S4053 (s4053-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4053 (s4053-il) Reynolds number: 50,000 Max Cl/Cd: 39.24 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4053-il-50000-n5.txt Download as CSV file: xf-s4053-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4053
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 -0.3085 0.10527 0.09863 -0.0307 1.0000 0.1121
-9.250 -0.3221 0.10319 0.09666 -0.0330 1.0000 0.1158
-9.000 -0.3320 0.10052 0.09409 -0.0347 1.0000 0.1164
-8.750 -0.3315 0.09673 0.09038 -0.0351 1.0000 0.1168
-8.500 -0.3302 0.09300 0.08667 -0.0352 1.0000 0.1170
-8.250 -0.3117 0.08797 0.08160 -0.0336 1.0000 0.1081
-7.750 -0.3974 0.08731 0.08063 -0.0359 1.0000 0.0574
-7.500 -0.4014 0.08390 0.07734 -0.0365 1.0000 0.0550
-7.000 -0.4130 0.07415 0.06763 -0.0440 1.0000 0.0479
-6.750 -0.4116 0.07093 0.06446 -0.0434 1.0000 0.0471
-6.500 -0.4108 0.06756 0.06110 -0.0433 1.0000 0.0463
-6.250 -0.4100 0.06405 0.05756 -0.0434 1.0000 0.0458
-6.000 -0.4082 0.06056 0.05399 -0.0433 1.0000 0.0455
-5.750 -0.4050 0.05710 0.05040 -0.0431 1.0000 0.0454
-5.500 -0.3999 0.05364 0.04674 -0.0429 1.0000 0.0457
-5.250 -0.3924 0.05030 0.04309 -0.0425 1.0000 0.0461
-5.000 -0.3826 0.04709 0.03956 -0.0420 1.0000 0.0463
-4.750 -0.3704 0.04400 0.03610 -0.0415 1.0000 0.0465
-4.500 -0.3561 0.04117 0.03290 -0.0408 1.0000 0.0462
-4.250 -0.3346 0.03823 0.02952 -0.0411 0.9981 0.0459
-4.000 -0.2997 0.03511 0.02580 -0.0434 0.9917 0.0459
-3.750 -0.2645 0.03251 0.02263 -0.0453 0.9852 0.0463
-3.500 -0.2300 0.03039 0.01998 -0.0467 0.9787 0.0470
-3.250 -0.1946 0.02864 0.01775 -0.0480 0.9723 0.0481
-3.000 -0.1618 0.02710 0.01603 -0.0490 0.9656 0.0506
-2.750 -0.1275 0.02611 0.01488 -0.0505 0.9587 0.0570
-2.500 -0.0946 0.02511 0.01369 -0.0514 0.9514 0.0645
-2.250 -0.0590 0.02423 0.01257 -0.0529 0.9448 0.0742
-2.000 -0.0268 0.02327 0.01162 -0.0539 0.9370 0.1012
-1.750 0.0020 0.02069 0.01114 -0.0552 0.9316 0.4721
-1.500 0.0601 0.01940 0.01083 -0.0590 0.9299 1.0000
-1.250 0.0910 0.01956 0.01055 -0.0599 0.9200 1.0000
-1.000 0.1256 0.01972 0.01030 -0.0615 0.9119 1.0000
-0.750 0.1605 0.01988 0.01014 -0.0632 0.9037 1.0000
-0.500 0.1915 0.02007 0.01006 -0.0641 0.8945 1.0000
-0.250 0.2305 0.02021 0.00993 -0.0664 0.8880 1.0000
0.000 0.2585 0.02043 0.00996 -0.0666 0.8779 1.0000
0.250 0.2905 0.02061 0.00997 -0.0676 0.8695 1.0000
0.500 0.3235 0.02077 0.00999 -0.0686 0.8613 1.0000
0.750 0.3509 0.02102 0.01012 -0.0687 0.8513 1.0000
1.000 0.3842 0.02117 0.01018 -0.0697 0.8434 1.0000
1.250 0.4132 0.02138 0.01033 -0.0700 0.8338 1.0000
1.500 0.4402 0.02164 0.01053 -0.0699 0.8235 1.0000
1.750 0.4719 0.02180 0.01065 -0.0705 0.8149 1.0000
2.000 0.5011 0.02199 0.01083 -0.0706 0.8050 1.0000
2.250 0.5268 0.02226 0.01111 -0.0702 0.7939 1.0000
2.500 0.5545 0.02247 0.01134 -0.0700 0.7832 1.0000
2.750 0.5854 0.02258 0.01147 -0.0702 0.7733 1.0000
3.000 0.6137 0.02272 0.01166 -0.0699 0.7620 1.0000
3.250 0.6392 0.02294 0.01197 -0.0692 0.7494 1.0000
3.500 0.6650 0.02313 0.01223 -0.0685 0.7365 1.0000
3.750 0.6911 0.02329 0.01247 -0.0678 0.7232 1.0000
4.000 0.7173 0.02341 0.01269 -0.0670 0.7093 1.0000
4.250 0.7435 0.02351 0.01294 -0.0661 0.6947 1.0000
4.500 0.7699 0.02355 0.01309 -0.0651 0.6791 1.0000
4.750 0.7969 0.02352 0.01317 -0.0641 0.6628 1.0000
5.000 0.8177 0.02371 0.01349 -0.0624 0.6428 1.0000
5.250 0.8425 0.02368 0.01359 -0.0610 0.6229 1.0000
5.500 0.8641 0.02377 0.01388 -0.0593 0.5999 1.0000
5.750 0.8861 0.02377 0.01400 -0.0574 0.5744 1.0000
6.000 0.9065 0.02384 0.01416 -0.0554 0.5448 1.0000
6.250 0.9267 0.02390 0.01428 -0.0532 0.5108 1.0000
6.500 0.9449 0.02413 0.01451 -0.0510 0.4715 1.0000
6.750 0.9617 0.02451 0.01487 -0.0485 0.4271 1.0000
7.000 0.9759 0.02517 0.01538 -0.0460 0.3788 1.0000
7.250 0.9875 0.02611 0.01610 -0.0433 0.3296 1.0000
7.500 0.9973 0.02730 0.01706 -0.0408 0.2844 1.0000
7.750 1.0057 0.02867 0.01822 -0.0382 0.2440 1.0000
8.000 1.0141 0.03013 0.01955 -0.0359 0.2091 1.0000
8.250 1.0226 0.03167 0.02098 -0.0336 0.1817 1.0000
8.500 1.0308 0.03327 0.02246 -0.0314 0.1607 1.0000
8.750 1.0399 0.03484 0.02409 -0.0293 0.1412 1.0000
9.000 1.0512 0.03647 0.02576 -0.0274 0.1269 1.0000
9.250 1.0663 0.03818 0.02754 -0.0260 0.1150 1.0000
9.500 1.0799 0.03990 0.02934 -0.0245 0.1036 1.0000
9.750 1.0938 0.04169 0.03114 -0.0232 0.0942 1.0000
10.000 1.1133 0.04370 0.03341 -0.0222 0.0857 1.0000
10.250 1.1268 0.04584 0.03574 -0.0209 0.0778 1.0000
10.500 1.1385 0.04791 0.03788 -0.0196 0.0713 1.0000
10.750 1.1507 0.05072 0.04114 -0.0182 0.0658 1.0000
11.000 1.1541 0.05301 0.04363 -0.0165 0.0608 1.0000
11.250 1.1592 0.05578 0.04651 -0.0151 0.0567 1.0000
11.500 1.1572 0.05928 0.05049 -0.0135 0.0542 1.0000
11.750 1.1513 0.06275 0.05429 -0.0121 0.0518 1.0000
12.000 1.1447 0.06600 0.05776 -0.0112 0.0495 1.0000
12.250 1.1420 0.06892 0.06071 -0.0107 0.0471 1.0000
12.500 1.1319 0.07313 0.06510 -0.0106 0.0459 1.0000
12.750 1.1137 0.07826 0.07056 -0.0113 0.0455 1.0000
13.000 1.0948 0.08391 0.07649 -0.0130 0.0453 1.0000
13.250 1.0738 0.09029 0.08310 -0.0155 0.0453 1.0000
13.500 1.0531 0.09722 0.09021 -0.0189 0.0455 1.0000
13.750 1.0317 0.10493 0.09806 -0.0232 0.0458 1.0000
14.000 1.0111 0.11328 0.10652 -0.0281 0.0462 1.0000
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Polar data table (+)
Polar graphs
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