S8064 (s8064-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8064 (s8064-il) Reynolds number: 100,000 Max Cl/Cd: 48.8 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8064-il-100000.txt Download as CSV file: xf-s8064-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S8064
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.7162 0.05226 0.04707 -0.0307 1.0000 0.0687
-8.000 -0.7523 0.05583 0.05041 -0.0285 1.0000 0.0637
-7.750 -0.7711 0.05041 0.04415 -0.0228 1.0000 0.0549
-7.500 -0.7701 0.04664 0.04014 -0.0199 1.0000 0.0534
-7.250 -0.7669 0.04319 0.03635 -0.0169 1.0000 0.0519
-7.000 -0.7611 0.03981 0.03251 -0.0138 1.0000 0.0506
-6.750 -0.7513 0.03672 0.02894 -0.0111 1.0000 0.0502
-6.500 -0.7374 0.03409 0.02585 -0.0087 1.0000 0.0504
-6.250 -0.7207 0.03196 0.02335 -0.0068 1.0000 0.0516
-6.000 -0.7030 0.03048 0.02145 -0.0048 1.0000 0.0553
-5.750 -0.6838 0.02827 0.01918 -0.0035 1.0000 0.0598
-5.500 -0.6638 0.02679 0.01756 -0.0019 1.0000 0.0651
-5.250 -0.6449 0.02522 0.01595 -0.0004 1.0000 0.0743
-5.000 -0.6273 0.02397 0.01475 0.0013 1.0000 0.0897
-4.750 -0.6107 0.02278 0.01363 0.0030 1.0000 0.1124
-4.500 -0.5948 0.02163 0.01267 0.0048 1.0000 0.1416
-4.250 -0.5800 0.02040 0.01177 0.0067 1.0000 0.1861
-4.000 -0.5686 0.01871 0.01093 0.0090 1.0000 0.2964
-3.750 -0.5630 0.01718 0.01080 0.0130 1.0000 0.5366
-3.500 -0.5524 0.01714 0.01132 0.0175 1.0000 0.6684
-3.250 -0.5395 0.01745 0.01165 0.0212 1.0000 0.7368
-3.000 -0.5267 0.01781 0.01197 0.0250 1.0000 0.7822
-2.750 -0.5139 0.01814 0.01226 0.0289 1.0000 0.8182
-2.500 -0.5013 0.01845 0.01248 0.0327 1.0000 0.8519
-2.250 -0.4851 0.01879 0.01274 0.0358 1.0000 0.8833
-2.000 -0.4422 0.01975 0.01353 0.0338 0.9960 0.9138
-1.750 -0.3686 0.02124 0.01474 0.0258 0.9926 0.9382
-1.500 -0.2785 0.02268 0.01590 0.0141 0.9905 0.9565
-1.250 -0.1975 0.02358 0.01656 0.0032 0.9876 0.9696
-1.000 -0.1251 0.02415 0.01695 -0.0066 0.9843 0.9792
-0.750 -0.0635 0.02443 0.01710 -0.0146 0.9799 0.9884
-0.500 -0.0017 0.02469 0.01725 -0.0226 0.9756 0.9971
-0.250 0.0444 0.02492 0.01741 -0.0279 0.9697 1.0000
0.000 0.0718 0.02498 0.01743 -0.0295 0.9608 1.0000
0.250 0.0986 0.02512 0.01753 -0.0308 0.9518 1.0000
0.500 0.1367 0.02539 0.01778 -0.0341 0.9445 1.0000
0.750 0.1557 0.02548 0.01786 -0.0338 0.9339 1.0000
1.000 0.1803 0.02568 0.01805 -0.0345 0.9242 1.0000
1.250 0.2189 0.02595 0.01834 -0.0375 0.9167 1.0000
1.500 0.2360 0.02608 0.01848 -0.0365 0.9050 1.0000
1.750 0.2568 0.02625 0.01868 -0.0362 0.8941 1.0000
2.000 0.3048 0.02649 0.01897 -0.0404 0.8875 1.0000
2.250 0.3200 0.02657 0.01909 -0.0388 0.8749 1.0000
2.500 0.3368 0.02667 0.01923 -0.0375 0.8625 1.0000
2.750 0.3581 0.02674 0.01935 -0.0367 0.8507 1.0000
3.000 0.4083 0.02668 0.01941 -0.0406 0.8429 1.0000
3.500 0.4620 0.02634 0.01925 -0.0401 0.8180 1.0000
3.750 0.4936 0.02597 0.01899 -0.0403 0.8051 1.0000
4.000 0.5396 0.02522 0.01843 -0.0425 0.7925 1.0000
4.250 0.5944 0.02387 0.01729 -0.0454 0.7793 1.0000
4.500 0.6415 0.02221 0.01585 -0.0464 0.7647 1.0000
4.750 0.6830 0.02044 0.01427 -0.0463 0.7485 1.0000
5.000 0.7212 0.01877 0.01277 -0.0456 0.7299 1.0000
5.250 0.7425 0.01777 0.01190 -0.0427 0.7040 1.0000
5.500 0.7639 0.01696 0.01115 -0.0399 0.6687 1.0000
5.750 0.7861 0.01636 0.01047 -0.0372 0.6143 1.0000
6.000 0.7979 0.01635 0.01016 -0.0331 0.5316 1.0000
6.250 0.7959 0.01712 0.01020 -0.0271 0.4107 1.0000
6.500 0.7848 0.01852 0.01078 -0.0204 0.2982 1.0000
6.750 0.7786 0.02013 0.01168 -0.0150 0.2216 1.0000
7.000 0.7819 0.02157 0.01268 -0.0111 0.1788 1.0000
7.250 0.7924 0.02294 0.01376 -0.0085 0.1520 1.0000
7.500 0.8099 0.02424 0.01499 -0.0068 0.1319 1.0000
7.750 0.8305 0.02561 0.01627 -0.0058 0.1158 1.0000
8.000 0.8562 0.02723 0.01785 -0.0056 0.1027 1.0000
8.250 0.8810 0.02892 0.01959 -0.0052 0.0907 1.0000
8.500 0.9054 0.03080 0.02149 -0.0049 0.0800 1.0000
8.750 0.9324 0.03324 0.02386 -0.0053 0.0705 1.0000
9.000 0.9509 0.03513 0.02619 -0.0035 0.0651 1.0000
9.250 0.9719 0.03742 0.02857 -0.0027 0.0603 1.0000
9.500 0.9858 0.04058 0.03208 -0.0010 0.0569 1.0000
9.750 0.9934 0.04307 0.03508 0.0019 0.0547 1.0000
10.000 0.9983 0.04627 0.03872 0.0048 0.0537 1.0000
10.250 0.9984 0.04966 0.04252 0.0080 0.0535 1.0000
10.500 0.9928 0.05316 0.04641 0.0115 0.0536 1.0000
10.750 0.9825 0.05663 0.05020 0.0153 0.0542 1.0000
11.000 0.9672 0.06003 0.05387 0.0192 0.0547 1.0000
11.250 0.9503 0.06363 0.05770 0.0224 0.0554 1.0000
11.500 0.9307 0.06743 0.06170 0.0250 0.0559 1.0000
11.750 0.9140 0.07148 0.06591 0.0265 0.0566 1.0000
12.000 0.8938 0.07596 0.07055 0.0274 0.0571 1.0000
12.250 0.8891 0.08194 0.07655 0.0272 0.0582 1.0000
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Polar data table (+)
Polar graphs
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