S5020 (s5020-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5020 (s5020-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.4 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5020-il-1000000.txt Download as CSV file: xf-s5020-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S5020
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5309 0.09145 0.08991 0.0197 0.8932 0.0086
-8.000 -0.5431 0.08626 0.08462 0.0180 0.8533 0.0088
-7.500 -0.5519 0.07833 0.07654 0.0130 0.8061 0.0089
-7.250 -0.5465 0.07487 0.07301 0.0106 0.7899 0.0090
-7.000 -0.5384 0.07129 0.06935 0.0081 0.7756 0.0091
-6.750 -0.5288 0.06731 0.06529 0.0053 0.7630 0.0093
-6.500 -0.5171 0.06349 0.06138 0.0029 0.7517 0.0095
-6.250 -0.5036 0.05929 0.05706 0.0004 0.7412 0.0097
-6.000 -0.4882 0.05494 0.05259 -0.0017 0.7313 0.0101
-5.750 -0.4709 0.05054 0.04803 -0.0035 0.7223 0.0105
-5.500 -0.4453 0.04545 0.04270 -0.0045 0.7141 0.0121
-5.250 -0.4235 0.04069 0.03769 -0.0048 0.7058 0.0122
-5.000 -0.4030 0.03599 0.03269 -0.0047 0.6983 0.0123
-4.750 -0.3903 0.02786 0.02404 -0.0045 0.6917 0.0129
-4.500 -0.3672 0.02634 0.02237 -0.0044 0.6833 0.0132
-4.250 -0.3432 0.02476 0.02063 -0.0042 0.6749 0.0137
-4.000 -0.3182 0.02334 0.01904 -0.0040 0.6668 0.0146
-3.750 -0.2898 0.02265 0.01815 -0.0033 0.6586 0.0169
-3.500 -0.2625 0.02161 0.01683 -0.0026 0.6505 0.0173
-3.250 -0.2409 0.01653 0.01121 -0.0017 0.6439 0.0187
-3.000 -0.2142 0.01570 0.01031 -0.0015 0.6357 0.0197
-2.750 -0.1871 0.01495 0.00942 -0.0013 0.6279 0.0211
-2.500 -0.1590 0.01257 0.00664 -0.0002 0.6203 0.0184
-2.250 -0.1312 0.01191 0.00585 0.0002 0.6125 0.0180
-2.000 -0.1036 0.01105 0.00494 0.0006 0.6042 0.0169
-1.750 -0.0763 0.01033 0.00411 0.0010 0.5965 0.0170
-1.500 -0.0484 0.01005 0.00377 0.0012 0.5880 0.0174
-1.250 -0.0222 0.00912 0.00276 0.0018 0.5800 0.0180
-0.750 0.0327 0.00839 0.00189 0.0023 0.5631 0.0190
-0.500 0.0606 0.00818 0.00163 0.0024 0.5547 0.0202
-0.250 0.0886 0.00801 0.00141 0.0026 0.5457 0.0211
0.000 0.1167 0.00788 0.00123 0.0027 0.5369 0.0227
0.250 0.1449 0.00781 0.00110 0.0028 0.5280 0.0246
0.500 0.1728 0.00760 0.00100 0.0029 0.5188 0.0677
0.750 0.1958 0.00637 0.00093 0.0033 0.5103 0.4826
1.000 0.2447 0.00501 0.00102 -0.0011 0.4992 0.9909
1.250 0.2969 0.00507 0.00099 -0.0064 0.4869 1.0000
1.500 0.3236 0.00512 0.00098 -0.0060 0.4764 1.0000
1.750 0.3503 0.00519 0.00098 -0.0057 0.4661 1.0000
2.000 0.3771 0.00527 0.00099 -0.0054 0.4555 1.0000
2.250 0.4039 0.00535 0.00101 -0.0051 0.4440 1.0000
2.500 0.4307 0.00543 0.00105 -0.0048 0.4327 1.0000
2.750 0.4575 0.00552 0.00109 -0.0046 0.4209 1.0000
3.000 0.4844 0.00562 0.00113 -0.0043 0.4090 1.0000
3.250 0.5112 0.00573 0.00119 -0.0041 0.3963 1.0000
3.500 0.5380 0.00585 0.00127 -0.0038 0.3827 1.0000
3.750 0.5649 0.00599 0.00134 -0.0036 0.3687 1.0000
4.000 0.5917 0.00613 0.00143 -0.0034 0.3542 1.0000
4.250 0.6185 0.00628 0.00153 -0.0032 0.3389 1.0000
4.500 0.6452 0.00645 0.00165 -0.0030 0.3244 1.0000
4.750 0.6719 0.00663 0.00178 -0.0029 0.3087 1.0000
5.000 0.6986 0.00682 0.00191 -0.0027 0.2931 1.0000
5.250 0.7252 0.00701 0.00206 -0.0025 0.2783 1.0000
5.500 0.7518 0.00724 0.00224 -0.0024 0.2620 1.0000
5.750 0.7783 0.00747 0.00241 -0.0022 0.2470 1.0000
6.000 0.8047 0.00772 0.00260 -0.0021 0.2312 1.0000
6.250 0.8310 0.00796 0.00281 -0.0019 0.2166 1.0000
6.500 0.8573 0.00822 0.00303 -0.0018 0.2021 1.0000
6.750 0.8835 0.00850 0.00327 -0.0016 0.1867 1.0000
7.000 0.9095 0.00881 0.00352 -0.0015 0.1710 1.0000
7.250 0.9354 0.00914 0.00380 -0.0014 0.1549 1.0000
7.750 0.9866 0.00992 0.00444 -0.0011 0.1216 1.0000
8.000 1.0121 0.01030 0.00478 -0.0010 0.1082 1.0000
8.250 1.0374 0.01072 0.00514 -0.0009 0.0946 1.0000
8.500 1.0623 0.01118 0.00555 -0.0007 0.0802 1.0000
8.750 1.0871 0.01164 0.00597 -0.0006 0.0685 1.0000
9.000 1.1116 0.01216 0.00643 -0.0004 0.0565 1.0000
9.250 1.1353 0.01276 0.00696 -0.0002 0.0433 1.0000
9.500 1.1579 0.01356 0.00765 0.0000 0.0277 1.0000
9.750 1.1769 0.01488 0.00882 0.0005 0.0083 1.0000
10.000 1.1992 0.01559 0.00959 0.0009 0.0064 1.0000
10.250 1.2213 0.01630 0.01036 0.0012 0.0058 1.0000
10.500 1.2410 0.01729 0.01146 0.0018 0.0050 1.0000
10.750 1.2613 0.01810 0.01237 0.0023 0.0047 1.0000
11.000 1.2812 0.01888 0.01323 0.0029 0.0044 1.0000
11.250 1.2992 0.01981 0.01425 0.0035 0.0042 1.0000
11.500 1.3156 0.02081 0.01537 0.0043 0.0041 1.0000
11.750 1.3297 0.02192 0.01658 0.0052 0.0040 1.0000
12.000 1.3415 0.02310 0.01785 0.0062 0.0039 1.0000
12.250 1.3447 0.02454 0.01941 0.0079 0.0038 1.0000
12.500 1.3436 0.02629 0.02125 0.0093 0.0037 1.0000
12.750 1.3436 0.02842 0.02350 0.0099 0.0037 1.0000
13.000 1.3436 0.03085 0.02604 0.0099 0.0036 1.0000
13.250 1.3425 0.03359 0.02889 0.0095 0.0035 1.0000
13.500 1.3376 0.03693 0.03234 0.0088 0.0035 1.0000
13.750 1.3342 0.04023 0.03576 0.0079 0.0035 1.0000
14.000 1.3257 0.04429 0.03993 0.0066 0.0034 1.0000
14.250 1.3165 0.04858 0.04435 0.0051 0.0034 1.0000
14.500 1.3025 0.05365 0.04954 0.0031 0.0033 1.0000
14.750 1.2899 0.05871 0.05472 0.0011 0.0033 1.0000
15.000 1.2840 0.06293 0.05905 -0.0006 0.0034 1.0000
15.250 1.2685 0.06883 0.06506 -0.0033 0.0033 1.0000
15.500 1.2616 0.07363 0.06996 -0.0054 0.0033 1.0000
15.750 1.2454 0.08004 0.07649 -0.0084 0.0033 1.0000
16.000 1.2336 0.08593 0.08248 -0.0112 0.0033 1.0000
16.250 1.2211 0.09209 0.08875 -0.0142 0.0033 1.0000
16.500 1.2096 0.09822 0.09498 -0.0171 0.0033 1.0000
16.750 1.1985 0.10442 0.10128 -0.0202 0.0033 1.0000
17.000 1.1881 0.11063 0.10759 -0.0233 0.0033 1.0000
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Polar data table (+)
Polar graphs
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