S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 50,000 Max Cl/Cd: 31.34 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4096-il-50000-n5.txt Download as CSV file: xf-s4096-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4096 (designed for the E-flite UMX ASK-21 scale
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6522 0.11127 0.10434 0.0016 1.0011 0.0530
-9.000 -0.6600 0.10528 0.09840 -0.0016 1.0011 0.0521
-8.750 -0.6654 0.09809 0.09120 -0.0067 1.0011 0.0511
-8.500 -0.6692 0.09012 0.08314 -0.0120 1.0011 0.0499
-8.250 -0.6705 0.08154 0.07434 -0.0173 1.0011 0.0486
-8.000 -0.6657 0.07293 0.06530 -0.0223 1.0011 0.0475
-7.750 -0.6523 0.06533 0.05710 -0.0263 1.0011 0.0468
-7.500 -0.6320 0.05937 0.05055 -0.0291 1.0011 0.0467
-7.250 -0.6085 0.05546 0.04628 -0.0308 1.0011 0.0478
-7.000 -0.5829 0.05190 0.04232 -0.0324 1.0011 0.0497
-6.750 -0.5551 0.04822 0.03810 -0.0340 1.0011 0.0516
-6.500 -0.5258 0.04472 0.03399 -0.0352 1.0011 0.0528
-6.250 -0.4960 0.04167 0.03043 -0.0361 1.0011 0.0538
-6.000 -0.4659 0.03908 0.02736 -0.0366 1.0011 0.0552
-5.750 -0.4365 0.03684 0.02483 -0.0370 1.0011 0.0569
-5.500 -0.4084 0.03513 0.02309 -0.0375 1.0011 0.0605
-5.250 -0.3795 0.03365 0.02139 -0.0378 1.0011 0.0659
-5.000 -0.3509 0.03215 0.01977 -0.0379 1.0011 0.0709
-4.750 -0.3222 0.03082 0.01837 -0.0382 1.0011 0.0777
-4.500 -0.2934 0.02955 0.01706 -0.0385 1.0011 0.0899
-4.250 -0.2640 0.02822 0.01583 -0.0392 1.0011 0.1203
-4.000 -0.2351 0.02663 0.01494 -0.0403 1.0011 0.2180
-3.750 -0.2083 0.02541 0.01457 -0.0409 1.0011 0.3824
-3.250 -0.1612 0.02379 0.01400 -0.0385 1.0011 0.6310
-3.000 -0.1431 0.02304 0.01373 -0.0349 1.0011 0.7711
-2.750 -0.1082 0.02198 0.01281 -0.0352 1.0011 0.9800
-2.500 -0.0793 0.02170 0.01220 -0.0362 1.0011 0.9989
-2.250 -0.0515 0.02181 0.01201 -0.0369 1.0011 0.9989
-2.000 -0.0242 0.02200 0.01196 -0.0374 1.0011 0.9989
-1.750 0.0024 0.02230 0.01203 -0.0379 1.0011 0.9989
-1.500 0.0283 0.02270 0.01225 -0.0382 1.0011 0.9989
-1.250 0.0531 0.02324 0.01264 -0.0385 1.0011 0.9989
-1.000 0.0770 0.02392 0.01319 -0.0386 1.0011 0.9989
-0.750 0.0996 0.02478 0.01394 -0.0387 1.0011 0.9989
-0.500 0.1411 0.02488 0.01387 -0.0425 0.9898 0.9989
-0.250 0.1875 0.02468 0.01352 -0.0471 0.9744 0.9989
0.000 0.2325 0.02452 0.01323 -0.0513 0.9577 0.9989
0.250 0.2749 0.02441 0.01301 -0.0548 0.9383 0.9989
0.500 0.3159 0.02435 0.01285 -0.0579 0.9185 0.9989
0.750 0.3546 0.02435 0.01276 -0.0602 0.8986 0.9989
1.000 0.3885 0.02446 0.01279 -0.0615 0.8757 0.9989
1.250 0.4205 0.02461 0.01286 -0.0621 0.8543 0.9989
1.500 0.4499 0.02484 0.01302 -0.0623 0.8322 0.9989
1.750 0.4784 0.02509 0.01320 -0.0622 0.8111 0.9989
2.000 0.5061 0.02536 0.01340 -0.0618 0.7909 0.9989
2.250 0.5336 0.02565 0.01366 -0.0616 0.7700 0.9989
2.500 0.5608 0.02594 0.01391 -0.0612 0.7502 0.9989
2.750 0.5880 0.02624 0.01415 -0.0608 0.7311 0.9989
3.000 0.6154 0.02656 0.01448 -0.0606 0.7107 0.9989
3.250 0.6427 0.02688 0.01478 -0.0603 0.6911 0.9989
3.500 0.6699 0.02719 0.01507 -0.0600 0.6721 0.9989
3.750 0.6973 0.02753 0.01542 -0.0599 0.6517 0.9989
4.000 0.7246 0.02787 0.01580 -0.0597 0.6314 0.9989
4.250 0.7519 0.02820 0.01612 -0.0594 0.6118 0.9989
4.500 0.7792 0.02857 0.01654 -0.0593 0.5905 0.9989
4.750 0.8064 0.02893 0.01695 -0.0592 0.5695 0.9989
5.000 0.8336 0.02931 0.01735 -0.0590 0.5484 0.9989
5.250 0.8609 0.02971 0.01782 -0.0590 0.5260 0.9989
5.500 0.8880 0.03012 0.01827 -0.0588 0.5043 0.9989
5.750 0.9150 0.03057 0.01880 -0.0588 0.4810 0.9989
6.000 0.9418 0.03104 0.01929 -0.0587 0.4586 0.9989
6.250 0.9684 0.03156 0.01985 -0.0586 0.4352 0.9989
6.500 0.9947 0.03213 0.02049 -0.0585 0.4122 0.9989
6.750 1.0207 0.03275 0.02113 -0.0584 0.3895 0.9989
7.000 1.0465 0.03346 0.02190 -0.0583 0.3665 0.9989
7.250 1.0718 0.03420 0.02266 -0.0582 0.3445 0.9989
7.500 1.0969 0.03504 0.02361 -0.0581 0.3223 0.9989
7.750 1.1214 0.03592 0.02452 -0.0579 0.3010 0.9989
8.000 1.1455 0.03689 0.02557 -0.0578 0.2805 0.9989
8.250 1.1690 0.03793 0.02670 -0.0576 0.2604 0.9989
8.500 1.1918 0.03903 0.02787 -0.0573 0.2421 0.9989
8.750 1.2140 0.04023 0.02915 -0.0570 0.2244 0.9989
9.000 1.2357 0.04153 0.03059 -0.0566 0.2073 0.9989
9.250 1.2562 0.04291 0.03209 -0.0561 0.1914 0.9989
9.500 1.2760 0.04438 0.03369 -0.0555 0.1770 0.9989
9.750 1.2945 0.04595 0.03542 -0.0548 0.1635 0.9989
10.000 1.3122 0.04762 0.03721 -0.0540 0.1517 0.9989
10.250 1.3283 0.04933 0.03898 -0.0530 0.1409 0.9989
10.500 1.3432 0.05125 0.04115 -0.0519 0.1306 0.9989
10.750 1.3563 0.05338 0.04353 -0.0506 0.1214 0.9989
11.000 1.3683 0.05539 0.04557 -0.0493 0.1139 0.9989
11.250 1.3773 0.05793 0.04852 -0.0476 0.1065 0.9989
11.500 1.3850 0.06025 0.05091 -0.0459 0.1004 0.9989
11.750 1.3864 0.06324 0.05429 -0.0437 0.0945 0.9989
12.000 1.3910 0.06559 0.05664 -0.0418 0.0898 0.9989
12.250 1.3812 0.06937 0.06084 -0.0388 0.0859 0.9989
12.500 1.3677 0.07327 0.06504 -0.0360 0.0827 0.9989
12.750 1.3590 0.07682 0.06872 -0.0344 0.0793 0.9989
13.000 1.3527 0.08061 0.07259 -0.0334 0.0762 0.9989
13.250 1.3314 0.08678 0.07917 -0.0334 0.0745 0.9989
13.500 1.3094 0.09355 0.08629 -0.0347 0.0729 0.9989
13.750 1.2860 0.10110 0.09413 -0.0372 0.0717 0.9989
14.000 1.2587 0.11007 0.10337 -0.0411 0.0712 0.9989
14.250 1.2215 0.12218 0.11574 -0.0478 0.0723 0.9989
14.500 1.1743 0.13862 0.13233 -0.0578 0.0742 0.9989
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Polar data table (+)
Polar graphs
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