S5010 (s5010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.77 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5010-il-1000000.txt Download as CSV file: xf-s5010-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S5010
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5633 0.08107 0.07941 0.0093 0.8579 0.0109
-8.250 -0.5732 0.07579 0.07406 0.0059 0.8310 0.0109
-8.000 -0.5872 0.07012 0.06832 0.0013 0.8102 0.0109
-7.750 -0.5917 0.06309 0.06115 -0.0030 0.7964 0.0109
-7.500 -0.5944 0.05595 0.05382 -0.0056 0.7848 0.0109
-7.250 -0.5957 0.04886 0.04647 -0.0069 0.7747 0.0109
-7.000 -0.6593 0.02039 0.01589 -0.0037 0.7710 0.0083
-6.750 -0.6338 0.02001 0.01544 -0.0034 0.7610 0.0086
-6.500 -0.6091 0.01921 0.01449 -0.0030 0.7519 0.0089
-6.250 -0.5843 0.01819 0.01328 -0.0025 0.7428 0.0093
-6.000 -0.5597 0.01688 0.01174 -0.0019 0.7345 0.0096
-5.750 -0.5344 0.01576 0.01039 -0.0014 0.7262 0.0101
-5.500 -0.5081 0.01493 0.00940 -0.0009 0.7179 0.0105
-5.250 -0.4810 0.01457 0.00890 -0.0006 0.7100 0.0109
-5.000 -0.4568 0.01304 0.00725 0.0000 0.7020 0.0119
-4.750 -0.4296 0.01279 0.00694 0.0002 0.6943 0.0126
-4.500 -0.4025 0.01234 0.00642 0.0004 0.6862 0.0134
-4.250 -0.3754 0.01189 0.00589 0.0008 0.6787 0.0141
-4.000 -0.3478 0.01160 0.00553 0.0010 0.6705 0.0147
-3.750 -0.3226 0.01057 0.00438 0.0016 0.6632 0.0159
-3.500 -0.2956 0.01018 0.00396 0.0019 0.6552 0.0170
-3.250 -0.2679 0.00993 0.00368 0.0020 0.6477 0.0182
-3.000 -0.2404 0.00965 0.00334 0.0023 0.6397 0.0192
-2.750 -0.2126 0.00941 0.00305 0.0024 0.6320 0.0200
-2.500 -0.1855 0.00897 0.00251 0.0028 0.6241 0.0214
-2.250 -0.1578 0.00869 0.00219 0.0030 0.6163 0.0235
-1.750 -0.1017 0.00836 0.00176 0.0032 0.6000 0.0267
-1.500 -0.0737 0.00818 0.00155 0.0034 0.5920 0.0330
-1.250 -0.0469 0.00772 0.00137 0.0036 0.5835 0.1104
-1.000 -0.0207 0.00719 0.00123 0.0038 0.5755 0.2327
-0.750 0.0051 0.00666 0.00112 0.0040 0.5669 0.3729
-0.500 0.0309 0.00618 0.00106 0.0043 0.5588 0.5066
-0.250 0.0563 0.00579 0.00101 0.0048 0.5502 0.6277
0.000 0.0805 0.00537 0.00099 0.0056 0.5417 0.7509
0.250 0.1025 0.00497 0.00100 0.0073 0.5336 0.8795
0.500 0.1460 0.00496 0.00111 0.0045 0.5231 0.9705
0.750 0.1942 0.00506 0.00115 0.0003 0.5123 0.9867
1.000 0.2385 0.00516 0.00116 -0.0031 0.5016 0.9941
1.250 0.2809 0.00521 0.00114 -0.0062 0.4906 0.9977
1.500 0.3177 0.00526 0.00112 -0.0081 0.4794 1.0000
1.750 0.3440 0.00530 0.00112 -0.0077 0.4695 1.0000
2.000 0.3703 0.00537 0.00113 -0.0073 0.4591 1.0000
2.500 0.4231 0.00552 0.00118 -0.0067 0.4368 1.0000
2.750 0.4496 0.00560 0.00121 -0.0063 0.4251 1.0000
3.000 0.4762 0.00570 0.00126 -0.0060 0.4130 1.0000
3.250 0.5027 0.00580 0.00132 -0.0057 0.4002 1.0000
3.500 0.5292 0.00592 0.00139 -0.0054 0.3878 1.0000
3.750 0.5558 0.00605 0.00146 -0.0052 0.3740 1.0000
4.000 0.5823 0.00619 0.00156 -0.0049 0.3604 1.0000
4.250 0.6088 0.00634 0.00165 -0.0047 0.3462 1.0000
4.500 0.6353 0.00650 0.00176 -0.0044 0.3313 1.0000
4.750 0.6617 0.00667 0.00188 -0.0042 0.3171 1.0000
5.000 0.6881 0.00685 0.00202 -0.0039 0.3014 1.0000
5.250 0.7145 0.00705 0.00217 -0.0037 0.2862 1.0000
5.500 0.7407 0.00726 0.00233 -0.0035 0.2701 1.0000
5.750 0.7669 0.00748 0.00251 -0.0032 0.2550 1.0000
6.000 0.7930 0.00772 0.00269 -0.0030 0.2394 1.0000
6.250 0.8191 0.00797 0.00289 -0.0028 0.2249 1.0000
6.500 0.8451 0.00823 0.00310 -0.0026 0.2102 1.0000
6.750 0.8709 0.00851 0.00334 -0.0024 0.1957 1.0000
7.000 0.8967 0.00878 0.00357 -0.0021 0.1827 1.0000
7.250 0.9223 0.00909 0.00383 -0.0019 0.1685 1.0000
7.500 0.9478 0.00940 0.00410 -0.0016 0.1558 1.0000
7.750 0.9731 0.00973 0.00440 -0.0014 0.1427 1.0000
8.000 0.9984 0.01008 0.00471 -0.0012 0.1305 1.0000
8.250 1.0234 0.01045 0.00504 -0.0009 0.1184 1.0000
8.500 1.0482 0.01084 0.00540 -0.0007 0.1066 1.0000
8.750 1.0726 0.01128 0.00579 -0.0004 0.0937 1.0000
9.000 1.0968 0.01174 0.00620 -0.0001 0.0823 1.0000
9.250 1.1207 0.01222 0.00663 0.0002 0.0712 1.0000
9.500 1.1443 0.01273 0.00710 0.0005 0.0611 1.0000
9.750 1.1680 0.01320 0.00756 0.0008 0.0536 1.0000
10.000 1.1913 0.01370 0.00805 0.0011 0.0468 1.0000
10.250 1.2137 0.01430 0.00862 0.0015 0.0397 1.0000
10.500 1.2366 0.01479 0.00913 0.0019 0.0350 1.0000
10.750 1.2581 0.01542 0.00975 0.0023 0.0295 1.0000
11.000 1.2788 0.01610 0.01041 0.0029 0.0241 1.0000
11.250 1.2986 0.01681 0.01112 0.0034 0.0190 1.0000
11.500 1.3148 0.01784 0.01212 0.0043 0.0121 1.0000
11.750 1.3297 0.01890 0.01320 0.0054 0.0082 1.0000
12.000 1.3443 0.01988 0.01422 0.0064 0.0068 1.0000
12.250 1.3565 0.02094 0.01535 0.0077 0.0058 1.0000
12.500 1.3663 0.02194 0.01643 0.0092 0.0052 1.0000
12.750 1.3697 0.02307 0.01765 0.0112 0.0051 1.0000
13.000 1.3705 0.02475 0.01942 0.0126 0.0048 1.0000
13.250 1.3735 0.02655 0.02130 0.0133 0.0045 1.0000
13.500 1.3691 0.02925 0.02413 0.0137 0.0042 1.0000
13.750 1.3687 0.03174 0.02674 0.0137 0.0041 1.0000
14.000 1.3705 0.03414 0.02924 0.0136 0.0041 1.0000
14.250 1.3685 0.03702 0.03224 0.0131 0.0041 1.0000
14.500 1.3679 0.03987 0.03519 0.0126 0.0039 1.0000
14.750 1.3653 0.04305 0.03848 0.0118 0.0039 1.0000
15.000 1.3601 0.04664 0.04217 0.0107 0.0038 1.0000
15.250 1.3535 0.05052 0.04617 0.0095 0.0037 1.0000
15.500 1.3429 0.05506 0.05083 0.0078 0.0038 1.0000
15.750 1.3293 0.06018 0.05607 0.0058 0.0036 1.0000
16.000 1.3212 0.06481 0.06080 0.0039 0.0036 1.0000
16.250 1.3094 0.07010 0.06621 0.0016 0.0035 1.0000
16.500 1.2975 0.07561 0.07184 -0.0009 0.0036 1.0000
16.750 1.2843 0.08150 0.07784 -0.0037 0.0035 1.0000
17.000 1.2650 0.08859 0.08506 -0.0071 0.0036 1.0000
17.250 1.2510 0.09496 0.09153 -0.0102 0.0035 1.0000
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Polar data table (+)
Polar graphs
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