MH 78 14.47% (mh78-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 78 14.47% (mh78-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.16 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh78-il-1000000-n5.txt Download as CSV file: xf-mh78-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 78 14.47%
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
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0895 0.08194 0.07908 0.0131 1.0000 0.0066
-15.500 -1.1359 0.06780 0.06468 0.0032 1.0000 0.0066
-15.250 -1.1658 0.05741 0.05407 -0.0047 1.0000 0.0066
-15.000 -1.1847 0.05042 0.04690 -0.0095 1.0000 0.0066
-14.750 -1.1955 0.04574 0.04208 -0.0118 1.0000 0.0066
-14.500 -1.2137 0.04107 0.03723 -0.0129 1.0000 0.0066
-14.250 -1.2225 0.03799 0.03402 -0.0124 1.0000 0.0066
-14.000 -1.2276 0.03555 0.03146 -0.0111 1.0000 0.0066
-13.750 -1.2324 0.03335 0.02912 -0.0092 1.0000 0.0066
-13.500 -1.2276 0.03198 0.02768 -0.0073 1.0000 0.0066
-13.250 -1.2287 0.03028 0.02586 -0.0047 1.0000 0.0066
-13.000 -1.2286 0.02874 0.02420 -0.0017 1.0000 0.0066
-12.750 -1.2225 0.02765 0.02303 0.0010 1.0000 0.0066
-12.500 -1.2181 0.02645 0.02172 0.0042 1.0000 0.0067
-12.250 -1.2063 0.02548 0.02068 0.0064 1.0000 0.0067
-12.000 -1.1928 0.02445 0.01956 0.0083 1.0000 0.0068
-11.750 -1.1766 0.02355 0.01859 0.0100 1.0000 0.0068
-11.500 -1.1596 0.02271 0.01760 0.0116 0.9074 0.0068
-11.250 -1.1470 0.02222 0.01680 0.0144 0.8177 0.0069
-11.000 -1.1284 0.02159 0.01598 0.0159 0.7740 0.0069
-10.750 -1.1084 0.02096 0.01520 0.0173 0.7399 0.0070
-10.500 -1.0875 0.02036 0.01445 0.0185 0.7097 0.0070
-10.250 -1.0659 0.01976 0.01373 0.0196 0.6850 0.0071
-10.000 -1.0436 0.01921 0.01305 0.0207 0.6614 0.0071
-9.750 -1.0207 0.01869 0.01243 0.0217 0.6396 0.0072
-9.500 -0.9974 0.01817 0.01181 0.0226 0.6199 0.0072
-9.250 -0.9737 0.01768 0.01122 0.0235 0.6012 0.0073
-9.000 -0.9496 0.01722 0.01067 0.0244 0.5838 0.0073
-8.750 -0.9251 0.01679 0.01014 0.0252 0.5658 0.0074
-8.500 -0.9004 0.01635 0.00962 0.0259 0.5493 0.0075
-8.250 -0.8753 0.01595 0.00914 0.0267 0.5342 0.0076
-8.000 -0.8500 0.01556 0.00867 0.0274 0.5199 0.0078
-7.500 -0.7987 0.01484 0.00780 0.0287 0.4916 0.0080
-7.250 -0.7726 0.01450 0.00740 0.0293 0.4785 0.0081
-6.750 -0.7199 0.01389 0.00665 0.0305 0.4535 0.0084
-6.500 -0.6933 0.01362 0.00632 0.0310 0.4423 0.0085
-6.250 -0.6665 0.01335 0.00600 0.0315 0.4302 0.0086
-6.000 -0.6401 0.01301 0.00560 0.0321 0.4195 0.0089
-5.750 -0.6131 0.01275 0.00529 0.0326 0.4091 0.0091
-5.500 -0.5860 0.01251 0.00501 0.0330 0.4006 0.0093
-5.250 -0.5587 0.01229 0.00475 0.0335 0.3903 0.0096
-5.000 -0.5312 0.01210 0.00452 0.0339 0.3806 0.0099
-4.750 -0.5037 0.01191 0.00429 0.0343 0.3706 0.0102
-4.500 -0.4759 0.01174 0.00408 0.0346 0.3629 0.0106
-4.250 -0.4482 0.01157 0.00387 0.0350 0.3546 0.0109
-4.000 -0.4205 0.01139 0.00366 0.0354 0.3470 0.0116
-3.750 -0.3927 0.01123 0.00348 0.0357 0.3389 0.0124
-3.500 -0.3647 0.01111 0.00331 0.0360 0.3301 0.0132
-3.250 -0.3368 0.01096 0.00315 0.0364 0.3235 0.0145
-3.000 -0.3087 0.01084 0.00301 0.0367 0.3162 0.0162
-2.750 -0.2806 0.01071 0.00287 0.0369 0.3103 0.0189
-2.500 -0.2526 0.01057 0.00275 0.0372 0.3040 0.0235
-2.250 -0.2245 0.01046 0.00263 0.0375 0.2963 0.0299
-2.000 -0.1965 0.01032 0.00252 0.0378 0.2909 0.0393
-1.750 -0.1687 0.01016 0.00240 0.0381 0.2853 0.0552
-1.500 -0.1411 0.00998 0.00230 0.0384 0.2795 0.0789
-1.250 -0.1137 0.00975 0.00220 0.0387 0.2753 0.1139
-1.000 -0.0866 0.00951 0.00211 0.0390 0.2703 0.1595
-0.750 -0.0596 0.00928 0.00204 0.0393 0.2646 0.2094
-0.250 -0.0055 0.00882 0.00193 0.0400 0.2567 0.3194
0.000 0.0199 0.00841 0.00187 0.0406 0.2528 0.4221
0.250 0.0447 0.00801 0.00182 0.0412 0.2485 0.5302
0.500 0.0703 0.00773 0.00179 0.0419 0.2445 0.6114
0.750 0.0960 0.00747 0.00177 0.0425 0.2414 0.6840
1.000 0.1213 0.00725 0.00179 0.0434 0.2382 0.7580
1.250 0.1475 0.00716 0.00185 0.0441 0.2348 0.8118
1.500 0.1752 0.00720 0.00193 0.0445 0.2311 0.8387
1.750 0.2036 0.00725 0.00200 0.0448 0.2282 0.8558
2.000 0.2322 0.00732 0.00206 0.0450 0.2254 0.8686
2.250 0.2606 0.00739 0.00213 0.0452 0.2224 0.8783
2.500 0.2891 0.00749 0.00220 0.0454 0.2195 0.8888
2.750 0.3168 0.00760 0.00231 0.0458 0.2164 0.8995
3.000 0.3448 0.00770 0.00240 0.0461 0.2138 0.9093
3.250 0.3723 0.00780 0.00251 0.0465 0.2118 0.9177
3.500 0.4000 0.00791 0.00260 0.0468 0.2091 0.9254
3.750 0.4272 0.00802 0.00271 0.0473 0.2066 0.9316
4.000 0.4545 0.00814 0.00281 0.0477 0.2040 0.9372
4.250 0.4824 0.00828 0.00291 0.0479 0.2012 0.9410
4.500 0.5109 0.00838 0.00300 0.0480 0.1992 0.9433
4.750 0.5395 0.00847 0.00309 0.0480 0.1972 0.9453
5.000 0.5678 0.00858 0.00319 0.0481 0.1948 0.9474
5.250 0.5961 0.00869 0.00329 0.0481 0.1925 0.9496
5.500 0.6244 0.00883 0.00341 0.0482 0.1901 0.9517
5.750 0.6523 0.00898 0.00353 0.0482 0.1876 0.9542
6.000 0.6803 0.00911 0.00366 0.0483 0.1857 0.9565
6.250 0.7088 0.00922 0.00377 0.0483 0.1840 0.9583
6.500 0.7374 0.00934 0.00390 0.0482 0.1818 0.9600
6.750 0.7658 0.00948 0.00403 0.0481 0.1795 0.9619
7.000 0.7939 0.00964 0.00418 0.0481 0.1773 0.9641
7.250 0.8217 0.00982 0.00435 0.0481 0.1750 0.9666
7.500 0.8492 0.00999 0.00452 0.0482 0.1730 0.9692
7.750 0.8773 0.01012 0.00467 0.0481 0.1716 0.9713
8.000 0.9071 0.01028 0.00484 0.0477 0.1696 0.9727
8.250 0.9367 0.01046 0.00502 0.0472 0.1674 0.9743
8.500 0.9659 0.01066 0.00521 0.0468 0.1652 0.9761
8.750 0.9948 0.01088 0.00543 0.0464 0.1630 0.9782
9.000 1.0233 0.01110 0.00566 0.0461 0.1609 0.9806
9.250 1.0518 0.01128 0.00586 0.0459 0.1597 0.9830
9.500 1.0831 0.01148 0.00608 0.0450 0.1579 0.9840
9.750 1.1140 0.01171 0.00632 0.0441 0.1558 0.9851
10.000 1.1446 0.01196 0.00658 0.0433 0.1538 0.9863
10.250 1.1747 0.01224 0.00686 0.0425 0.1517 0.9877
10.500 1.2045 0.01255 0.00718 0.0417 0.1493 0.9892
10.750 1.2345 0.01278 0.00744 0.0410 0.1481 0.9907
11.000 1.2639 0.01303 0.00772 0.0403 0.1464 0.9924
11.250 1.2932 0.01331 0.00803 0.0396 0.1444 0.9940
11.500 1.3234 0.01363 0.00836 0.0386 0.1422 0.9955
11.750 1.3530 0.01401 0.00874 0.0377 0.1397 0.9974
12.000 1.3824 0.01438 0.00913 0.0368 0.1377 0.9992
12.250 1.4069 0.01467 0.00946 0.0369 0.1362 1.0000
12.500 1.4259 0.01498 0.00980 0.0381 0.1344 1.0000
12.750 1.4452 0.01533 0.01018 0.0391 0.1323 1.0000
13.000 1.4643 0.01575 0.01061 0.0400 0.1302 1.0000
13.250 1.4831 0.01623 0.01110 0.0409 0.1281 1.0000
13.500 1.5030 0.01664 0.01155 0.0416 0.1267 1.0000
13.750 1.5226 0.01705 0.01202 0.0422 0.1252 1.0000
14.000 1.5410 0.01753 0.01254 0.0430 0.1235 1.0000
14.250 1.5574 0.01809 0.01313 0.0439 0.1216 1.0000
14.500 1.5695 0.01878 0.01385 0.0452 0.1197 1.0000
14.750 1.5724 0.01971 0.01483 0.0473 0.1181 1.0000
15.000 1.5780 0.02084 0.01602 0.0484 0.1168 1.0000
15.250 1.5853 0.02213 0.01737 0.0488 0.1154 1.0000
15.500 1.5915 0.02370 0.01901 0.0488 0.1137 1.0000
15.750 1.5956 0.02563 0.02100 0.0485 0.1121 1.0000
16.000 1.5962 0.02802 0.02346 0.0479 0.1102 1.0000
16.250 1.5927 0.03093 0.02643 0.0470 0.1085 1.0000
16.500 1.5905 0.03376 0.02935 0.0461 0.1071 1.0000
16.750 1.5865 0.03681 0.03248 0.0451 0.1057 1.0000
17.000 1.5789 0.04027 0.03603 0.0439 0.1043 1.0000
17.250 1.5652 0.04446 0.04029 0.0424 0.1027 1.0000
17.500 1.5458 0.04930 0.04521 0.0405 0.1009 1.0000
17.750 1.5196 0.05507 0.05107 0.0382 0.0994 1.0000
18.000 1.5031 0.05989 0.05599 0.0362 0.0981 1.0000
18.250 1.4856 0.06498 0.06117 0.0340 0.0964 1.0000
18.500 1.4658 0.07050 0.06677 0.0316 0.0945 1.0000
18.750 1.4442 0.07638 0.07273 0.0289 0.0929 1.0000
19.000 1.4137 0.08363 0.08005 0.0254 0.0906 1.0000
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Polar data table (+)
Polar graphs
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