S5010 (s5010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S5010 (s5010-il) Reynolds number: 50,000 Max Cl/Cd: 24.09 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s5010-il-50000.txt Download as CSV file: xf-s5010-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5061 0.11100 0.10502 0.0246 1.0000 0.2368
-8.500 -0.5272 0.11028 0.10444 0.0209 1.0000 0.2459
-8.250 -0.5129 0.10581 0.09999 0.0214 1.0000 0.2601
-8.000 -0.5013 0.10177 0.09599 0.0215 1.0000 0.2742
-7.750 -0.4934 0.09814 0.09242 0.0213 1.0000 0.2886
-7.500 -0.4931 0.09519 0.08957 0.0207 1.0000 0.3040
-7.250 -0.4691 0.09046 0.08485 0.0223 1.0000 0.3253
-7.000 -0.4735 0.08825 0.08275 0.0221 1.0000 0.3479
-6.750 -0.4551 0.08434 0.07888 0.0237 1.0000 0.3756
-6.500 -0.4409 0.08065 0.07525 0.0246 1.0000 0.3991
-6.250 -0.4345 0.07764 0.07232 0.0255 1.0000 0.4262
-5.250 -0.4314 0.04771 0.04111 -0.0227 1.0000 0.1561
-5.000 -0.4177 0.04345 0.03643 -0.0226 1.0000 0.1399
-4.750 -0.4120 0.04059 0.03281 -0.0206 1.0000 0.1288
-4.500 -0.4038 0.03806 0.03018 -0.0185 1.0000 0.1260
-4.250 -0.3941 0.03576 0.02755 -0.0165 1.0000 0.1230
-4.000 -0.3820 0.03376 0.02517 -0.0147 1.0000 0.1227
-3.750 -0.3676 0.03202 0.02306 -0.0131 1.0000 0.1250
-3.500 -0.3508 0.03039 0.02099 -0.0117 1.0000 0.1267
-3.250 -0.3320 0.02887 0.01910 -0.0104 1.0000 0.1279
-3.000 -0.3119 0.02740 0.01739 -0.0094 1.0000 0.1308
-2.750 -0.2919 0.02625 0.01621 -0.0086 1.0000 0.1396
-2.500 -0.2602 0.02508 0.01497 -0.0095 0.9961 0.1542
-2.250 -0.2080 0.02349 0.01349 -0.0137 0.9850 0.1924
-2.000 -0.0955 0.01918 0.01206 -0.0246 0.9843 1.0000
-1.750 -0.0369 0.01964 0.01190 -0.0316 0.9692 1.0000
-1.500 0.0190 0.02008 0.01189 -0.0380 0.9539 1.0000
-1.250 0.0763 0.02049 0.01194 -0.0444 0.9391 1.0000
-1.000 0.1291 0.02089 0.01204 -0.0497 0.9240 1.0000
-0.750 0.1715 0.02135 0.01226 -0.0530 0.9081 1.0000
-0.500 0.2070 0.02187 0.01259 -0.0549 0.8922 1.0000
-0.250 0.2384 0.02244 0.01301 -0.0559 0.8765 1.0000
0.000 0.2663 0.02305 0.01348 -0.0562 0.8611 1.0000
0.250 0.2916 0.02370 0.01400 -0.0559 0.8459 1.0000
0.500 0.3150 0.02437 0.01457 -0.0552 0.8308 1.0000
0.750 0.3371 0.02505 0.01517 -0.0543 0.8158 1.0000
1.000 0.3582 0.02575 0.01579 -0.0531 0.8010 1.0000
1.250 0.3787 0.02647 0.01644 -0.0518 0.7862 1.0000
1.500 0.3989 0.02719 0.01709 -0.0504 0.7715 1.0000
1.750 0.4189 0.02791 0.01777 -0.0490 0.7568 1.0000
2.000 0.4389 0.02864 0.01846 -0.0474 0.7420 1.0000
2.250 0.4588 0.02936 0.01916 -0.0459 0.7273 1.0000
2.500 0.4787 0.03008 0.01987 -0.0444 0.7125 1.0000
2.750 0.4989 0.03078 0.02055 -0.0428 0.6977 1.0000
3.000 0.5190 0.03148 0.02125 -0.0412 0.6828 1.0000
3.250 0.5395 0.03213 0.02194 -0.0395 0.6679 1.0000
3.500 0.5601 0.03278 0.02259 -0.0378 0.6529 1.0000
3.750 0.5810 0.03337 0.02320 -0.0361 0.6379 1.0000
4.000 0.6022 0.03393 0.02379 -0.0343 0.6229 1.0000
4.250 0.6215 0.03473 0.02467 -0.0329 0.6067 1.0000
4.500 0.6398 0.03566 0.02567 -0.0316 0.5898 1.0000
4.750 0.6596 0.03641 0.02648 -0.0301 0.5735 1.0000
5.000 0.6803 0.03703 0.02716 -0.0284 0.5574 1.0000
5.250 0.7016 0.03755 0.02779 -0.0267 0.5415 1.0000
5.500 0.7239 0.03790 0.02821 -0.0248 0.5257 1.0000
5.750 0.7468 0.03814 0.02853 -0.0228 0.5101 1.0000
6.000 0.7704 0.03823 0.02869 -0.0207 0.4944 1.0000
6.250 0.7950 0.03817 0.02873 -0.0185 0.4788 1.0000
6.500 0.8209 0.03790 0.02852 -0.0161 0.4631 1.0000
6.750 0.8367 0.03934 0.03011 -0.0152 0.4442 1.0000
7.000 0.8571 0.03998 0.03088 -0.0136 0.4265 1.0000
7.250 0.8814 0.04002 0.03103 -0.0116 0.4096 1.0000
7.500 0.9090 0.03956 0.03060 -0.0093 0.3927 1.0000
7.750 0.9355 0.03935 0.03041 -0.0072 0.3755 1.0000
8.000 0.9484 0.04130 0.03258 -0.0064 0.3570 1.0000
8.250 0.9685 0.04213 0.03352 -0.0049 0.3391 1.0000
8.500 0.9954 0.04203 0.03345 -0.0030 0.3212 1.0000
8.750 1.0203 0.04236 0.03377 -0.0012 0.3036 1.0000
9.000 1.0319 0.04452 0.03615 -0.0003 0.2873 1.0000
9.250 1.0445 0.04658 0.03838 0.0008 0.2720 1.0000
9.500 1.0566 0.04856 0.04052 0.0019 0.2570 1.0000
9.750 1.0685 0.05083 0.04296 0.0030 0.2439 1.0000
10.000 1.0804 0.05290 0.04515 0.0041 0.2306 1.0000
10.250 1.0027 0.06504 0.05760 0.0006 0.2376 1.0000
10.500 0.9766 0.07159 0.06414 -0.0011 0.2345 1.0000
11.000 1.0961 0.06469 0.05745 0.0076 0.1910 1.0000
13.000 0.7446 0.15726 0.14911 -0.0491 0.3159 1.0000
13.250 0.7689 0.16316 0.15514 -0.0490 0.3042 1.0000
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Polar data table (+)
Polar graphs
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