S3010-103-84 (s3010-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 50,000 Max Cl/Cd: 28.48 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3010-il-50000.txt Download as CSV file: xf-s3010-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S3010-103-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3930 0.10840 0.10170 -0.0086 1.0000 0.2349
-8.500 -0.3769 0.10398 0.09730 -0.0081 1.0000 0.2440
-8.250 -0.4009 0.10410 0.09759 -0.0110 1.0000 0.2519
-8.000 -0.3747 0.09885 0.09233 -0.0094 1.0000 0.2654
-7.750 -0.3622 0.09492 0.08844 -0.0091 1.0000 0.2746
-7.500 -0.3702 0.09297 0.08663 -0.0100 1.0000 0.2849
-7.250 -0.3719 0.09088 0.08463 -0.0100 1.0000 0.2979
-7.000 -0.3503 0.08632 0.08008 -0.0090 1.0000 0.3083
-6.750 -0.3484 0.08351 0.07737 -0.0086 1.0000 0.3201
-6.500 -0.3543 0.08139 0.07540 -0.0079 1.0000 0.3329
-6.250 -0.3613 0.07940 0.07356 -0.0069 1.0000 0.3472
-6.000 -0.3657 0.07730 0.07159 -0.0058 1.0000 0.3622
-5.750 -0.3690 0.07514 0.06957 -0.0039 1.0000 0.3776
-5.500 -0.4019 0.05686 0.05055 -0.0382 1.0000 0.1588
-5.250 -0.3937 0.05162 0.04511 -0.0389 1.0000 0.1409
-5.000 -0.3833 0.04610 0.03897 -0.0408 1.0000 0.1275
-4.750 -0.3702 0.04260 0.03523 -0.0406 1.0000 0.1235
-4.500 -0.3537 0.03889 0.03098 -0.0408 1.0000 0.1201
-4.250 -0.3356 0.03618 0.02784 -0.0406 1.0000 0.1208
-4.000 -0.3160 0.03388 0.02514 -0.0402 1.0000 0.1238
-3.750 -0.2942 0.03166 0.02243 -0.0398 1.0000 0.1266
-3.500 -0.2709 0.02972 0.01994 -0.0392 1.0000 0.1300
-3.250 -0.2501 0.02824 0.01847 -0.0386 1.0000 0.1405
-3.000 -0.2279 0.02690 0.01700 -0.0380 1.0000 0.1549
-2.750 -0.2059 0.02563 0.01577 -0.0372 1.0000 0.1809
-2.500 -0.1850 0.02449 0.01482 -0.0364 1.0000 0.2333
-2.250 -0.1637 0.02316 0.01408 -0.0356 1.0000 0.3360
-2.000 -0.1451 0.02183 0.01374 -0.0339 1.0000 0.5007
-1.750 -0.1387 0.02086 0.01387 -0.0285 1.0000 0.6969
-1.500 -0.1146 0.02005 0.01337 -0.0272 1.0000 1.0000
-1.250 -0.0826 0.02063 0.01333 -0.0302 0.9961 1.0000
-1.000 -0.0267 0.02164 0.01375 -0.0370 0.9807 1.0000
-0.750 0.0245 0.02256 0.01423 -0.0426 0.9646 1.0000
-0.500 0.0737 0.02343 0.01475 -0.0477 0.9485 1.0000
-0.250 0.1212 0.02426 0.01528 -0.0523 0.9323 1.0000
0.000 0.1673 0.02502 0.01581 -0.0564 0.9161 1.0000
0.250 0.2118 0.02572 0.01632 -0.0600 0.8999 1.0000
0.500 0.2557 0.02637 0.01681 -0.0633 0.8837 1.0000
0.750 0.2989 0.02696 0.01726 -0.0663 0.8677 1.0000
1.000 0.3420 0.02748 0.01768 -0.0691 0.8517 1.0000
1.250 0.3796 0.02799 0.01811 -0.0708 0.8356 1.0000
1.500 0.4122 0.02851 0.01857 -0.0716 0.8191 1.0000
1.750 0.4436 0.02902 0.01903 -0.0720 0.8025 1.0000
2.000 0.4744 0.02951 0.01948 -0.0722 0.7862 1.0000
2.250 0.5041 0.02998 0.01993 -0.0721 0.7700 1.0000
2.500 0.5330 0.03044 0.02037 -0.0719 0.7538 1.0000
2.750 0.5612 0.03088 0.02082 -0.0714 0.7376 1.0000
3.000 0.5888 0.03130 0.02123 -0.0707 0.7215 1.0000
3.250 0.6161 0.03169 0.02164 -0.0699 0.7053 1.0000
3.500 0.6430 0.03206 0.02204 -0.0689 0.6892 1.0000
3.750 0.6698 0.03238 0.02239 -0.0678 0.6729 1.0000
4.000 0.6964 0.03270 0.02273 -0.0667 0.6567 1.0000
4.250 0.7228 0.03298 0.02305 -0.0654 0.6404 1.0000
4.500 0.7494 0.03321 0.02334 -0.0641 0.6241 1.0000
4.750 0.7761 0.03342 0.02358 -0.0627 0.6078 1.0000
5.000 0.8032 0.03354 0.02374 -0.0612 0.5913 1.0000
5.250 0.8307 0.03362 0.02389 -0.0597 0.5749 1.0000
5.500 0.8587 0.03361 0.02390 -0.0582 0.5583 1.0000
5.750 0.8814 0.03416 0.02451 -0.0567 0.5401 1.0000
6.000 0.9021 0.03492 0.02536 -0.0553 0.5211 1.0000
6.250 0.9267 0.03528 0.02581 -0.0538 0.5029 1.0000
6.500 0.9534 0.03543 0.02599 -0.0523 0.4850 1.0000
6.750 0.9814 0.03545 0.02601 -0.0508 0.4671 1.0000
7.000 1.0045 0.03607 0.02670 -0.0494 0.4486 1.0000
7.250 1.0231 0.03713 0.02790 -0.0480 0.4291 1.0000
7.500 1.0463 0.03775 0.02857 -0.0466 0.4104 1.0000
7.750 1.0728 0.03803 0.02886 -0.0452 0.3919 1.0000
8.000 1.0980 0.03856 0.02937 -0.0438 0.3738 1.0000
8.250 1.1128 0.04011 0.03110 -0.0424 0.3554 1.0000
8.500 1.1305 0.04143 0.03255 -0.0410 0.3378 1.0000
8.750 1.1499 0.04257 0.03379 -0.0396 0.3205 1.0000
9.000 1.1699 0.04374 0.03502 -0.0383 0.3038 1.0000
9.250 1.1895 0.04498 0.03631 -0.0369 0.2877 1.0000
9.500 1.2053 0.04667 0.03811 -0.0355 0.2728 1.0000
9.750 1.2135 0.04912 0.04078 -0.0340 0.2598 1.0000
10.000 1.2193 0.05176 0.04365 -0.0324 0.2479 1.0000
10.250 1.2307 0.05407 0.04607 -0.0311 0.2366 1.0000
10.500 1.2485 0.05576 0.04780 -0.0299 0.2242 1.0000
10.750 1.2170 0.06154 0.05400 -0.0279 0.2211 1.0000
11.000 1.1716 0.06844 0.06112 -0.0267 0.2215 1.0000
11.250 1.1141 0.07812 0.07082 -0.0287 0.2245 1.0000
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Polar data table (+)
Polar graphs
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