S2060 8% (s2060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 1,000,000 Max Cl/Cd: 101.46 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2060-il-1000000.txt Download as CSV file: xf-s2060-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7664 0.03351 0.03118 -0.0557 1.0000 0.0062
-9.500 -0.7688 0.02959 0.02692 -0.0545 1.0000 0.0062
-9.250 -0.7647 0.02656 0.02358 -0.0529 1.0000 0.0062
-9.000 -0.7569 0.02402 0.02074 -0.0512 1.0000 0.0063
-8.750 -0.7460 0.02184 0.01829 -0.0494 1.0000 0.0063
-8.500 -0.7329 0.01997 0.01618 -0.0477 1.0000 0.0064
-8.250 -0.7179 0.01837 0.01435 -0.0461 1.0000 0.0064
-8.000 -0.6887 0.01696 0.01275 -0.0473 0.9988 0.0066
-7.750 -0.6575 0.01578 0.01140 -0.0487 0.9973 0.0068
-7.500 -0.6253 0.01489 0.01039 -0.0502 0.9959 0.0071
-7.250 -0.5930 0.01378 0.00911 -0.0516 0.9947 0.0073
-7.000 -0.5623 0.01281 0.00798 -0.0525 0.9928 0.0075
-6.750 -0.5312 0.01198 0.00703 -0.0535 0.9907 0.0078
-6.500 -0.4989 0.01131 0.00625 -0.0546 0.9887 0.0083
-6.250 -0.4655 0.01084 0.00570 -0.0559 0.9871 0.0087
-6.000 -0.4323 0.00994 0.00468 -0.0573 0.9856 0.0100
-5.750 -0.3979 0.00951 0.00421 -0.0589 0.9844 0.0112
-5.500 -0.3628 0.00908 0.00371 -0.0605 0.9835 0.0134
-5.250 -0.3339 0.00862 0.00332 -0.0608 0.9796 0.0221
-5.000 -0.3009 0.00836 0.00311 -0.0620 0.9772 0.0309
-4.750 -0.2674 0.00813 0.00287 -0.0632 0.9748 0.0360
-4.500 -0.2340 0.00790 0.00265 -0.0645 0.9725 0.0416
-4.250 -0.2019 0.00768 0.00242 -0.0654 0.9696 0.0470
-4.000 -0.1744 0.00748 0.00225 -0.0652 0.9634 0.0543
-3.750 -0.1448 0.00724 0.00205 -0.0656 0.9586 0.0657
-3.500 -0.1168 0.00703 0.00186 -0.0655 0.9523 0.0781
-3.250 -0.0893 0.00682 0.00168 -0.0654 0.9451 0.0935
-3.000 -0.0622 0.00661 0.00154 -0.0651 0.9375 0.1162
-2.750 -0.0351 0.00639 0.00140 -0.0649 0.9296 0.1445
-2.500 -0.0083 0.00619 0.00128 -0.0646 0.9206 0.1780
-2.250 0.0186 0.00597 0.00117 -0.0644 0.9120 0.2197
-2.000 0.0452 0.00572 0.00107 -0.0642 0.9020 0.2757
-1.750 0.0719 0.00549 0.00099 -0.0639 0.8918 0.3352
-1.500 0.0984 0.00522 0.00092 -0.0637 0.8814 0.4102
-1.250 0.1248 0.00495 0.00087 -0.0634 0.8704 0.4937
-1.000 0.1511 0.00469 0.00084 -0.0631 0.8586 0.5843
-0.750 0.1776 0.00453 0.00083 -0.0627 0.8462 0.6498
-0.250 0.2309 0.00437 0.00083 -0.0619 0.8192 0.7372
0.000 0.2574 0.00432 0.00084 -0.0614 0.8039 0.7724
0.250 0.2836 0.00430 0.00085 -0.0609 0.7871 0.8046
0.500 0.3094 0.00428 0.00087 -0.0602 0.7685 0.8360
0.750 0.3347 0.00428 0.00090 -0.0595 0.7476 0.8676
1.000 0.3591 0.00430 0.00093 -0.0585 0.7250 0.8995
1.250 0.3825 0.00434 0.00096 -0.0572 0.6997 0.9326
1.500 0.4105 0.00442 0.00098 -0.0570 0.6710 0.9660
1.750 0.4479 0.00456 0.00100 -0.0591 0.6355 0.9932
2.000 0.4765 0.00476 0.00106 -0.0593 0.5998 1.0000
2.250 0.5022 0.00495 0.00113 -0.0588 0.5667 1.0000
2.500 0.5276 0.00520 0.00121 -0.0584 0.5270 1.0000
2.750 0.5521 0.00556 0.00133 -0.0578 0.4675 1.0000
3.000 0.5763 0.00599 0.00148 -0.0572 0.4003 1.0000
3.250 0.6016 0.00633 0.00163 -0.0568 0.3521 1.0000
3.500 0.6265 0.00671 0.00180 -0.0563 0.3015 1.0000
3.750 0.6515 0.00711 0.00199 -0.0559 0.2520 1.0000
4.000 0.6767 0.00750 0.00220 -0.0555 0.2090 1.0000
4.250 0.7017 0.00791 0.00242 -0.0551 0.1669 1.0000
4.500 0.7259 0.00843 0.00270 -0.0546 0.1176 1.0000
4.750 0.7499 0.00899 0.00303 -0.0540 0.0714 1.0000
5.000 0.7727 0.00976 0.00351 -0.0533 0.0222 1.0000
5.250 0.7982 0.01016 0.00390 -0.0528 0.0169 1.0000
5.500 0.8241 0.01047 0.00424 -0.0524 0.0156 1.0000
5.750 0.8495 0.01084 0.00465 -0.0520 0.0145 1.0000
6.000 0.8747 0.01125 0.00510 -0.0515 0.0137 1.0000
6.250 0.8992 0.01176 0.00567 -0.0509 0.0130 1.0000
6.500 0.9227 0.01243 0.00642 -0.0501 0.0124 1.0000
6.750 0.9434 0.01347 0.00759 -0.0489 0.0119 1.0000
7.000 0.9679 0.01393 0.00810 -0.0483 0.0117 1.0000
7.250 0.9919 0.01444 0.00867 -0.0477 0.0113 1.0000
7.500 1.0153 0.01502 0.00931 -0.0470 0.0109 1.0000
7.750 1.0376 0.01578 0.01014 -0.0461 0.0105 1.0000
8.000 1.0593 0.01662 0.01105 -0.0451 0.0101 1.0000
8.250 1.0807 0.01751 0.01202 -0.0442 0.0099 1.0000
8.500 1.1019 0.01840 0.01299 -0.0432 0.0096 1.0000
8.750 1.1227 0.01936 0.01405 -0.0422 0.0093 1.0000
9.000 1.1429 0.02038 0.01514 -0.0412 0.0090 1.0000
9.250 1.1614 0.02166 0.01650 -0.0401 0.0086 1.0000
9.750 1.1911 0.02575 0.02099 -0.0369 0.0078 1.0000
10.000 1.2083 0.02694 0.02234 -0.0355 0.0077 1.0000
10.250 1.2238 0.02830 0.02387 -0.0340 0.0074 1.0000
10.500 1.2362 0.03001 0.02578 -0.0322 0.0072 1.0000
10.750 1.2450 0.03203 0.02802 -0.0300 0.0070 1.0000
11.000 1.2505 0.03415 0.03035 -0.0276 0.0069 1.0000
11.250 1.2550 0.03575 0.03211 -0.0251 0.0066 1.0000
11.500 1.2484 0.03793 0.03449 -0.0212 0.0066 1.0000
11.750 1.2445 0.03974 0.03643 -0.0182 0.0064 1.0000
12.000 1.2289 0.04298 0.03990 -0.0151 0.0064 1.0000
12.250 1.2146 0.04632 0.04344 -0.0133 0.0064 1.0000
12.500 1.2001 0.05007 0.04736 -0.0126 0.0064 1.0000
12.750 1.1976 0.05262 0.04998 -0.0128 0.0062 1.0000
13.000 1.1942 0.05561 0.05305 -0.0135 0.0061 1.0000
13.250 1.1560 0.06472 0.06246 -0.0177 0.0062 1.0000
13.500 1.1071 0.07825 0.07630 -0.0265 0.0065 1.0000
13.750 1.0912 0.08659 0.08477 -0.0326 0.0064 1.0000
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Polar data table (+)
Polar graphs
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