S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| 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: 500,000 Max Cl/Cd: 76.51 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4094-il-500000.txt Download as CSV file: xf-s4094-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5975 0.09723 0.09513 0.0094 1.0004 0.0227
-8.500 -0.6025 0.09155 0.08948 0.0056 1.0004 0.0227
-8.250 -0.6177 0.08289 0.08086 -0.0008 1.0004 0.0232
-8.000 -0.6105 0.07932 0.07727 -0.0034 1.0004 0.0236
-7.750 -0.6007 0.07524 0.07317 -0.0070 1.0004 0.0240
-7.500 -0.5890 0.07030 0.06818 -0.0116 1.0004 0.0245
-7.250 -0.5750 0.06446 0.06226 -0.0169 1.0004 0.0252
-7.000 -0.5580 0.05729 0.05492 -0.0228 1.0004 0.0266
-6.750 -0.5406 0.04192 0.03867 -0.0319 1.0004 0.0302
-6.500 -0.5171 0.03995 0.03669 -0.0327 1.0004 0.0310
-6.250 -0.4921 0.03786 0.03451 -0.0338 1.0004 0.0321
-6.000 -0.4580 0.02390 0.01893 -0.0368 1.0004 0.0216
-5.750 -0.4279 0.02146 0.01614 -0.0376 1.0004 0.0216
-5.500 -0.3975 0.01920 0.01357 -0.0383 1.0004 0.0213
-5.250 -0.3671 0.01750 0.01164 -0.0388 1.0004 0.0213
-5.000 -0.3370 0.01625 0.01025 -0.0392 1.0004 0.0215
-4.750 -0.3069 0.01526 0.00916 -0.0397 1.0004 0.0219
-4.500 -0.2768 0.01446 0.00828 -0.0401 1.0004 0.0223
-4.250 -0.2468 0.01379 0.00756 -0.0405 1.0004 0.0227
-4.000 -0.2166 0.01272 0.00644 -0.0412 1.0004 0.0238
-3.750 -0.1863 0.01217 0.00590 -0.0418 1.0004 0.0254
-3.500 -0.1536 0.01185 0.00556 -0.0429 0.9843 0.0269
-3.250 -0.1226 0.01176 0.00538 -0.0432 0.9325 0.0287
-3.000 -0.0981 0.01161 0.00509 -0.0419 0.8903 0.0321
-2.750 -0.0716 0.01141 0.00482 -0.0413 0.8570 0.0447
-2.500 -0.0436 0.01101 0.00459 -0.0413 0.8287 0.1059
-2.250 -0.0152 0.01080 0.00444 -0.0414 0.8034 0.1565
-2.000 0.0136 0.01054 0.00432 -0.0417 0.7804 0.2219
-1.750 0.0427 0.01028 0.00422 -0.0421 0.7596 0.3003
-1.500 0.0720 0.00996 0.00416 -0.0425 0.7401 0.4014
-1.250 0.1010 0.00953 0.00414 -0.0430 0.7223 0.5408
-1.000 0.1286 0.00898 0.00417 -0.0430 0.7060 0.7241
-0.750 0.1477 0.00841 0.00409 -0.0403 0.6912 0.9042
-0.500 0.1774 0.00795 0.00358 -0.0404 0.6758 0.9996
-0.250 0.2071 0.00805 0.00353 -0.0407 0.6614 0.9996
0.000 0.2368 0.00814 0.00351 -0.0410 0.6473 0.9996
0.250 0.2665 0.00824 0.00349 -0.0414 0.6337 0.9996
0.500 0.2962 0.00833 0.00349 -0.0417 0.6204 0.9996
0.750 0.3258 0.00843 0.00349 -0.0421 0.6071 0.9996
1.000 0.3554 0.00854 0.00351 -0.0424 0.5940 0.9996
1.250 0.3850 0.00865 0.00353 -0.0427 0.5807 0.9996
1.500 0.4146 0.00876 0.00355 -0.0431 0.5671 0.9996
1.750 0.4441 0.00888 0.00359 -0.0434 0.5532 0.9996
2.000 0.4737 0.00899 0.00364 -0.0438 0.5388 0.9996
2.250 0.5032 0.00911 0.00369 -0.0441 0.5240 0.9996
2.500 0.5326 0.00924 0.00375 -0.0444 0.5084 0.9996
2.750 0.5621 0.00937 0.00383 -0.0448 0.4920 0.9996
3.000 0.5915 0.00951 0.00391 -0.0451 0.4744 0.9996
3.250 0.6208 0.00967 0.00400 -0.0455 0.4561 0.9996
3.500 0.6501 0.00986 0.00411 -0.0458 0.4375 0.9996
3.750 0.6793 0.01006 0.00423 -0.0462 0.4188 0.9996
4.000 0.7085 0.01026 0.00437 -0.0466 0.3998 0.9996
4.250 0.7376 0.01048 0.00452 -0.0469 0.3807 0.9996
4.500 0.7666 0.01072 0.00470 -0.0473 0.3622 0.9996
4.750 0.7956 0.01097 0.00488 -0.0477 0.3436 0.9996
5.000 0.8245 0.01122 0.00507 -0.0480 0.3251 0.9996
5.250 0.8533 0.01149 0.00529 -0.0484 0.3067 0.9996
5.500 0.8821 0.01177 0.00552 -0.0488 0.2895 0.9996
5.750 0.9108 0.01208 0.00576 -0.0491 0.2720 0.9996
6.000 0.9394 0.01237 0.00602 -0.0495 0.2553 0.9996
6.250 0.9679 0.01269 0.00630 -0.0498 0.2385 0.9996
6.500 0.9963 0.01303 0.00659 -0.0502 0.2218 0.9996
6.750 1.0245 0.01339 0.00690 -0.0505 0.2053 0.9996
7.000 1.0526 0.01378 0.00725 -0.0508 0.1890 0.9996
7.250 1.0806 0.01418 0.00760 -0.0511 0.1743 0.9996
7.500 1.1084 0.01459 0.00798 -0.0514 0.1604 0.9996
7.750 1.1361 0.01503 0.00839 -0.0517 0.1461 0.9996
8.000 1.1635 0.01548 0.00881 -0.0520 0.1315 0.9996
8.250 1.1907 0.01596 0.00924 -0.0522 0.1179 0.9996
8.500 1.2177 0.01647 0.00972 -0.0525 0.1053 0.9996
8.750 1.2444 0.01698 0.01022 -0.0527 0.0936 0.9996
9.000 1.2711 0.01749 0.01072 -0.0528 0.0833 0.9996
9.250 1.2973 0.01804 0.01126 -0.0530 0.0733 0.9996
9.500 1.3232 0.01862 0.01183 -0.0531 0.0641 0.9996
9.750 1.3486 0.01926 0.01246 -0.0531 0.0560 0.9996
10.000 1.3737 0.01991 0.01311 -0.0531 0.0485 0.9996
10.250 1.3986 0.02053 0.01376 -0.0531 0.0415 0.9996
10.500 1.4222 0.02136 0.01456 -0.0529 0.0322 0.9996
10.750 1.4427 0.02266 0.01577 -0.0525 0.0190 0.9996
11.000 1.4623 0.02400 0.01713 -0.0518 0.0138 0.9996
11.250 1.4823 0.02512 0.01837 -0.0511 0.0121 0.9996
11.500 1.5013 0.02625 0.01959 -0.0504 0.0110 0.9996
11.750 1.5154 0.02785 0.02130 -0.0491 0.0100 0.9996
12.000 1.5308 0.02910 0.02268 -0.0479 0.0095 0.9996
12.250 1.5438 0.03046 0.02418 -0.0464 0.0092 0.9996
12.500 1.5531 0.03200 0.02585 -0.0445 0.0088 0.9996
12.750 1.5583 0.03373 0.02771 -0.0423 0.0086 0.9996
13.000 1.5543 0.03575 0.02987 -0.0390 0.0084 0.9996
13.250 1.5475 0.03840 0.03266 -0.0366 0.0083 0.9996
13.500 1.5417 0.04165 0.03607 -0.0357 0.0081 0.9996
13.750 1.5353 0.04553 0.04010 -0.0359 0.0080 0.9996
14.000 1.5274 0.04996 0.04469 -0.0368 0.0079 0.9996
14.250 1.5176 0.05493 0.04981 -0.0382 0.0078 0.9996
14.500 1.5057 0.06035 0.05538 -0.0399 0.0078 0.9996
14.750 1.4919 0.06615 0.06133 -0.0419 0.0077 0.9996
15.000 1.4770 0.07221 0.06754 -0.0440 0.0077 0.9996
15.250 1.4610 0.07850 0.07396 -0.0462 0.0077 0.9996
15.500 1.4446 0.08496 0.08056 -0.0485 0.0076 0.9996
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Polar data table (+)
Polar graphs
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