S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 50,000 Max Cl/Cd: 32.42 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8052-il-50000-n5.txt Download as CSV file: xf-s8052-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3886 0.12318 0.11633 -0.0189 1.0000 0.0515
-11.750 -0.3894 0.11902 0.11219 -0.0206 1.0000 0.0504
-11.250 -0.5098 0.11109 0.10380 -0.0237 1.0000 0.0453
-11.000 -0.5079 0.10663 0.09939 -0.0254 1.0000 0.0450
-10.750 -0.5080 0.10178 0.09458 -0.0275 1.0000 0.0446
-10.500 -0.5095 0.09671 0.08956 -0.0300 1.0000 0.0442
-10.250 -0.5143 0.09074 0.08365 -0.0334 1.0000 0.0438
-10.000 -0.5227 0.08410 0.07705 -0.0378 1.0000 0.0432
-9.750 -0.5376 0.07746 0.07041 -0.0425 1.0000 0.0426
-9.500 -0.5566 0.07170 0.06463 -0.0463 1.0000 0.0421
-9.250 -0.5763 0.06713 0.06001 -0.0478 1.0000 0.0418
-9.000 -0.5939 0.06324 0.05601 -0.0475 1.0000 0.0415
-8.750 -0.6055 0.05946 0.05205 -0.0469 1.0000 0.0413
-8.500 -0.6134 0.05580 0.04816 -0.0458 1.0000 0.0412
-8.250 -0.6173 0.05240 0.04449 -0.0443 1.0000 0.0412
-8.000 -0.6183 0.04930 0.04109 -0.0424 1.0000 0.0417
-7.750 -0.6170 0.04654 0.03801 -0.0402 1.0000 0.0423
-7.500 -0.6142 0.04409 0.03524 -0.0376 1.0000 0.0431
-7.250 -0.6106 0.04179 0.03254 -0.0348 1.0000 0.0443
-7.000 -0.6050 0.03975 0.03010 -0.0320 1.0000 0.0455
-6.750 -0.5968 0.03791 0.02819 -0.0297 1.0000 0.0468
-6.500 -0.5870 0.03629 0.02643 -0.0274 1.0000 0.0482
-6.250 -0.5751 0.03472 0.02467 -0.0251 1.0000 0.0495
-6.000 -0.5615 0.03323 0.02294 -0.0230 1.0000 0.0513
-5.750 -0.5465 0.03185 0.02135 -0.0210 1.0000 0.0536
-5.500 -0.5313 0.03062 0.01994 -0.0190 1.0000 0.0572
-5.250 -0.5044 0.02937 0.01867 -0.0194 0.9951 0.0639
-5.000 -0.4742 0.02806 0.01727 -0.0203 0.9886 0.0728
-4.750 -0.4437 0.02681 0.01599 -0.0214 0.9824 0.0903
-4.500 -0.4165 0.02548 0.01480 -0.0220 0.9753 0.1235
-4.250 -0.3886 0.02386 0.01371 -0.0233 0.9691 0.1974
-4.000 -0.3667 0.02239 0.01301 -0.0236 0.9616 0.3232
-3.750 -0.3435 0.02144 0.01294 -0.0229 0.9554 0.4832
-3.500 -0.3232 0.02143 0.01333 -0.0203 0.9477 0.6029
-3.250 -0.2946 0.02172 0.01358 -0.0192 0.9418 0.6817
-3.000 -0.2726 0.02199 0.01376 -0.0171 0.9341 0.7307
-2.750 -0.2425 0.02228 0.01387 -0.0163 0.9282 0.7725
-2.500 -0.2159 0.02252 0.01396 -0.0151 0.9214 0.8057
-2.250 -0.1825 0.02276 0.01402 -0.0152 0.9155 0.8357
-2.000 -0.1370 0.02300 0.01404 -0.0176 0.9117 0.8615
-1.750 -0.1008 0.02317 0.01402 -0.0188 0.9048 0.8836
-1.500 -0.0496 0.02331 0.01395 -0.0229 0.9002 0.9021
-1.250 0.0068 0.02339 0.01382 -0.0282 0.8965 0.9176
-1.000 0.0524 0.02345 0.01372 -0.0319 0.8894 0.9320
-0.750 0.1061 0.02342 0.01355 -0.0371 0.8841 0.9439
-0.500 0.1529 0.02340 0.01341 -0.0412 0.8773 0.9561
-0.250 0.2023 0.02331 0.01323 -0.0458 0.8701 0.9662
0.000 0.2479 0.02322 0.01307 -0.0497 0.8624 0.9764
0.250 0.2921 0.02310 0.01291 -0.0533 0.8539 0.9863
0.500 0.3334 0.02302 0.01281 -0.0565 0.8443 0.9966
0.750 0.3656 0.02293 0.01269 -0.0577 0.8348 1.0000
1.000 0.3824 0.02302 0.01276 -0.0562 0.8226 1.0000
1.250 0.3969 0.02313 0.01287 -0.0542 0.8097 1.0000
1.500 0.4121 0.02323 0.01297 -0.0522 0.7968 1.0000
1.750 0.4285 0.02329 0.01303 -0.0502 0.7841 1.0000
2.000 0.4464 0.02331 0.01305 -0.0484 0.7714 1.0000
2.250 0.4660 0.02326 0.01299 -0.0466 0.7587 1.0000
2.500 0.4838 0.02326 0.01299 -0.0445 0.7450 1.0000
2.750 0.5007 0.02328 0.01304 -0.0423 0.7302 1.0000
3.000 0.5188 0.02328 0.01303 -0.0402 0.7151 1.0000
3.250 0.5380 0.02324 0.01300 -0.0382 0.6997 1.0000
3.500 0.5584 0.02316 0.01295 -0.0362 0.6836 1.0000
3.750 0.5752 0.02323 0.01306 -0.0340 0.6649 1.0000
4.000 0.5944 0.02321 0.01308 -0.0321 0.6457 1.0000
4.250 0.6161 0.02309 0.01298 -0.0303 0.6261 1.0000
4.500 0.6361 0.02305 0.01299 -0.0284 0.6039 1.0000
4.750 0.6586 0.02291 0.01288 -0.0267 0.5808 1.0000
5.000 0.6799 0.02289 0.01287 -0.0250 0.5546 1.0000
5.250 0.7022 0.02289 0.01283 -0.0234 0.5264 1.0000
5.500 0.7241 0.02299 0.01289 -0.0217 0.4960 1.0000
5.750 0.7452 0.02323 0.01302 -0.0201 0.4646 1.0000
6.000 0.7650 0.02362 0.01327 -0.0185 0.4324 1.0000
6.250 0.7839 0.02418 0.01369 -0.0169 0.4016 1.0000
6.500 0.8018 0.02485 0.01425 -0.0153 0.3724 1.0000
6.750 0.8193 0.02561 0.01492 -0.0138 0.3455 1.0000
7.000 0.8367 0.02644 0.01563 -0.0124 0.3216 1.0000
7.250 0.8539 0.02731 0.01643 -0.0110 0.2992 1.0000
7.500 0.8714 0.02822 0.01728 -0.0098 0.2796 1.0000
7.750 0.8886 0.02917 0.01824 -0.0085 0.2605 1.0000
8.000 0.9062 0.03015 0.01922 -0.0074 0.2437 1.0000
8.250 0.9236 0.03117 0.02025 -0.0062 0.2279 1.0000
8.500 0.9414 0.03223 0.02137 -0.0052 0.2135 1.0000
8.750 0.9583 0.03333 0.02251 -0.0041 0.1997 1.0000
9.000 0.9751 0.03449 0.02371 -0.0030 0.1872 1.0000
9.250 0.9917 0.03568 0.02491 -0.0019 0.1757 1.0000
9.500 1.0066 0.03691 0.02619 -0.0007 0.1646 1.0000
9.750 1.0213 0.03832 0.02779 0.0005 0.1543 1.0000
10.000 1.0353 0.03973 0.02929 0.0016 0.1452 1.0000
10.250 1.0481 0.04110 0.03073 0.0029 0.1371 1.0000
10.500 1.0602 0.04284 0.03269 0.0042 0.1298 1.0000
10.750 1.0717 0.04436 0.03426 0.0055 0.1234 1.0000
11.000 1.0794 0.04629 0.03640 0.0069 0.1175 1.0000
11.250 1.0858 0.04823 0.03853 0.0083 0.1121 1.0000
11.500 1.1016 0.04990 0.04017 0.0090 0.1078 1.0000
11.750 1.0981 0.05282 0.04352 0.0106 0.1043 1.0000
12.000 1.0957 0.05560 0.04656 0.0117 0.1008 1.0000
12.250 1.0984 0.05787 0.04895 0.0125 0.0974 1.0000
12.500 1.1044 0.06008 0.05118 0.0131 0.0944 1.0000
12.750 1.0868 0.06445 0.05592 0.0134 0.0927 1.0000
13.000 1.0665 0.06944 0.06122 0.0128 0.0915 1.0000
13.250 1.0413 0.07546 0.06751 0.0112 0.0907 1.0000
13.500 1.0063 0.08347 0.07575 0.0076 0.0905 1.0000
13.750 0.9521 0.09609 0.08855 0.0003 0.0913 1.0000
14.000 0.8813 0.11591 0.10836 -0.0119 0.0923 1.0000
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Polar data table (+)
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