S5010 (s5010-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 50,000 Max Cl/Cd: 32.53 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s5010-il-50000-n5.txt Download as CSV file: xf-s5010-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5197 0.09576 0.08971 0.0060 1.0000 0.0581
-8.250 -0.5415 0.08732 0.08134 -0.0068 1.0000 0.0517
-8.000 -0.5320 0.08351 0.07759 -0.0065 1.0000 0.0507
-7.750 -0.5281 0.07901 0.07311 -0.0087 1.0000 0.0498
-7.500 -0.5249 0.07425 0.06834 -0.0115 1.0000 0.0488
-7.250 -0.5216 0.06930 0.06333 -0.0143 1.0000 0.0479
-7.000 -0.5168 0.06430 0.05822 -0.0168 1.0000 0.0470
-6.750 -0.5098 0.05939 0.05312 -0.0190 1.0000 0.0462
-6.500 -0.5003 0.05461 0.04807 -0.0206 1.0000 0.0457
-6.250 -0.4876 0.05037 0.04351 -0.0217 1.0000 0.0462
-6.000 -0.4726 0.04648 0.03922 -0.0225 1.0000 0.0476
-5.750 -0.4555 0.04288 0.03516 -0.0228 1.0000 0.0491
-5.500 -0.4371 0.03962 0.03140 -0.0227 1.0000 0.0499
-5.250 -0.4188 0.03672 0.02806 -0.0222 1.0000 0.0503
-5.000 -0.4019 0.03433 0.02524 -0.0212 0.9970 0.0509
-4.750 -0.3656 0.03147 0.02192 -0.0235 0.9699 0.0532
-4.500 -0.3283 0.02953 0.01977 -0.0258 0.9511 0.0584
-4.250 -0.2903 0.02756 0.01736 -0.0274 0.9350 0.0618
-4.000 -0.2537 0.02599 0.01539 -0.0283 0.9198 0.0649
-3.750 -0.2222 0.02467 0.01406 -0.0288 0.9047 0.0708
-3.500 -0.1924 0.02374 0.01293 -0.0288 0.8897 0.0804
-3.250 -0.1647 0.02286 0.01189 -0.0284 0.8753 0.0913
-3.000 -0.1390 0.02189 0.01093 -0.0279 0.8614 0.1117
-2.750 -0.1173 0.02049 0.01013 -0.0271 0.8481 0.2033
-2.500 -0.1067 0.01850 0.01004 -0.0237 0.8359 0.5651
-2.250 -0.0142 0.01788 0.00995 -0.0301 0.8292 0.9562
-2.000 0.0443 0.01772 0.00927 -0.0360 0.8168 1.0000
-1.750 0.0641 0.01779 0.00903 -0.0349 0.8032 1.0000
-1.500 0.0847 0.01790 0.00883 -0.0338 0.7901 1.0000
-1.250 0.1057 0.01803 0.00870 -0.0328 0.7777 1.0000
-1.000 0.1270 0.01818 0.00861 -0.0317 0.7657 1.0000
-0.750 0.1484 0.01833 0.00853 -0.0305 0.7545 1.0000
-0.500 0.1706 0.01851 0.00849 -0.0295 0.7427 1.0000
-0.250 0.1934 0.01870 0.00851 -0.0286 0.7307 1.0000
0.000 0.2162 0.01891 0.00855 -0.0277 0.7192 1.0000
0.250 0.2388 0.01911 0.00860 -0.0267 0.7083 1.0000
0.500 0.2613 0.01930 0.00862 -0.0255 0.6980 1.0000
0.750 0.2848 0.01954 0.00876 -0.0247 0.6860 1.0000
1.000 0.3082 0.01978 0.00891 -0.0239 0.6744 1.0000
1.250 0.3314 0.02001 0.00904 -0.0229 0.6633 1.0000
1.500 0.3543 0.02020 0.00912 -0.0217 0.6531 1.0000
1.750 0.3781 0.02045 0.00931 -0.0209 0.6412 1.0000
2.000 0.4019 0.02072 0.00953 -0.0202 0.6291 1.0000
2.250 0.4256 0.02098 0.00976 -0.0193 0.6174 1.0000
2.500 0.4492 0.02120 0.00993 -0.0184 0.6061 1.0000
2.750 0.4728 0.02137 0.01003 -0.0172 0.5955 1.0000
3.000 0.4968 0.02165 0.01033 -0.0164 0.5828 1.0000
3.250 0.5208 0.02193 0.01062 -0.0157 0.5701 1.0000
3.500 0.5447 0.02220 0.01090 -0.0148 0.5574 1.0000
3.750 0.5687 0.02246 0.01117 -0.0140 0.5446 1.0000
4.000 0.5927 0.02271 0.01147 -0.0131 0.5318 1.0000
4.250 0.6167 0.02296 0.01173 -0.0122 0.5188 1.0000
4.500 0.6406 0.02321 0.01200 -0.0113 0.5055 1.0000
4.750 0.6646 0.02347 0.01230 -0.0104 0.4919 1.0000
5.000 0.6885 0.02375 0.01266 -0.0096 0.4777 1.0000
5.250 0.7123 0.02406 0.01302 -0.0088 0.4631 1.0000
5.500 0.7359 0.02439 0.01342 -0.0080 0.4479 1.0000
5.750 0.7594 0.02475 0.01385 -0.0072 0.4324 1.0000
6.000 0.7827 0.02513 0.01435 -0.0064 0.4165 1.0000
6.250 0.8058 0.02553 0.01481 -0.0055 0.4003 1.0000
6.500 0.8286 0.02595 0.01529 -0.0047 0.3840 1.0000
6.750 0.8513 0.02639 0.01579 -0.0038 0.3677 1.0000
7.000 0.8737 0.02686 0.01634 -0.0029 0.3514 1.0000
7.250 0.8950 0.02753 0.01712 -0.0022 0.3341 1.0000
7.500 0.9158 0.02822 0.01792 -0.0014 0.3167 1.0000
7.750 0.9364 0.02896 0.01874 -0.0006 0.3000 1.0000
8.000 0.9562 0.02972 0.01957 0.0002 0.2835 1.0000
8.250 0.9756 0.03057 0.02052 0.0011 0.2677 1.0000
8.500 0.9941 0.03147 0.02147 0.0020 0.2521 1.0000
8.750 1.0114 0.03253 0.02261 0.0028 0.2369 1.0000
9.000 1.0275 0.03369 0.02388 0.0037 0.2221 1.0000
9.250 1.0428 0.03491 0.02520 0.0046 0.2082 1.0000
9.500 1.0570 0.03619 0.02655 0.0056 0.1951 1.0000
9.750 1.0693 0.03762 0.02815 0.0065 0.1825 1.0000
10.000 1.0797 0.03926 0.02998 0.0075 0.1708 1.0000
10.250 1.0882 0.04100 0.03187 0.0085 0.1600 1.0000
10.500 1.0962 0.04273 0.03368 0.0095 0.1505 1.0000
10.750 1.1041 0.04444 0.03547 0.0105 0.1419 1.0000
11.000 1.1032 0.04681 0.03807 0.0116 0.1343 1.0000
11.250 1.1086 0.04854 0.03974 0.0125 0.1270 1.0000
11.500 1.1026 0.05173 0.04325 0.0127 0.1209 1.0000
11.750 1.1096 0.05359 0.04507 0.0133 0.1145 1.0000
12.000 1.0991 0.05762 0.04942 0.0126 0.1100 1.0000
12.250 1.0928 0.06117 0.05313 0.0119 0.1050 1.0000
12.500 1.0942 0.06390 0.05591 0.0117 0.1000 1.0000
12.750 1.0763 0.06960 0.06191 0.0095 0.0975 1.0000
13.000 1.0570 0.07593 0.06844 0.0066 0.0954 1.0000
13.250 1.0328 0.08352 0.07621 0.0027 0.0942 1.0000
13.500 0.9886 0.09579 0.08863 -0.0046 0.0950 1.0000
13.750 0.9230 0.11515 0.10792 -0.0160 0.0971 1.0000
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Polar data table (+)
Polar graphs
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