S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Reynolds number: 100,000 Max Cl/Cd: 47.1 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4094-il-100000-n5.txt Download as CSV file: xf-s4094-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4094 (root airfoil designed for and used on the
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5833 0.10021 0.09545 0.0044 1.0004 0.0338
-8.500 -0.5802 0.09655 0.09182 0.0039 1.0004 0.0332
-8.250 -0.5812 0.09225 0.08756 0.0020 1.0004 0.0326
-8.000 -0.5799 0.08708 0.08242 -0.0020 1.0004 0.0319
-7.750 -0.5763 0.08096 0.07628 -0.0074 1.0004 0.0312
-7.500 -0.5703 0.07378 0.06904 -0.0139 1.0004 0.0304
-7.250 -0.5614 0.06515 0.06023 -0.0210 1.0004 0.0294
-7.000 -0.5493 0.05474 0.04938 -0.0281 1.0004 0.0283
-6.750 -0.5308 0.04504 0.03888 -0.0334 1.0004 0.0275
-6.500 -0.5065 0.03967 0.03288 -0.0358 1.0004 0.0275
-6.250 -0.4804 0.03701 0.02992 -0.0371 1.0004 0.0285
-6.000 -0.4529 0.03441 0.02693 -0.0383 1.0004 0.0300
-5.750 -0.4238 0.03149 0.02349 -0.0393 1.0004 0.0311
-5.500 -0.3942 0.02879 0.02032 -0.0401 1.0004 0.0315
-5.250 -0.3644 0.02660 0.01773 -0.0407 1.0004 0.0321
-5.000 -0.3348 0.02479 0.01562 -0.0411 1.0004 0.0328
-4.750 -0.3054 0.02329 0.01387 -0.0414 1.0004 0.0338
-4.500 -0.2765 0.02186 0.01237 -0.0417 1.0004 0.0350
-4.250 -0.2476 0.02086 0.01137 -0.0422 1.0004 0.0375
-4.000 -0.2186 0.02005 0.01050 -0.0425 1.0004 0.0417
-3.750 -0.1894 0.01912 0.00952 -0.0429 1.0004 0.0457
-3.500 -0.1602 0.01831 0.00869 -0.0433 1.0004 0.0520
-3.250 -0.1308 0.01749 0.00791 -0.0438 1.0004 0.0664
-3.000 -0.1020 0.01675 0.00739 -0.0443 1.0004 0.1024
-2.750 -0.0739 0.01609 0.00712 -0.0450 1.0004 0.1701
-2.500 -0.0431 0.01547 0.00697 -0.0463 0.9895 0.2688
-2.250 -0.0055 0.01494 0.00683 -0.0487 0.9565 0.3837
-2.000 0.0290 0.01443 0.00675 -0.0500 0.9254 0.5199
-1.750 0.0552 0.01389 0.00673 -0.0488 0.8955 0.6840
-1.500 0.0745 0.01323 0.00647 -0.0451 0.8671 0.8954
-1.250 0.1068 0.01298 0.00599 -0.0456 0.8397 0.9996
-1.000 0.1343 0.01312 0.00586 -0.0452 0.8164 0.9996
-0.750 0.1617 0.01327 0.00576 -0.0448 0.7956 0.9996
-0.500 0.1895 0.01342 0.00569 -0.0445 0.7756 0.9996
-0.250 0.2175 0.01357 0.00563 -0.0444 0.7568 0.9996
0.000 0.2456 0.01373 0.00560 -0.0442 0.7392 0.9996
0.250 0.2737 0.01389 0.00559 -0.0441 0.7222 0.9996
0.500 0.3019 0.01406 0.00559 -0.0440 0.7058 0.9996
0.750 0.3303 0.01423 0.00561 -0.0439 0.6896 0.9996
1.000 0.3587 0.01440 0.00565 -0.0439 0.6735 0.9996
1.250 0.3872 0.01458 0.00571 -0.0440 0.6576 0.9996
1.500 0.4158 0.01477 0.00578 -0.0440 0.6418 0.9996
1.750 0.4443 0.01495 0.00587 -0.0441 0.6261 0.9996
2.000 0.4729 0.01515 0.00598 -0.0441 0.6102 0.9996
2.250 0.5015 0.01534 0.00610 -0.0442 0.5942 0.9996
2.500 0.5300 0.01555 0.00622 -0.0443 0.5780 0.9996
2.750 0.5585 0.01576 0.00638 -0.0444 0.5616 0.9996
3.000 0.5870 0.01597 0.00653 -0.0445 0.5450 0.9996
3.250 0.6154 0.01620 0.00669 -0.0445 0.5283 0.9996
3.500 0.6439 0.01642 0.00691 -0.0447 0.5102 0.9996
3.750 0.6724 0.01666 0.00711 -0.0448 0.4918 0.9996
4.000 0.7007 0.01691 0.00732 -0.0449 0.4732 0.9996
4.250 0.7288 0.01719 0.00754 -0.0450 0.4547 0.9996
4.500 0.7571 0.01747 0.00784 -0.0452 0.4349 0.9996
4.750 0.7851 0.01779 0.00812 -0.0453 0.4154 0.9996
5.000 0.8129 0.01814 0.00842 -0.0454 0.3964 0.9996
5.250 0.8408 0.01850 0.00881 -0.0456 0.3767 0.9996
5.500 0.8684 0.01890 0.00919 -0.0457 0.3573 0.9996
5.750 0.8958 0.01934 0.00959 -0.0458 0.3389 0.9996
6.000 0.9232 0.01978 0.01005 -0.0460 0.3197 0.9996
6.250 0.9504 0.02025 0.01056 -0.0461 0.3013 0.9996
6.500 0.9773 0.02077 0.01107 -0.0462 0.2832 0.9996
6.750 1.0039 0.02132 0.01162 -0.0463 0.2660 0.9996
7.000 1.0305 0.02188 0.01222 -0.0464 0.2485 0.9996
7.250 1.0568 0.02248 0.01289 -0.0465 0.2319 0.9996
7.500 1.0826 0.02312 0.01358 -0.0465 0.2158 0.9996
7.750 1.1081 0.02380 0.01431 -0.0465 0.2006 0.9996
8.000 1.1332 0.02453 0.01509 -0.0465 0.1857 0.9996
8.250 1.1578 0.02530 0.01592 -0.0464 0.1716 0.9996
8.500 1.1820 0.02612 0.01684 -0.0462 0.1582 0.9996
8.750 1.2055 0.02699 0.01779 -0.0460 0.1455 0.9996
9.000 1.2284 0.02792 0.01881 -0.0458 0.1340 0.9996
9.250 1.2504 0.02893 0.01989 -0.0454 0.1233 0.9996
9.500 1.2710 0.03004 0.02106 -0.0450 0.1138 0.9996
9.750 1.2920 0.03111 0.02234 -0.0444 0.1042 0.9996
10.000 1.3111 0.03235 0.02370 -0.0438 0.0963 0.9996
10.250 1.3284 0.03367 0.02511 -0.0429 0.0891 0.9996
10.500 1.3455 0.03498 0.02662 -0.0421 0.0809 0.9996
10.750 1.3598 0.03637 0.02812 -0.0411 0.0725 0.9996
11.000 1.3713 0.03786 0.02965 -0.0400 0.0638 0.9996
11.250 1.3834 0.03929 0.03132 -0.0389 0.0547 0.9996
11.500 1.3903 0.04112 0.03331 -0.0373 0.0486 0.9996
11.750 1.3918 0.04325 0.03557 -0.0354 0.0437 0.9996
12.000 1.3873 0.04567 0.03816 -0.0329 0.0398 0.9996
12.250 1.3816 0.04863 0.04130 -0.0315 0.0362 0.9996
12.500 1.3715 0.05253 0.04531 -0.0312 0.0339 0.9996
12.750 1.3637 0.05666 0.04966 -0.0315 0.0314 0.9996
13.000 1.3538 0.06137 0.05459 -0.0325 0.0295 0.9996
13.250 1.3418 0.06667 0.06007 -0.0342 0.0281 0.9996
13.500 1.3277 0.07254 0.06610 -0.0365 0.0271 0.9996
13.750 1.3117 0.07889 0.07259 -0.0391 0.0265 0.9996
14.000 1.2946 0.08561 0.07945 -0.0419 0.0260 0.9996
14.250 1.2784 0.09234 0.08633 -0.0447 0.0255 0.9996
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Polar data table (+)
Polar graphs
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