MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.84 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh70-il-1000000-n5.txt Download as CSV file: xf-mh70-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4136 0.11259 0.11090 -0.0144 1.0000 0.0041
-10.500 -0.7039 0.03552 0.03320 -0.0642 0.9182 0.0028
-10.250 -0.7242 0.02986 0.02695 -0.0630 0.8831 0.0029
-9.750 -0.7100 0.02434 0.02069 -0.0609 0.8522 0.0029
-9.500 -0.6946 0.02242 0.01847 -0.0600 0.8410 0.0029
-9.250 -0.6764 0.02089 0.01669 -0.0593 0.8309 0.0029
-9.000 -0.6560 0.01963 0.01521 -0.0586 0.8210 0.0030
-8.750 -0.6345 0.01848 0.01385 -0.0580 0.8125 0.0030
-8.500 -0.6113 0.01765 0.01286 -0.0575 0.8036 0.0030
-8.250 -0.5880 0.01671 0.01175 -0.0570 0.7959 0.0031
-8.000 -0.5671 0.01520 0.00996 -0.0562 0.7874 0.0033
-7.750 -0.5425 0.01446 0.00910 -0.0558 0.7800 0.0034
-7.500 -0.5168 0.01396 0.00851 -0.0555 0.7721 0.0035
-7.250 -0.4909 0.01346 0.00791 -0.0552 0.7653 0.0036
-7.000 -0.4647 0.01303 0.00739 -0.0549 0.7578 0.0038
-6.750 -0.4383 0.01260 0.00688 -0.0546 0.7511 0.0039
-6.500 -0.4118 0.01217 0.00637 -0.0544 0.7438 0.0041
-6.250 -0.3852 0.01177 0.00588 -0.0541 0.7371 0.0042
-6.000 -0.3582 0.01140 0.00544 -0.0539 0.7302 0.0044
-5.750 -0.3313 0.01107 0.00503 -0.0536 0.7232 0.0045
-5.500 -0.3041 0.01073 0.00462 -0.0534 0.7166 0.0046
-5.250 -0.2767 0.01045 0.00428 -0.0532 0.7095 0.0047
-5.000 -0.2494 0.01015 0.00392 -0.0531 0.7030 0.0049
-4.750 -0.2220 0.00983 0.00354 -0.0529 0.6959 0.0051
-4.500 -0.1944 0.00959 0.00324 -0.0527 0.6892 0.0054
-4.250 -0.1666 0.00936 0.00298 -0.0526 0.6819 0.0058
-4.000 -0.1388 0.00919 0.00276 -0.0525 0.6746 0.0063
-3.750 -0.1108 0.00900 0.00253 -0.0524 0.6673 0.0071
-3.250 -0.0550 0.00865 0.00213 -0.0521 0.6515 0.0106
-3.000 -0.0272 0.00850 0.00195 -0.0520 0.6431 0.0149
-2.750 0.0009 0.00834 0.00180 -0.0519 0.6344 0.0221
-2.500 0.0288 0.00820 0.00167 -0.0519 0.6258 0.0319
-2.250 0.0565 0.00799 0.00153 -0.0518 0.6162 0.0564
-2.000 0.0840 0.00773 0.00140 -0.0517 0.6068 0.0991
-1.750 0.1114 0.00750 0.00130 -0.0516 0.5967 0.1485
-1.500 0.1390 0.00732 0.00122 -0.0516 0.5857 0.1930
-1.250 0.1669 0.00720 0.00117 -0.0515 0.5745 0.2280
-1.000 0.1943 0.00704 0.00112 -0.0515 0.5624 0.2820
-0.750 0.2219 0.00692 0.00109 -0.0514 0.5499 0.3291
-0.500 0.2496 0.00684 0.00107 -0.0513 0.5364 0.3691
-0.250 0.2773 0.00677 0.00106 -0.0513 0.5227 0.4105
0.000 0.3049 0.00671 0.00107 -0.0512 0.5087 0.4525
0.250 0.3324 0.00666 0.00108 -0.0511 0.4944 0.4965
0.500 0.3598 0.00661 0.00110 -0.0510 0.4805 0.5426
0.750 0.3870 0.00656 0.00113 -0.0509 0.4668 0.5938
1.000 0.4140 0.00650 0.00118 -0.0507 0.4524 0.6504
1.250 0.4406 0.00645 0.00123 -0.0504 0.4384 0.7082
1.500 0.4667 0.00640 0.00130 -0.0499 0.4236 0.7694
1.750 0.4921 0.00636 0.00138 -0.0493 0.4094 0.8277
2.000 0.5169 0.00636 0.00147 -0.0485 0.3951 0.8796
2.250 0.5417 0.00640 0.00155 -0.0476 0.3807 0.9240
2.500 0.5715 0.00651 0.00163 -0.0479 0.3652 0.9582
2.750 0.6075 0.00666 0.00171 -0.0497 0.3490 0.9790
3.000 0.6431 0.00683 0.00181 -0.0514 0.3327 0.9925
3.250 0.6754 0.00701 0.00190 -0.0525 0.3180 1.0000
3.500 0.7012 0.00719 0.00201 -0.0521 0.3039 1.0000
4.000 0.7531 0.00757 0.00226 -0.0514 0.2766 1.0000
4.250 0.7792 0.00777 0.00239 -0.0511 0.2633 1.0000
4.500 0.8055 0.00795 0.00253 -0.0508 0.2525 1.0000
4.750 0.8317 0.00816 0.00269 -0.0506 0.2411 1.0000
5.000 0.8576 0.00839 0.00285 -0.0503 0.2289 1.0000
5.250 0.8838 0.00859 0.00301 -0.0500 0.2184 1.0000
5.500 0.9098 0.00881 0.00319 -0.0498 0.2075 1.0000
5.750 0.9358 0.00904 0.00338 -0.0495 0.1977 1.0000
6.000 0.9616 0.00928 0.00357 -0.0492 0.1883 1.0000
6.250 0.9875 0.00951 0.00378 -0.0490 0.1789 1.0000
6.500 1.0131 0.00977 0.00400 -0.0487 0.1703 1.0000
6.750 1.0385 0.01004 0.00422 -0.0484 0.1606 1.0000
7.000 1.0641 0.01028 0.00446 -0.0481 0.1530 1.0000
7.250 1.0889 0.01059 0.00472 -0.0477 0.1440 1.0000
7.500 1.1143 0.01084 0.00496 -0.0474 0.1372 1.0000
7.750 1.1389 0.01115 0.00524 -0.0470 0.1295 1.0000
8.000 1.1634 0.01146 0.00553 -0.0466 0.1216 1.0000
8.250 1.1878 0.01177 0.00583 -0.0462 0.1147 1.0000
8.500 1.2116 0.01211 0.00615 -0.0458 0.1076 1.0000
8.750 1.2356 0.01244 0.00647 -0.0453 0.1013 1.0000
9.000 1.2586 0.01283 0.00683 -0.0447 0.0943 1.0000
9.250 1.2819 0.01317 0.00718 -0.0442 0.0886 1.0000
9.500 1.3039 0.01361 0.00759 -0.0435 0.0814 1.0000
9.750 1.3262 0.01400 0.00798 -0.0428 0.0757 1.0000
10.000 1.3474 0.01446 0.00841 -0.0420 0.0698 1.0000
10.250 1.3688 0.01486 0.00884 -0.0412 0.0655 1.0000
10.500 1.3885 0.01537 0.00933 -0.0402 0.0598 1.0000
10.750 1.4081 0.01585 0.00982 -0.0392 0.0550 1.0000
11.000 1.4259 0.01642 0.01037 -0.0380 0.0495 1.0000
11.250 1.4430 0.01698 0.01094 -0.0367 0.0453 1.0000
11.500 1.4579 0.01754 0.01152 -0.0350 0.0415 1.0000
11.750 1.4701 0.01812 0.01211 -0.0328 0.0383 1.0000
12.000 1.4804 0.01881 0.01282 -0.0305 0.0351 1.0000
12.250 1.4911 0.01952 0.01355 -0.0285 0.0320 1.0000
12.500 1.5001 0.02039 0.01444 -0.0264 0.0293 1.0000
12.750 1.5091 0.02131 0.01538 -0.0246 0.0262 1.0000
13.000 1.5165 0.02240 0.01649 -0.0228 0.0231 1.0000
13.250 1.5259 0.02343 0.01757 -0.0213 0.0216 1.0000
13.500 1.5325 0.02472 0.01889 -0.0198 0.0195 1.0000
13.750 1.5385 0.02612 0.02032 -0.0185 0.0169 1.0000
14.000 1.5458 0.02749 0.02175 -0.0174 0.0161 1.0000
14.250 1.5514 0.02906 0.02336 -0.0163 0.0143 1.0000
14.500 1.5537 0.03098 0.02532 -0.0153 0.0125 1.0000
14.750 1.5582 0.03279 0.02721 -0.0145 0.0112 1.0000
15.000 1.5595 0.03497 0.02944 -0.0139 0.0099 1.0000
15.250 1.5624 0.03709 0.03162 -0.0134 0.0092 1.0000
15.500 1.5649 0.03931 0.03393 -0.0131 0.0088 1.0000
15.750 1.5646 0.04191 0.03660 -0.0129 0.0080 1.0000
16.000 1.5632 0.04473 0.03950 -0.0130 0.0074 1.0000
16.250 1.5624 0.04758 0.04244 -0.0132 0.0071 1.0000
16.500 1.5597 0.05081 0.04575 -0.0137 0.0065 1.0000
16.750 1.5552 0.05439 0.04942 -0.0144 0.0061 1.0000
17.000 1.5502 0.05819 0.05333 -0.0153 0.0059 1.0000
17.250 1.5445 0.06224 0.05748 -0.0165 0.0057 1.0000
17.500 1.5358 0.06685 0.06220 -0.0181 0.0050 1.0000
17.750 1.5296 0.07126 0.06672 -0.0197 0.0051 1.0000
18.000 1.5191 0.07644 0.07201 -0.0218 0.0049 1.0000
18.250 1.5075 0.08196 0.07765 -0.0241 0.0047 1.0000
18.500 1.4947 0.08782 0.08362 -0.0267 0.0045 1.0000
18.750 1.4795 0.09426 0.09019 -0.0297 0.0043 1.0000
19.000 1.4641 0.10086 0.09690 -0.0329 0.0042 1.0000
19.250 1.4483 0.10772 0.10389 -0.0363 0.0042 1.0000
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Polar data table (+)
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