S2048 (s2048-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 50,000 Max Cl/Cd: 37.45 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2048-il-50000-n5.txt Download as CSV file: xf-s2048-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2048
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4719 0.12355 0.11623 -0.0228 1.0000 0.1030
-10.250 -0.4791 0.12074 0.11352 -0.0257 1.0000 0.1040
-10.000 -0.4804 0.11723 0.11007 -0.0275 1.0000 0.1042
-9.750 -0.4810 0.11356 0.10648 -0.0291 1.0000 0.1042
-9.250 -0.4755 0.09820 0.09113 -0.0356 1.0000 0.0505
-9.000 -0.4770 0.09413 0.08713 -0.0371 1.0000 0.0504
-8.750 -0.4787 0.09018 0.08325 -0.0383 1.0000 0.0502
-8.500 -0.4838 0.08599 0.07915 -0.0399 1.0000 0.0501
-8.250 -0.4894 0.08209 0.07533 -0.0411 1.0000 0.0498
-8.000 -0.4952 0.07796 0.07125 -0.0426 1.0000 0.0495
-7.750 -0.4994 0.07410 0.06740 -0.0433 1.0000 0.0491
-7.500 -0.5040 0.07006 0.06334 -0.0441 1.0000 0.0488
-7.250 -0.5072 0.06604 0.05926 -0.0446 1.0000 0.0485
-7.000 -0.5081 0.06205 0.05516 -0.0448 1.0000 0.0480
-6.750 -0.5069 0.05803 0.05097 -0.0448 1.0000 0.0475
-6.500 -0.5030 0.05397 0.04667 -0.0447 1.0000 0.0471
-6.250 -0.4959 0.04997 0.04235 -0.0445 1.0000 0.0468
-6.000 -0.4856 0.04615 0.03813 -0.0441 1.0000 0.0467
-5.750 -0.4722 0.04258 0.03412 -0.0436 1.0000 0.0468
-5.500 -0.4560 0.03927 0.03033 -0.0429 1.0000 0.0472
-5.250 -0.4373 0.03633 0.02683 -0.0421 1.0000 0.0486
-5.000 -0.4173 0.03386 0.02377 -0.0414 1.0000 0.0516
-4.750 -0.3978 0.03200 0.02178 -0.0407 1.0000 0.0553
-4.500 -0.3757 0.02999 0.01941 -0.0397 1.0000 0.0571
-4.250 -0.3530 0.02821 0.01732 -0.0385 1.0000 0.0592
-4.000 -0.3303 0.02670 0.01550 -0.0372 1.0000 0.0618
-3.750 -0.3085 0.02540 0.01403 -0.0357 1.0000 0.0648
-3.500 -0.2874 0.02428 0.01285 -0.0345 1.0000 0.0699
-3.250 -0.2655 0.02333 0.01173 -0.0335 1.0000 0.0806
-3.000 -0.2434 0.02240 0.01078 -0.0328 1.0000 0.0999
-2.750 -0.2198 0.02116 0.00972 -0.0327 1.0000 0.1447
-2.500 -0.1991 0.01867 0.00920 -0.0327 1.0000 0.4526
-2.250 -0.1888 0.01821 0.00941 -0.0280 1.0000 0.6694
-2.000 -0.1784 0.01806 0.00940 -0.0234 1.0000 0.7667
-1.750 -0.1664 0.01786 0.00930 -0.0189 1.0000 0.8570
-1.500 -0.1213 0.01757 0.00879 -0.0219 1.0000 1.0000
-1.250 -0.1005 0.01760 0.00851 -0.0218 1.0000 1.0000
-1.000 -0.0786 0.01771 0.00832 -0.0218 1.0000 1.0000
-0.750 -0.0564 0.01787 0.00822 -0.0217 1.0000 1.0000
-0.500 -0.0271 0.01815 0.00822 -0.0230 0.9967 1.0000
-0.250 0.0103 0.01854 0.00837 -0.0258 0.9893 1.0000
0.000 0.0492 0.01899 0.00862 -0.0288 0.9822 1.0000
0.250 0.0853 0.01935 0.00883 -0.0312 0.9734 1.0000
0.500 0.1222 0.01973 0.00906 -0.0337 0.9647 1.0000
0.750 0.1621 0.02015 0.00938 -0.0366 0.9562 1.0000
1.000 0.1972 0.02045 0.00961 -0.0386 0.9454 1.0000
1.250 0.2336 0.02074 0.00986 -0.0408 0.9341 1.0000
1.500 0.2710 0.02100 0.01011 -0.0430 0.9222 1.0000
1.750 0.3092 0.02118 0.01031 -0.0451 0.9092 1.0000
2.000 0.3477 0.02129 0.01047 -0.0472 0.8948 1.0000
2.250 0.3872 0.02131 0.01056 -0.0492 0.8794 1.0000
2.500 0.4277 0.02123 0.01061 -0.0512 0.8638 1.0000
2.750 0.4687 0.02107 0.01057 -0.0530 0.8479 1.0000
3.000 0.5038 0.02091 0.01055 -0.0537 0.8300 1.0000
3.250 0.5371 0.02075 0.01053 -0.0539 0.8103 1.0000
3.500 0.5734 0.02049 0.01048 -0.0544 0.7906 1.0000
3.750 0.6033 0.02035 0.01050 -0.0539 0.7661 1.0000
4.000 0.6336 0.02019 0.01051 -0.0533 0.7387 1.0000
4.250 0.6637 0.02004 0.01050 -0.0526 0.7067 1.0000
4.500 0.6922 0.01996 0.01061 -0.0517 0.6673 1.0000
4.750 0.7197 0.01997 0.01067 -0.0505 0.6192 1.0000
5.000 0.7467 0.02012 0.01074 -0.0491 0.5616 1.0000
5.250 0.7707 0.02058 0.01096 -0.0475 0.4995 1.0000
5.500 0.7909 0.02134 0.01145 -0.0457 0.4392 1.0000
5.750 0.8094 0.02225 0.01211 -0.0440 0.3852 1.0000
6.000 0.8273 0.02323 0.01299 -0.0424 0.3367 1.0000
6.250 0.8447 0.02425 0.01387 -0.0409 0.2919 1.0000
6.500 0.8620 0.02532 0.01484 -0.0394 0.2489 1.0000
6.750 0.8792 0.02650 0.01594 -0.0380 0.2060 1.0000
7.000 0.8959 0.02782 0.01714 -0.0367 0.1648 1.0000
7.250 0.9144 0.02936 0.01861 -0.0355 0.1343 1.0000
7.500 0.9321 0.03092 0.02009 -0.0343 0.1108 1.0000
7.750 0.9523 0.03271 0.02195 -0.0332 0.0958 1.0000
8.000 0.9715 0.03454 0.02397 -0.0321 0.0825 1.0000
8.250 0.9913 0.03666 0.02617 -0.0311 0.0727 1.0000
8.500 1.0108 0.03889 0.02858 -0.0301 0.0642 1.0000
8.750 1.0279 0.04135 0.03139 -0.0288 0.0559 1.0000
9.000 1.0448 0.04413 0.03427 -0.0278 0.0511 1.0000
9.250 1.0564 0.04728 0.03796 -0.0261 0.0462 1.0000
9.500 1.0644 0.04985 0.04082 -0.0244 0.0418 1.0000
9.750 1.0721 0.05303 0.04415 -0.0229 0.0395 1.0000
10.000 1.0728 0.05702 0.04854 -0.0209 0.0384 1.0000
10.250 1.0656 0.06089 0.05290 -0.0185 0.0376 1.0000
10.500 1.0525 0.06464 0.05701 -0.0160 0.0371 1.0000
10.750 1.0362 0.06866 0.06134 -0.0143 0.0368 1.0000
11.000 1.0186 0.07304 0.06597 -0.0138 0.0368 1.0000
11.250 0.9985 0.07808 0.07123 -0.0146 0.0368 1.0000
11.500 0.9790 0.08380 0.07711 -0.0167 0.0372 1.0000
11.750 0.9594 0.09028 0.08373 -0.0202 0.0376 1.0000
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Polar data table (+)
Polar graphs
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