S2060 8% (s2060-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 500,000 Max Cl/Cd: 90.99 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2060-il-500000.txt Download as CSV file: xf-s2060-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S2060 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6355 0.03789 0.03504 -0.0512 1.0000 0.0128
-8.000 -0.6355 0.03381 0.03060 -0.0500 1.0000 0.0127
-7.750 -0.6250 0.03171 0.02825 -0.0484 1.0000 0.0124
-7.500 -0.6245 0.02664 0.02274 -0.0466 1.0000 0.0120
-7.250 -0.6154 0.02297 0.01858 -0.0449 1.0000 0.0118
-7.000 -0.6009 0.02033 0.01553 -0.0433 1.0000 0.0118
-6.750 -0.5832 0.01840 0.01329 -0.0420 1.0000 0.0119
-6.500 -0.5637 0.01699 0.01163 -0.0408 1.0000 0.0122
-6.250 -0.5399 0.01529 0.00964 -0.0404 0.9995 0.0126
-6.000 -0.5077 0.01380 0.00800 -0.0418 0.9976 0.0138
-5.750 -0.4733 0.01311 0.00722 -0.0434 0.9955 0.0152
-5.500 -0.4389 0.01247 0.00648 -0.0449 0.9936 0.0168
-5.250 -0.4061 0.01176 0.00572 -0.0463 0.9908 0.0208
-5.000 -0.3717 0.01117 0.00512 -0.0477 0.9881 0.0293
-4.750 -0.3360 0.01079 0.00474 -0.0495 0.9858 0.0388
-4.500 -0.2993 0.01053 0.00444 -0.0515 0.9840 0.0461
-4.250 -0.2666 0.01031 0.00422 -0.0527 0.9804 0.0537
-4.000 -0.2328 0.00997 0.00390 -0.0541 0.9768 0.0630
-3.750 -0.1969 0.00963 0.00355 -0.0558 0.9741 0.0731
-3.500 -0.1597 0.00929 0.00325 -0.0579 0.9721 0.0875
-3.250 -0.1215 0.00895 0.00297 -0.0602 0.9706 0.1113
-3.000 -0.0913 0.00859 0.00275 -0.0608 0.9651 0.1444
-2.750 -0.0563 0.00821 0.00255 -0.0625 0.9616 0.1952
-2.500 -0.0210 0.00776 0.00235 -0.0642 0.9585 0.2668
-2.250 0.0106 0.00733 0.00219 -0.0651 0.9536 0.3486
-2.000 0.0397 0.00686 0.00206 -0.0655 0.9471 0.4484
-1.750 0.0705 0.00636 0.00194 -0.0661 0.9423 0.5638
-1.500 0.0956 0.00606 0.00191 -0.0653 0.9331 0.6526
-1.250 0.1232 0.00585 0.00185 -0.0649 0.9255 0.7126
-1.000 0.1491 0.00568 0.00181 -0.0641 0.9161 0.7585
-0.750 0.1744 0.00555 0.00177 -0.0632 0.9057 0.7987
-0.500 0.1995 0.00544 0.00174 -0.0621 0.8953 0.8343
-0.250 0.2241 0.00536 0.00170 -0.0609 0.8844 0.8688
0.000 0.2476 0.00529 0.00167 -0.0594 0.8722 0.9023
0.250 0.2728 0.00523 0.00164 -0.0583 0.8592 0.9360
0.500 0.3065 0.00520 0.00159 -0.0592 0.8459 0.9656
0.750 0.3461 0.00519 0.00153 -0.0616 0.8314 0.9869
1.000 0.3824 0.00520 0.00148 -0.0633 0.8149 1.0000
1.250 0.4066 0.00526 0.00147 -0.0624 0.7959 1.0000
1.500 0.4315 0.00534 0.00147 -0.0617 0.7747 1.0000
1.750 0.4566 0.00544 0.00149 -0.0610 0.7515 1.0000
2.000 0.4818 0.00557 0.00152 -0.0603 0.7250 1.0000
2.250 0.5068 0.00573 0.00157 -0.0596 0.6945 1.0000
2.500 0.5317 0.00592 0.00163 -0.0588 0.6607 1.0000
2.750 0.5567 0.00614 0.00171 -0.0582 0.6261 1.0000
3.000 0.5814 0.00639 0.00184 -0.0575 0.5878 1.0000
3.250 0.6052 0.00673 0.00197 -0.0566 0.5346 1.0000
3.500 0.6280 0.00720 0.00213 -0.0557 0.4659 1.0000
3.750 0.6510 0.00770 0.00233 -0.0549 0.3983 1.0000
4.000 0.6752 0.00813 0.00257 -0.0543 0.3467 1.0000
4.250 0.6994 0.00858 0.00281 -0.0538 0.2967 1.0000
4.500 0.7231 0.00912 0.00309 -0.0532 0.2401 1.0000
4.750 0.7465 0.00971 0.00341 -0.0526 0.1819 1.0000
5.000 0.7698 0.01033 0.00379 -0.0520 0.1302 1.0000
5.250 0.7915 0.01120 0.00430 -0.0512 0.0636 1.0000
5.500 0.8134 0.01210 0.00497 -0.0502 0.0273 1.0000
5.750 0.8376 0.01270 0.00562 -0.0494 0.0232 1.0000
6.000 0.8622 0.01319 0.00618 -0.0488 0.0214 1.0000
6.250 0.8861 0.01375 0.00679 -0.0482 0.0197 1.0000
6.500 0.9089 0.01448 0.00758 -0.0473 0.0187 1.0000
6.750 0.9298 0.01548 0.00866 -0.0461 0.0178 1.0000
7.000 0.9477 0.01700 0.01032 -0.0445 0.0171 1.0000
7.250 0.9698 0.01789 0.01130 -0.0435 0.0168 1.0000
7.500 0.9914 0.01897 0.01249 -0.0425 0.0166 1.0000
7.750 1.0134 0.02001 0.01364 -0.0415 0.0161 1.0000
8.000 1.0353 0.02108 0.01482 -0.0406 0.0154 1.0000
8.250 1.0563 0.02249 0.01637 -0.0395 0.0150 1.0000
8.500 1.0768 0.02412 0.01816 -0.0384 0.0147 1.0000
8.750 1.0964 0.02600 0.02024 -0.0372 0.0145 1.0000
9.000 1.1141 0.02825 0.02277 -0.0358 0.0144 1.0000
9.250 1.1281 0.03128 0.02615 -0.0340 0.0145 1.0000
9.500 1.1383 0.03450 0.02973 -0.0318 0.0145 1.0000
9.750 1.1455 0.03764 0.03321 -0.0295 0.0143 1.0000
10.000 1.1428 0.04216 0.03816 -0.0265 0.0147 1.0000
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Polar data table (+)
Polar graphs
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