S2060 8% (s2060-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 500,000 Max Cl/Cd: 75.1 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2060-il-500000-n5.txt Download as CSV file: xf-s2060-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5593 0.09157 0.08923 -0.0208 1.0000 0.0058
-10.250 -0.5763 0.08382 0.08152 -0.0246 1.0000 0.0058
-9.750 -0.7631 0.03517 0.03229 -0.0549 1.0000 0.0046
-9.500 -0.7643 0.03100 0.02773 -0.0543 1.0000 0.0047
-9.250 -0.7585 0.02786 0.02423 -0.0532 1.0000 0.0048
-9.000 -0.7478 0.02551 0.02157 -0.0519 1.0000 0.0049
-8.750 -0.7339 0.02369 0.01948 -0.0506 1.0000 0.0050
-8.500 -0.7181 0.02223 0.01778 -0.0494 1.0000 0.0053
-8.250 -0.7018 0.02075 0.01605 -0.0480 1.0000 0.0054
-8.000 -0.6751 0.01940 0.01446 -0.0487 0.9985 0.0057
-7.750 -0.6455 0.01804 0.01286 -0.0499 0.9963 0.0058
-7.500 -0.6151 0.01682 0.01143 -0.0510 0.9944 0.0059
-7.250 -0.5866 0.01555 0.00996 -0.0518 0.9918 0.0061
-7.000 -0.5572 0.01436 0.00859 -0.0527 0.9891 0.0066
-6.750 -0.5261 0.01355 0.00763 -0.0537 0.9867 0.0071
-6.500 -0.4939 0.01291 0.00690 -0.0549 0.9848 0.0076
-6.250 -0.4616 0.01234 0.00622 -0.0561 0.9829 0.0083
-6.000 -0.4326 0.01186 0.00564 -0.0565 0.9790 0.0089
-5.750 -0.4014 0.01133 0.00506 -0.0574 0.9760 0.0107
-5.500 -0.3692 0.01084 0.00456 -0.0585 0.9735 0.0156
-5.250 -0.3364 0.01045 0.00419 -0.0597 0.9712 0.0229
-5.000 -0.3066 0.01016 0.00388 -0.0602 0.9671 0.0282
-4.750 -0.2767 0.00990 0.00362 -0.0607 0.9623 0.0336
-4.500 -0.2450 0.00964 0.00332 -0.0615 0.9586 0.0391
-4.250 -0.2143 0.00942 0.00311 -0.0622 0.9541 0.0469
-4.000 -0.1855 0.00914 0.00287 -0.0624 0.9478 0.0555
-3.750 -0.1543 0.00891 0.00262 -0.0631 0.9429 0.0627
-3.500 -0.1261 0.00871 0.00240 -0.0631 0.9356 0.0717
-3.250 -0.0965 0.00848 0.00220 -0.0635 0.9293 0.0852
-3.000 -0.0686 0.00827 0.00203 -0.0635 0.9212 0.1010
-2.750 -0.0400 0.00807 0.00186 -0.0636 0.9135 0.1202
-2.500 -0.0127 0.00786 0.00171 -0.0634 0.9038 0.1457
-2.250 0.0147 0.00764 0.00158 -0.0633 0.8940 0.1804
-2.000 0.0420 0.00742 0.00147 -0.0632 0.8840 0.2205
-1.750 0.0689 0.00720 0.00137 -0.0630 0.8730 0.2701
-1.500 0.0958 0.00699 0.00128 -0.0628 0.8613 0.3203
-1.250 0.1224 0.00674 0.00120 -0.0626 0.8488 0.3875
-1.000 0.1488 0.00647 0.00115 -0.0623 0.8354 0.4651
-0.750 0.1749 0.00623 0.00111 -0.0619 0.8208 0.5452
-0.500 0.2008 0.00604 0.00111 -0.0614 0.8052 0.6214
-0.250 0.2267 0.00593 0.00112 -0.0608 0.7882 0.6785
0.000 0.2527 0.00587 0.00113 -0.0602 0.7696 0.7211
0.250 0.2784 0.00584 0.00114 -0.0595 0.7489 0.7589
0.500 0.3036 0.00584 0.00116 -0.0588 0.7267 0.7936
0.750 0.3285 0.00587 0.00119 -0.0579 0.7020 0.8255
1.250 0.3759 0.00596 0.00128 -0.0555 0.6477 0.8939
1.500 0.4006 0.00605 0.00132 -0.0546 0.6179 0.9330
1.750 0.4334 0.00619 0.00136 -0.0555 0.5835 0.9686
2.250 0.4930 0.00665 0.00152 -0.0565 0.5075 1.0000
2.500 0.5180 0.00692 0.00163 -0.0560 0.4685 1.0000
2.750 0.5430 0.00723 0.00176 -0.0555 0.4266 1.0000
3.000 0.5668 0.00768 0.00194 -0.0549 0.3640 1.0000
3.250 0.5906 0.00818 0.00214 -0.0543 0.2993 1.0000
3.500 0.6150 0.00864 0.00235 -0.0538 0.2460 1.0000
3.750 0.6402 0.00900 0.00256 -0.0534 0.2097 1.0000
4.000 0.6647 0.00945 0.00283 -0.0530 0.1655 1.0000
4.250 0.6894 0.00990 0.00310 -0.0525 0.1271 1.0000
4.500 0.7135 0.01043 0.00342 -0.0520 0.0861 1.0000
5.000 0.7615 0.01155 0.00422 -0.0509 0.0234 1.0000
5.250 0.7867 0.01195 0.00459 -0.0505 0.0172 1.0000
5.500 0.8120 0.01232 0.00498 -0.0500 0.0154 1.0000
5.750 0.8370 0.01274 0.00544 -0.0495 0.0140 1.0000
6.000 0.8615 0.01326 0.00604 -0.0489 0.0130 1.0000
6.250 0.8862 0.01370 0.00655 -0.0484 0.0127 1.0000
6.500 0.9106 0.01416 0.00708 -0.0479 0.0122 1.0000
6.750 0.9346 0.01467 0.00765 -0.0473 0.0116 1.0000
7.000 0.9580 0.01526 0.00831 -0.0466 0.0113 1.0000
7.250 0.9810 0.01590 0.00902 -0.0458 0.0110 1.0000
7.500 1.0034 0.01658 0.00978 -0.0450 0.0106 1.0000
7.750 1.0254 0.01732 0.01061 -0.0441 0.0103 1.0000
8.000 1.0469 0.01810 0.01147 -0.0432 0.0100 1.0000
8.250 1.0677 0.01896 0.01242 -0.0423 0.0097 1.0000
8.500 1.0875 0.01996 0.01351 -0.0412 0.0094 1.0000
8.750 1.1056 0.02121 0.01487 -0.0399 0.0090 1.0000
9.000 1.1199 0.02326 0.01708 -0.0381 0.0085 1.0000
9.250 1.1402 0.02410 0.01807 -0.0372 0.0084 1.0000
9.500 1.1593 0.02508 0.01919 -0.0361 0.0082 1.0000
9.750 1.1766 0.02634 0.02062 -0.0348 0.0080 1.0000
10.000 1.1928 0.02768 0.02213 -0.0334 0.0078 1.0000
10.250 1.2071 0.02919 0.02383 -0.0318 0.0076 1.0000
10.500 1.2194 0.03082 0.02567 -0.0301 0.0074 1.0000
10.750 1.2296 0.03251 0.02755 -0.0282 0.0072 1.0000
11.000 1.2369 0.03423 0.02948 -0.0260 0.0070 1.0000
11.250 1.2405 0.03575 0.03118 -0.0233 0.0068 1.0000
11.500 1.2414 0.03741 0.03301 -0.0205 0.0066 1.0000
11.750 1.2429 0.03889 0.03462 -0.0182 0.0064 1.0000
12.000 1.2416 0.04080 0.03667 -0.0161 0.0062 1.0000
12.250 1.2394 0.04289 0.03889 -0.0146 0.0061 1.0000
12.500 1.2339 0.04556 0.04173 -0.0134 0.0060 1.0000
12.750 1.2306 0.04814 0.04442 -0.0130 0.0059 1.0000
13.000 1.2239 0.05143 0.04784 -0.0132 0.0058 1.0000
13.250 1.2100 0.05622 0.05283 -0.0145 0.0058 1.0000
13.500 1.1967 0.06144 0.05822 -0.0168 0.0058 1.0000
13.750 1.1806 0.06783 0.06479 -0.0204 0.0058 1.0000
14.000 1.1609 0.07571 0.07287 -0.0254 0.0058 1.0000
14.250 1.1409 0.08451 0.08184 -0.0312 0.0058 1.0000
14.500 1.1006 0.09922 0.09682 -0.0409 0.0059 1.0000
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Polar data table (+)
Polar graphs
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