S2060 8% (s2060-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2060 8% (s2060-il) Reynolds number: 50,000 Max Cl/Cd: 36.89 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2060-il-50000-n5.txt Download as CSV file: xf-s2060-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5041 0.09280 0.08569 -0.0270 1.0000 0.0461
-8.750 -0.5062 0.08840 0.08138 -0.0291 1.0000 0.0460
-8.500 -0.5105 0.08379 0.07686 -0.0316 1.0000 0.0459
-8.250 -0.5164 0.07896 0.07212 -0.0346 1.0000 0.0457
-8.000 -0.5202 0.07371 0.06690 -0.0381 1.0000 0.0455
-7.750 -0.5240 0.06860 0.06178 -0.0408 1.0000 0.0452
-7.500 -0.5277 0.06343 0.05652 -0.0431 1.0000 0.0451
-7.250 -0.5294 0.05832 0.05125 -0.0448 1.0000 0.0450
-7.000 -0.5280 0.05334 0.04600 -0.0458 1.0000 0.0452
-6.750 -0.5235 0.04826 0.04050 -0.0465 1.0000 0.0457
-6.500 -0.5147 0.04339 0.03502 -0.0466 1.0000 0.0466
-6.250 -0.5007 0.04112 0.03271 -0.0460 1.0000 0.0503
-6.000 -0.4849 0.03829 0.02948 -0.0455 1.0000 0.0550
-5.750 -0.4668 0.03439 0.02469 -0.0450 1.0000 0.0590
-5.500 -0.4485 0.03279 0.02307 -0.0442 1.0000 0.0664
-5.250 -0.4273 0.03015 0.01986 -0.0434 1.0000 0.0732
-5.000 -0.4064 0.02862 0.01812 -0.0425 1.0000 0.0827
-4.750 -0.3846 0.02693 0.01623 -0.0416 1.0000 0.0906
-4.500 -0.3623 0.02557 0.01462 -0.0406 1.0000 0.1014
-4.250 -0.3398 0.02437 0.01321 -0.0395 1.0000 0.1118
-4.000 -0.3178 0.02330 0.01205 -0.0384 1.0000 0.1236
-3.750 -0.2954 0.02240 0.01104 -0.0375 1.0000 0.1399
-3.500 -0.2729 0.02149 0.01011 -0.0365 1.0000 0.1566
-3.250 -0.2505 0.02070 0.00937 -0.0358 1.0000 0.1847
-3.000 -0.2280 0.01986 0.00866 -0.0352 1.0000 0.2208
-2.750 -0.2056 0.01901 0.00807 -0.0347 1.0000 0.2840
-2.500 -0.1843 0.01807 0.00768 -0.0339 1.0000 0.3915
-2.250 -0.1674 0.01722 0.00761 -0.0315 1.0000 0.5510
-2.000 -0.1548 0.01676 0.00765 -0.0274 1.0000 0.7077
-1.750 -0.1380 0.01645 0.00758 -0.0238 1.0000 0.8479
-1.500 -0.0962 0.01620 0.00712 -0.0265 1.0000 1.0000
-1.250 -0.0752 0.01628 0.00691 -0.0260 1.0000 1.0000
-1.000 -0.0539 0.01640 0.00679 -0.0255 1.0000 1.0000
-0.750 -0.0326 0.01655 0.00670 -0.0251 1.0000 1.0000
-0.500 -0.0113 0.01674 0.00670 -0.0246 1.0000 1.0000
-0.250 0.0102 0.01697 0.00677 -0.0242 0.9999 1.0000
0.000 0.0517 0.01736 0.00700 -0.0277 0.9893 1.0000
0.250 0.0928 0.01775 0.00724 -0.0309 0.9786 1.0000
0.500 0.1341 0.01811 0.00751 -0.0342 0.9675 1.0000
0.750 0.1762 0.01845 0.00778 -0.0374 0.9561 1.0000
1.000 0.2158 0.01872 0.00802 -0.0401 0.9433 1.0000
1.250 0.2552 0.01894 0.00825 -0.0427 0.9298 1.0000
1.500 0.2949 0.01913 0.00847 -0.0451 0.9159 1.0000
1.750 0.3352 0.01927 0.00868 -0.0475 0.9016 1.0000
2.000 0.3761 0.01935 0.00884 -0.0498 0.8868 1.0000
2.250 0.4141 0.01938 0.00897 -0.0514 0.8706 1.0000
2.500 0.4473 0.01941 0.00913 -0.0520 0.8515 1.0000
2.750 0.4827 0.01936 0.00921 -0.0527 0.8324 1.0000
3.000 0.5160 0.01929 0.00928 -0.0529 0.8115 1.0000
3.250 0.5479 0.01921 0.00938 -0.0528 0.7883 1.0000
3.500 0.5775 0.01916 0.00946 -0.0522 0.7619 1.0000
3.750 0.6069 0.01909 0.00953 -0.0514 0.7328 1.0000
4.000 0.6356 0.01906 0.00959 -0.0504 0.7001 1.0000
4.250 0.6625 0.01911 0.00976 -0.0491 0.6620 1.0000
4.500 0.6885 0.01925 0.00992 -0.0476 0.6194 1.0000
4.750 0.7129 0.01951 0.01015 -0.0460 0.5719 1.0000
5.000 0.7353 0.01993 0.01050 -0.0442 0.5196 1.0000
5.250 0.7563 0.02051 0.01101 -0.0424 0.4642 1.0000
5.500 0.7758 0.02125 0.01159 -0.0406 0.4063 1.0000
5.750 0.7937 0.02216 0.01229 -0.0388 0.3445 1.0000
6.000 0.8101 0.02326 0.01314 -0.0370 0.2781 1.0000
6.250 0.8254 0.02464 0.01417 -0.0355 0.2076 1.0000
6.500 0.8399 0.02641 0.01540 -0.0342 0.1335 1.0000
6.750 0.8561 0.02838 0.01714 -0.0330 0.0918 1.0000
7.000 0.8731 0.03023 0.01888 -0.0317 0.0721 1.0000
7.250 0.8918 0.03203 0.02080 -0.0303 0.0624 1.0000
7.500 0.9110 0.03399 0.02283 -0.0290 0.0573 1.0000
7.750 0.9337 0.03605 0.02519 -0.0279 0.0533 1.0000
8.000 0.9551 0.03818 0.02750 -0.0270 0.0499 1.0000
8.250 0.9745 0.04062 0.02998 -0.0262 0.0466 1.0000
8.500 0.9935 0.04318 0.03313 -0.0251 0.0437 1.0000
8.750 1.0097 0.04620 0.03659 -0.0238 0.0421 1.0000
9.000 1.0221 0.04954 0.04038 -0.0224 0.0411 1.0000
9.250 1.0300 0.05312 0.04440 -0.0209 0.0404 1.0000
9.500 1.0328 0.05690 0.04861 -0.0193 0.0400 1.0000
9.750 1.0301 0.06087 0.05297 -0.0176 0.0397 1.0000
10.000 1.0216 0.06496 0.05741 -0.0161 0.0396 1.0000
10.250 1.0060 0.06899 0.06172 -0.0144 0.0397 1.0000
10.500 0.9864 0.07346 0.06642 -0.0138 0.0399 1.0000
10.750 0.9636 0.07880 0.07195 -0.0151 0.0402 1.0000
11.000 0.9386 0.08545 0.07876 -0.0187 0.0407 1.0000
11.250 0.9132 0.09378 0.08718 -0.0245 0.0414 1.0000
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Polar data table (+)
Polar graphs
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