S2050 8.93% (s2050-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2050 8.93% (s2050-il) Reynolds number: 50,000 Max Cl/Cd: 34.6 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2050-il-50000-n5.txt Download as CSV file: xf-s2050-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2050 8.93%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5379 0.09441 0.08718 -0.0227 1.0000 0.0449
-9.250 -0.5430 0.08909 0.08195 -0.0255 1.0000 0.0444
-8.750 -0.5945 0.07064 0.06355 -0.0398 1.0000 0.0400
-8.500 -0.6051 0.06594 0.05877 -0.0415 1.0000 0.0399
-8.250 -0.6139 0.06122 0.05387 -0.0426 1.0000 0.0399
-8.000 -0.6185 0.05661 0.04904 -0.0432 1.0000 0.0401
-7.750 -0.6148 0.05311 0.04541 -0.0430 1.0000 0.0411
-7.500 -0.6091 0.04950 0.04156 -0.0428 1.0000 0.0420
-7.250 -0.6006 0.04581 0.03755 -0.0425 1.0000 0.0431
-7.000 -0.5891 0.04220 0.03355 -0.0420 1.0000 0.0444
-6.750 -0.5746 0.03875 0.02962 -0.0414 1.0000 0.0467
-6.500 -0.5569 0.03541 0.02555 -0.0408 1.0000 0.0510
-6.250 -0.5382 0.03353 0.02362 -0.0401 1.0000 0.0561
-6.000 -0.5169 0.03109 0.02066 -0.0392 1.0000 0.0635
-5.750 -0.4962 0.02947 0.01895 -0.0384 1.0000 0.0734
-5.500 -0.4747 0.02791 0.01726 -0.0375 1.0000 0.0859
-5.250 -0.4526 0.02646 0.01566 -0.0365 1.0000 0.1002
-5.000 -0.4302 0.02516 0.01422 -0.0355 1.0000 0.1159
-4.750 -0.4083 0.02402 0.01304 -0.0345 1.0000 0.1336
-4.500 -0.3863 0.02298 0.01201 -0.0335 1.0000 0.1534
-4.250 -0.3640 0.02201 0.01102 -0.0326 1.0000 0.1772
-4.000 -0.3418 0.02106 0.01017 -0.0319 1.0000 0.2080
-3.750 -0.3197 0.02011 0.00937 -0.0313 1.0000 0.2484
-3.500 -0.2978 0.01912 0.00865 -0.0307 1.0000 0.3079
-3.250 -0.2771 0.01809 0.00817 -0.0298 1.0000 0.4059
-3.000 -0.2615 0.01743 0.00823 -0.0268 1.0000 0.5367
-2.750 -0.2464 0.01732 0.00837 -0.0232 1.0000 0.6449
-2.500 -0.2305 0.01732 0.00832 -0.0201 1.0000 0.7130
-2.250 -0.2163 0.01729 0.00829 -0.0165 1.0000 0.7624
-2.000 -0.2028 0.01724 0.00822 -0.0128 1.0000 0.8057
-1.750 -0.1888 0.01716 0.00811 -0.0093 1.0000 0.8462
-1.250 -0.1391 0.01695 0.00774 -0.0070 1.0000 0.9326
-1.000 -0.0819 0.01686 0.00747 -0.0128 1.0000 0.9832
-0.750 -0.0625 0.01676 0.00725 -0.0128 1.0000 1.0000
-0.500 -0.0484 0.01677 0.00713 -0.0118 1.0000 1.0000
-0.250 -0.0272 0.01689 0.00713 -0.0121 0.9985 1.0000
0.000 0.0195 0.01724 0.00734 -0.0168 0.9851 1.0000
0.250 0.0651 0.01752 0.00751 -0.0212 0.9712 1.0000
0.500 0.1075 0.01770 0.00762 -0.0247 0.9553 1.0000
0.750 0.1492 0.01784 0.00773 -0.0280 0.9386 1.0000
1.000 0.1912 0.01795 0.00782 -0.0311 0.9220 1.0000
1.250 0.2342 0.01800 0.00789 -0.0342 0.9053 1.0000
1.500 0.2783 0.01801 0.00793 -0.0372 0.8887 1.0000
1.750 0.3187 0.01800 0.00798 -0.0395 0.8701 1.0000
2.000 0.3570 0.01799 0.00802 -0.0412 0.8494 1.0000
2.250 0.3972 0.01793 0.00805 -0.0429 0.8291 1.0000
2.500 0.4313 0.01795 0.00813 -0.0436 0.8044 1.0000
2.750 0.4653 0.01797 0.00820 -0.0442 0.7786 1.0000
3.000 0.4976 0.01803 0.00829 -0.0443 0.7508 1.0000
3.250 0.5277 0.01815 0.00846 -0.0440 0.7210 1.0000
3.500 0.5559 0.01831 0.00864 -0.0433 0.6891 1.0000
3.750 0.5829 0.01853 0.00885 -0.0425 0.6560 1.0000
4.000 0.6085 0.01879 0.00914 -0.0415 0.6208 1.0000
4.250 0.6337 0.01910 0.00944 -0.0404 0.5841 1.0000
4.500 0.6579 0.01948 0.00978 -0.0393 0.5457 1.0000
4.750 0.6816 0.01991 0.01015 -0.0381 0.5061 1.0000
5.000 0.7044 0.02042 0.01062 -0.0369 0.4649 1.0000
5.250 0.7266 0.02100 0.01113 -0.0357 0.4222 1.0000
5.500 0.7481 0.02166 0.01172 -0.0345 0.3789 1.0000
5.750 0.7690 0.02242 0.01239 -0.0333 0.3352 1.0000
6.000 0.7892 0.02330 0.01315 -0.0322 0.2913 1.0000
6.250 0.8089 0.02429 0.01407 -0.0311 0.2483 1.0000
6.500 0.8284 0.02542 0.01511 -0.0301 0.2076 1.0000
6.750 0.8475 0.02674 0.01633 -0.0291 0.1719 1.0000
7.000 0.8657 0.02820 0.01770 -0.0280 0.1403 1.0000
7.250 0.8838 0.02978 0.01922 -0.0270 0.1148 1.0000
7.500 0.9011 0.03145 0.02081 -0.0259 0.0961 1.0000
7.750 0.9188 0.03324 0.02262 -0.0249 0.0822 1.0000
8.000 0.9376 0.03502 0.02459 -0.0238 0.0713 1.0000
8.250 0.9579 0.03723 0.02703 -0.0228 0.0645 1.0000
8.500 0.9768 0.03934 0.02928 -0.0219 0.0595 1.0000
8.750 0.9947 0.04182 0.03199 -0.0209 0.0551 1.0000
9.000 1.0103 0.04441 0.03498 -0.0198 0.0511 1.0000
9.250 1.0243 0.04716 0.03807 -0.0188 0.0488 1.0000
9.500 1.0362 0.05013 0.04128 -0.0177 0.0473 1.0000
9.750 1.0457 0.05357 0.04493 -0.0167 0.0461 1.0000
10.000 1.0463 0.05747 0.04926 -0.0152 0.0455 1.0000
10.250 1.0404 0.06152 0.05376 -0.0137 0.0451 1.0000
10.500 1.0280 0.06551 0.05809 -0.0121 0.0449 1.0000
10.750 1.0115 0.06965 0.06250 -0.0112 0.0448 1.0000
11.000 0.9918 0.07441 0.06749 -0.0117 0.0448 1.0000
11.250 0.9714 0.07994 0.07320 -0.0139 0.0450 1.0000
11.500 0.9498 0.08654 0.07993 -0.0178 0.0453 1.0000
11.750 0.9295 0.09404 0.08753 -0.0228 0.0456 1.0000
12.000 0.9112 0.10227 0.09581 -0.0284 0.0460 1.0000
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Polar data table (+)
Polar graphs
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