SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 100,000 Max Cl/Cd: 51.6 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6060-il-100000.txt Download as CSV file: xf-sd6060-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD6060-104-88
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4707 0.11441 0.10952 -0.0152 1.0000 0.0926
-10.000 -0.4817 0.11116 0.10634 -0.0200 1.0000 0.0945
-9.750 -0.5001 0.10769 0.10299 -0.0265 1.0000 0.0952
-9.500 -0.4621 0.10295 0.09817 -0.0193 1.0000 0.1010
-9.250 -0.4632 0.09941 0.09469 -0.0215 1.0000 0.1058
-9.000 -0.4926 0.09565 0.09109 -0.0303 1.0000 0.1087
-8.750 -0.4750 0.09098 0.08642 -0.0275 1.0000 0.1113
-8.500 -0.4625 0.08788 0.08331 -0.0262 1.0000 0.1156
-8.250 -0.4739 0.08396 0.07948 -0.0303 1.0000 0.1206
-8.000 -0.5174 0.08003 0.07560 -0.0385 1.0000 0.1227
-7.750 -0.4920 0.07563 0.07129 -0.0349 1.0000 0.1264
-7.500 -0.4889 0.07248 0.06817 -0.0347 1.0000 0.1317
-7.250 -0.5216 0.06864 0.06423 -0.0382 1.0000 0.1381
-7.000 -0.5027 0.06542 0.06114 -0.0354 1.0000 0.1420
-6.750 -0.5369 0.06423 0.05964 -0.0345 1.0000 0.1516
-6.500 -0.5207 0.06010 0.05578 -0.0317 1.0000 0.1548
-6.250 -0.5233 0.05797 0.05364 -0.0289 1.0000 0.1606
-5.750 -0.5362 0.04412 0.03820 -0.0259 1.0000 0.0805
-5.500 -0.5345 0.04417 0.03850 -0.0242 1.0000 0.1110
-5.250 -0.5160 0.03507 0.02776 -0.0201 1.0000 0.0549
-5.000 -0.5024 0.03191 0.02435 -0.0185 1.0000 0.0535
-4.750 -0.4862 0.02941 0.02147 -0.0168 1.0000 0.0526
-4.500 -0.4677 0.02739 0.01905 -0.0152 1.0000 0.0530
-4.250 -0.4484 0.02631 0.01753 -0.0136 1.0000 0.0556
-4.000 -0.4229 0.02397 0.01513 -0.0137 0.9986 0.0594
-3.750 -0.3826 0.02236 0.01335 -0.0158 0.9931 0.0650
-3.500 -0.3449 0.02094 0.01190 -0.0177 0.9869 0.0794
-3.250 -0.3092 0.01934 0.01056 -0.0195 0.9808 0.1217
-3.000 -0.2820 0.01688 0.00955 -0.0204 0.9741 0.3268
-2.750 -0.2642 0.01555 0.01012 -0.0169 0.9676 0.7437
-2.500 -0.2345 0.01601 0.01065 -0.0147 0.9602 0.8685
-2.250 -0.1685 0.01684 0.01117 -0.0194 0.9586 0.9421
-2.000 -0.0531 0.01729 0.01111 -0.0350 0.9639 0.9795
-1.750 0.0379 0.01712 0.01059 -0.0477 0.9652 1.0000
-1.500 0.0859 0.01704 0.01031 -0.0528 0.9576 1.0000
-1.250 0.1241 0.01699 0.01011 -0.0559 0.9473 1.0000
-1.000 0.1688 0.01692 0.00991 -0.0601 0.9392 1.0000
-0.750 0.2133 0.01683 0.00970 -0.0640 0.9310 1.0000
-0.500 0.2468 0.01681 0.00961 -0.0658 0.9202 1.0000
-0.250 0.2829 0.01677 0.00949 -0.0679 0.9107 1.0000
0.000 0.3191 0.01667 0.00934 -0.0698 0.9014 1.0000
0.250 0.3426 0.01673 0.00936 -0.0693 0.8891 1.0000
0.500 0.3652 0.01679 0.00939 -0.0686 0.8770 1.0000
0.750 0.3877 0.01684 0.00941 -0.0677 0.8654 1.0000
1.000 0.4113 0.01684 0.00940 -0.0668 0.8546 1.0000
1.250 0.4346 0.01681 0.00935 -0.0656 0.8440 1.0000
1.500 0.4522 0.01692 0.00946 -0.0637 0.8312 1.0000
1.750 0.4704 0.01703 0.00957 -0.0617 0.8189 1.0000
2.000 0.4895 0.01711 0.00967 -0.0599 0.8068 1.0000
2.250 0.5097 0.01714 0.00969 -0.0580 0.7952 1.0000
2.500 0.5317 0.01707 0.00963 -0.0563 0.7843 1.0000
2.750 0.5530 0.01703 0.00959 -0.0545 0.7724 1.0000
3.000 0.5729 0.01705 0.00967 -0.0525 0.7591 1.0000
3.250 0.5935 0.01705 0.00969 -0.0507 0.7456 1.0000
3.500 0.6148 0.01701 0.00968 -0.0488 0.7318 1.0000
3.750 0.6367 0.01695 0.00964 -0.0470 0.7175 1.0000
4.000 0.6591 0.01686 0.00961 -0.0453 0.7028 1.0000
4.250 0.6821 0.01675 0.00952 -0.0436 0.6873 1.0000
4.500 0.7044 0.01669 0.00951 -0.0419 0.6700 1.0000
4.750 0.7262 0.01667 0.00954 -0.0402 0.6507 1.0000
5.000 0.7499 0.01655 0.00947 -0.0386 0.6314 1.0000
5.250 0.7721 0.01653 0.00950 -0.0369 0.6088 1.0000
5.500 0.7952 0.01647 0.00944 -0.0353 0.5850 1.0000
5.750 0.8173 0.01647 0.00946 -0.0336 0.5575 1.0000
6.000 0.8379 0.01655 0.00962 -0.0318 0.5250 1.0000
6.250 0.8583 0.01669 0.00972 -0.0300 0.4890 1.0000
6.500 0.8772 0.01700 0.00995 -0.0281 0.4475 1.0000
6.750 0.8948 0.01751 0.01030 -0.0261 0.4029 1.0000
7.000 0.9108 0.01822 0.01085 -0.0241 0.3561 1.0000
7.250 0.9245 0.01906 0.01147 -0.0220 0.3066 1.0000
7.500 0.9364 0.01999 0.01221 -0.0198 0.2548 1.0000
7.750 0.9481 0.02108 0.01309 -0.0177 0.2084 1.0000
8.000 0.9571 0.02251 0.01426 -0.0154 0.1606 1.0000
8.250 0.9604 0.02457 0.01589 -0.0123 0.1112 1.0000
8.500 0.9665 0.02661 0.01767 -0.0096 0.0848 1.0000
8.750 0.9791 0.02857 0.01954 -0.0076 0.0724 1.0000
9.000 0.9993 0.03053 0.02160 -0.0063 0.0651 1.0000
9.250 1.0208 0.03291 0.02391 -0.0057 0.0586 1.0000
9.500 1.0423 0.03491 0.02620 -0.0047 0.0544 1.0000
9.750 1.0646 0.03743 0.02892 -0.0040 0.0516 1.0000
10.000 1.0860 0.04047 0.03210 -0.0034 0.0494 1.0000
10.250 1.0990 0.04447 0.03640 -0.0023 0.0473 1.0000
10.500 1.1028 0.04692 0.03933 0.0002 0.0460 1.0000
10.750 1.1039 0.05018 0.04301 0.0026 0.0455 1.0000
11.000 1.0998 0.05374 0.04697 0.0051 0.0454 1.0000
11.250 1.0898 0.05713 0.05067 0.0079 0.0455 1.0000
11.500 1.0756 0.06069 0.05451 0.0104 0.0458 1.0000
11.750 1.0601 0.06447 0.05854 0.0121 0.0461 1.0000
12.000 1.0425 0.06862 0.06291 0.0129 0.0464 1.0000
12.250 1.0234 0.07323 0.06771 0.0127 0.0467 1.0000
12.500 1.0045 0.07832 0.07297 0.0117 0.0471 1.0000
12.750 0.9858 0.08418 0.07897 0.0099 0.0475 1.0000
13.250 0.8627 0.11282 0.10815 -0.0121 0.0550 1.0000
13.500 0.8450 0.12330 0.11859 -0.0176 0.0575 1.0000
13.750 0.8401 0.13018 0.12545 -0.0203 0.0586 1.0000
14.000 0.8397 0.13596 0.13122 -0.0219 0.0593 1.0000
14.250 0.6535 0.15479 0.15040 -0.0286 0.1235 1.0000
14.500 0.6434 0.15868 0.15426 -0.0315 0.1227 1.0000
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Polar data table (+)
Polar graphs
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