941 0.01420 0.00751 -0.0429 0.1360 1.0000
8.750 1.2165 0.01462 0.00793 -0.0423 0.1283 1.0000
9.000 1.2384 0.01506 0.00836 -0.0416 0.1205 1.0000
9.250 1.2601 0.01548 0.00880 -0.0408 0.1138 1.0000
9.500 1.2807 0.01598 0.00929 -0.0400 0.1066 1.0000
9.750 1.3015 0.01642 0.00977 -0.0391 0.1005 1.0000
10.000 1.3203 0.01699 0.01031 -0.0380 0.0934 1.0000
10.250 1.3398 0.01747 0.01083 -0.0370 0.0878 1.0000
10.500 1.3565 0.01809 0.01145 -0.0357 0.0813 1.0000
10.750 1.3735 0.01863 0.01203 -0.0343 0.0760 1.0000
11.000 1.3859 0.01929 0.01269 -0.0323 0.0709 1.0000
11.250 1.3991 0.01990 0.01335 -0.0304 0.0667 1.0000
11.500 1.4099 0.02067 0.01414 -0.0284 0.0620 1.0000
11.750 1.4209 0.02147 0.01499 -0.0266 0.0578 1.0000
12.000 1.4308 0.02239 0.01594 -0.0249 0.0534 1.0000
12.250 1.4400 0.02341 0.01700 -0.0233 0.0497 1.0000
12.500 1.4492 0.02449 0.01812 -0.0218 0.0460 1.0000
12.750 1.4563 0.02578 0.01944 -0.0204 0.0427 1.0000
13.000 1.4651 0.02700 0.02073 -0.0192 0.0399 1.0000
13.250 1.4714 0.02847 0.02226 -0.0180 0.0371 1.0000
13.500 1.4775 0.03004 0.02389 -0.0170 0.0348 1.0000
13.750 1.4835 0.03167 0.02559 -0.0161 0.0325 1.0000
14.000 1.4874 0.03356 0.02754 -0.0153 0.0304 1.0000
14.250 1.4907 0.03556 0.02962 -0.0146 0.0287 1.0000
14.500 1.4944 0.03762 0.03177 -0.0142 0.0269 1.0000
14.750 1.4956 0.03999 0.03421 -0.0138 0.0254 1.0000
15.000 1.4944 0.04272 0.03701 -0.0137 0.0239 1.0000
15.250 1.4955 0.04528 0.03969 -0.0137 0.0227 1.0000
15.500 1.4942 0.04821 0.04272 -0.0139 0.0215 1.0000
15.750 1.4908 0.05150 0.04610 -0.0143 0.0204 1.0000
16.000 1.4852 0.05523 0.04992 -0.0151 0.0195 1.0000
16.250 1.4823 0.05877 0.05358 -0.0159 0.0186 1.0000
16.500 1.4771 0.06277 0.05769 -0.0171 0.0178 1.0000
16.750 1.4693 0.06725 0.06227 -0.0186 0.0166 1.0000
17.000 1.4598 0.07218 0.06731 -0.0204 0.0160 1.0000
17.250 1.4502 0.07728 0.07253 -0.0224 0.0156 1.0000
17.500 1.4410 0.08246 0.07784 -0.0246 0.0149 1.0000
17.750 1.4307 0.08794 0.08345 -0.0270 0.0144 1.0000
18.000 1.4178 0.09401 0.08963 -0.0298 0.0137 1.0000
18.250 1.4042 0.10032 0.09607 -0.0328 0.0135 1.0000
18.500 1.3893 0.10702 0.10289 -0.0361 0.0131 1.0000
18.750 1.3736 0.11403 0.11002 -0.0397 0.0127 1.0000
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Polar data table (+)
Polar graphs
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