S2062 8% (s2062-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 50,000 Max Cl/Cd: 36.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2062-il-50000-n5.txt Download as CSV file: xf-s2062-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2062 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 -0.4973 0.09504 0.08791 -0.0231 1.0000 0.0409
-8.750 -0.4988 0.09070 0.08365 -0.0251 1.0000 0.0403
-8.500 -0.5020 0.08619 0.07923 -0.0274 1.0000 0.0398
-8.250 -0.5067 0.08167 0.07481 -0.0299 1.0000 0.0393
-8.000 -0.5132 0.07668 0.06991 -0.0333 1.0000 0.0385
-7.750 -0.5182 0.07100 0.06426 -0.0372 1.0000 0.0379
-7.500 -0.5230 0.06540 0.05862 -0.0402 1.0000 0.0373
-7.250 -0.5264 0.06000 0.05309 -0.0424 1.0000 0.0367
-7.000 -0.5269 0.05485 0.04771 -0.0437 1.0000 0.0365
-6.750 -0.5234 0.05002 0.04255 -0.0443 1.0000 0.0364
-6.500 -0.5156 0.04570 0.03785 -0.0443 1.0000 0.0366
-6.250 -0.5042 0.04177 0.03349 -0.0440 1.0000 0.0372
-6.000 -0.4895 0.03847 0.02975 -0.0434 1.0000 0.0389
-5.750 -0.4724 0.03537 0.02611 -0.0427 1.0000 0.0422
-5.500 -0.4524 0.03239 0.02237 -0.0417 1.0000 0.0455
-5.250 -0.4334 0.03020 0.02012 -0.0408 1.0000 0.0490
-5.000 -0.4119 0.02806 0.01763 -0.0396 1.0000 0.0543
-4.750 -0.3909 0.02652 0.01594 -0.0386 1.0000 0.0650
-4.500 -0.3690 0.02500 0.01412 -0.0374 1.0000 0.0825
-4.250 -0.3478 0.02370 0.01286 -0.0364 1.0000 0.1047
-4.000 -0.3258 0.02255 0.01167 -0.0354 1.0000 0.1314
-3.750 -0.3033 0.02153 0.01061 -0.0346 1.0000 0.1600
-3.500 -0.2811 0.02064 0.00977 -0.0338 1.0000 0.1969
-3.250 -0.2590 0.01978 0.00904 -0.0330 1.0000 0.2418
-3.000 -0.2372 0.01896 0.00839 -0.0323 1.0000 0.3057
-2.750 -0.2164 0.01813 0.00796 -0.0313 1.0000 0.3946
-2.500 -0.1981 0.01733 0.00770 -0.0294 1.0000 0.5170
-2.250 -0.1851 0.01672 0.00771 -0.0254 1.0000 0.6657
-2.000 -0.1704 0.01643 0.00768 -0.0213 1.0000 0.8125
-1.750 -0.1181 0.01613 0.00720 -0.0252 1.0000 1.0000
-1.500 -0.0992 0.01616 0.00692 -0.0244 1.0000 1.0000
-1.250 -0.0793 0.01622 0.00672 -0.0236 1.0000 1.0000
-1.000 -0.0590 0.01633 0.00659 -0.0229 1.0000 1.0000
-0.750 -0.0384 0.01648 0.00649 -0.0223 1.0000 1.0000
-0.500 -0.0177 0.01665 0.00649 -0.0217 1.0000 1.0000
-0.250 0.0030 0.01687 0.00655 -0.0212 1.0000 1.0000
0.000 0.0390 0.01722 0.00675 -0.0236 0.9924 1.0000
0.250 0.0809 0.01763 0.00701 -0.0271 0.9819 1.0000
0.500 0.1224 0.01799 0.00728 -0.0304 0.9707 1.0000
0.750 0.1623 0.01830 0.00753 -0.0333 0.9584 1.0000
1.000 0.2019 0.01858 0.00779 -0.0360 0.9455 1.0000
1.250 0.2417 0.01882 0.00803 -0.0387 0.9321 1.0000
1.500 0.2817 0.01902 0.00826 -0.0412 0.9182 1.0000
1.750 0.3222 0.01916 0.00849 -0.0437 0.9037 1.0000
2.000 0.3631 0.01926 0.00867 -0.0461 0.8889 1.0000
2.250 0.4028 0.01929 0.00880 -0.0480 0.8731 1.0000
2.500 0.4368 0.01931 0.00898 -0.0487 0.8543 1.0000
2.750 0.4713 0.01927 0.00908 -0.0494 0.8346 1.0000
3.000 0.5053 0.01920 0.00914 -0.0497 0.8138 1.0000
3.250 0.5368 0.01913 0.00922 -0.0495 0.7903 1.0000
3.500 0.5663 0.01907 0.00936 -0.0489 0.7639 1.0000
3.750 0.5957 0.01901 0.00944 -0.0481 0.7348 1.0000
4.000 0.6237 0.01899 0.00953 -0.0470 0.7015 1.0000
4.250 0.6510 0.01902 0.00970 -0.0458 0.6637 1.0000
4.500 0.6768 0.01916 0.00986 -0.0443 0.6205 1.0000
4.750 0.7004 0.01944 0.01013 -0.0426 0.5715 1.0000
5.000 0.7229 0.01985 0.01047 -0.0408 0.5187 1.0000
5.250 0.7436 0.02044 0.01094 -0.0389 0.4620 1.0000
5.500 0.7629 0.02118 0.01154 -0.0371 0.4022 1.0000
5.750 0.7804 0.02211 0.01232 -0.0352 0.3381 1.0000
6.000 0.7964 0.02326 0.01318 -0.0335 0.2683 1.0000
6.250 0.8107 0.02477 0.01423 -0.0319 0.1885 1.0000
6.500 0.8254 0.02665 0.01556 -0.0307 0.1145 1.0000
6.750 0.8419 0.02866 0.01734 -0.0294 0.0820 1.0000
7.000 0.8593 0.03059 0.01927 -0.0280 0.0687 1.0000
7.250 0.8792 0.03244 0.02131 -0.0266 0.0607 1.0000
7.500 0.8982 0.03433 0.02323 -0.0255 0.0544 1.0000
7.750 0.9198 0.03621 0.02551 -0.0245 0.0489 1.0000
8.000 0.9408 0.03840 0.02789 -0.0236 0.0461 1.0000
8.250 0.9614 0.04112 0.03073 -0.0228 0.0441 1.0000
8.500 0.9810 0.04418 0.03419 -0.0217 0.0429 1.0000
8.750 0.9963 0.04750 0.03804 -0.0204 0.0421 1.0000
9.000 1.0066 0.05117 0.04222 -0.0189 0.0415 1.0000
9.250 1.0114 0.05503 0.04658 -0.0172 0.0409 1.0000
9.500 1.0103 0.05898 0.05099 -0.0155 0.0403 1.0000
9.750 1.0041 0.06297 0.05537 -0.0139 0.0397 1.0000
10.000 0.9922 0.06695 0.05967 -0.0124 0.0393 1.0000
10.250 0.9754 0.07102 0.06397 -0.0111 0.0394 1.0000
10.500 0.9559 0.07565 0.06880 -0.0113 0.0396 1.0000
10.750 0.9348 0.08118 0.07448 -0.0134 0.0400 1.0000
11.000 0.9141 0.08771 0.08111 -0.0171 0.0407 1.0000
11.250 0.8945 0.09534 0.08880 -0.0223 0.0413 1.0000
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Polar data table (+)
Polar graphs
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