S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=200,000 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: 200,000 Max Cl/Cd: 59.26 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4094-il-200000.txt Download as CSV file: xf-s4094-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5710 0.09431 0.09108 0.0075 1.0004 0.0515
-7.750 -0.5689 0.09008 0.08687 0.0044 1.0004 0.0528
-7.500 -0.5636 0.08491 0.08171 -0.0010 1.0004 0.0547
-7.250 -0.5525 0.07354 0.06993 -0.0222 1.0004 0.0591
-7.000 -0.5455 0.06580 0.06215 -0.0250 1.0004 0.0602
-6.750 -0.5301 0.06309 0.05952 -0.0241 1.0004 0.0614
-6.500 -0.5127 0.06090 0.05735 -0.0240 1.0004 0.0639
-6.250 -0.4875 0.05282 0.04852 -0.0328 1.0004 0.0730
-6.000 -0.4368 0.03818 0.03448 -0.0329 1.0004 0.0753
-5.750 -0.4165 0.03490 0.03112 -0.0340 1.0004 0.0783
-5.500 -0.4024 0.03193 0.02612 -0.0391 1.0004 0.0451
-5.250 -0.3678 0.02560 0.01866 -0.0404 1.0004 0.0385
-5.000 -0.3370 0.02355 0.01625 -0.0409 1.0004 0.0381
-4.750 -0.3073 0.02144 0.01400 -0.0415 1.0004 0.0396
-4.500 -0.2774 0.02016 0.01259 -0.0420 1.0004 0.0413
-4.250 -0.2472 0.01873 0.01103 -0.0423 1.0004 0.0421
-4.000 -0.2172 0.01753 0.00975 -0.0426 1.0004 0.0435
-3.750 -0.1872 0.01653 0.00870 -0.0429 1.0004 0.0456
-3.500 -0.1574 0.01551 0.00765 -0.0433 1.0004 0.0486
-3.250 -0.1276 0.01475 0.00697 -0.0439 1.0004 0.0564
-3.000 -0.0972 0.01381 0.00615 -0.0445 1.0004 0.0764
-2.750 -0.0671 0.01285 0.00564 -0.0455 1.0004 0.1604
-2.500 -0.0380 0.01228 0.00552 -0.0465 1.0004 0.2537
-2.250 -0.0011 0.01165 0.00557 -0.0492 0.9853 0.4167
-2.000 0.0354 0.01083 0.00563 -0.0511 0.9545 0.6404
-1.750 0.0543 0.01026 0.00569 -0.0476 0.9196 0.8484
-1.500 0.0815 0.00979 0.00514 -0.0463 0.8853 0.9996
-1.250 0.1070 0.00994 0.00505 -0.0453 0.8579 0.9996
-1.000 0.1333 0.01010 0.00496 -0.0447 0.8342 0.9996
-0.750 0.1605 0.01025 0.00490 -0.0442 0.8125 0.9996
-0.500 0.1879 0.01041 0.00484 -0.0439 0.7933 0.9996
-0.250 0.2162 0.01055 0.00481 -0.0438 0.7742 0.9996
0.000 0.2447 0.01070 0.00479 -0.0437 0.7563 0.9996
0.250 0.2732 0.01086 0.00478 -0.0437 0.7393 0.9996
0.500 0.3018 0.01101 0.00479 -0.0437 0.7229 0.9996
0.750 0.3305 0.01117 0.00481 -0.0438 0.7070 0.9996
1.000 0.3593 0.01133 0.00484 -0.0438 0.6913 0.9996
1.250 0.3882 0.01149 0.00488 -0.0439 0.6758 0.9996
1.500 0.4170 0.01165 0.00494 -0.0440 0.6604 0.9996
1.750 0.4459 0.01181 0.00500 -0.0442 0.6449 0.9996
2.000 0.4748 0.01197 0.00507 -0.0443 0.6294 0.9996
2.250 0.5036 0.01214 0.00515 -0.0444 0.6137 0.9996
2.500 0.5325 0.01232 0.00524 -0.0446 0.5978 0.9996
2.750 0.5614 0.01248 0.00535 -0.0447 0.5813 0.9996
3.000 0.5904 0.01264 0.00546 -0.0449 0.5640 0.9996
3.250 0.6193 0.01281 0.00558 -0.0451 0.5465 0.9996
3.500 0.6481 0.01299 0.00572 -0.0453 0.5285 0.9996
3.750 0.6768 0.01319 0.00584 -0.0455 0.5104 0.9996
4.000 0.7055 0.01339 0.00599 -0.0457 0.4916 0.9996
4.250 0.7343 0.01359 0.00616 -0.0459 0.4714 0.9996
4.500 0.7628 0.01383 0.00635 -0.0461 0.4516 0.9996
4.750 0.7913 0.01410 0.00656 -0.0463 0.4313 0.9996
5.000 0.8198 0.01438 0.00679 -0.0465 0.4104 0.9996
5.250 0.8479 0.01473 0.00707 -0.0467 0.3905 0.9996
5.500 0.8763 0.01505 0.00737 -0.0470 0.3695 0.9996
5.750 0.9043 0.01542 0.00769 -0.0472 0.3492 0.9996
6.000 0.9322 0.01583 0.00804 -0.0474 0.3294 0.9996
6.250 0.9602 0.01622 0.00844 -0.0476 0.3093 0.9996
6.500 0.9878 0.01667 0.00885 -0.0479 0.2903 0.9996
6.750 1.0151 0.01716 0.00929 -0.0481 0.2717 0.9996
7.000 1.0426 0.01762 0.00978 -0.0483 0.2529 0.9996
7.250 1.0696 0.01814 0.01029 -0.0484 0.2348 0.9996
7.500 1.0963 0.01871 0.01082 -0.0486 0.2176 0.9996
7.750 1.1226 0.01935 0.01141 -0.0487 0.2011 0.9996
8.000 1.1489 0.01994 0.01205 -0.0488 0.1847 0.9996
8.250 1.1748 0.02059 0.01273 -0.0489 0.1694 0.9996
8.500 1.2002 0.02132 0.01347 -0.0489 0.1552 0.9996
8.750 1.2251 0.02210 0.01427 -0.0488 0.1420 0.9996
9.000 1.2493 0.02295 0.01515 -0.0487 0.1295 0.9996
9.250 1.2727 0.02388 0.01607 -0.0485 0.1178 0.9996
9.500 1.2958 0.02473 0.01696 -0.0482 0.1062 0.9996
9.750 1.3193 0.02543 0.01775 -0.0481 0.0947 0.9996
10.000 1.3421 0.02619 0.01862 -0.0479 0.0841 0.9996
10.250 1.3634 0.02713 0.01963 -0.0475 0.0749 0.9996
10.500 1.3825 0.02829 0.02083 -0.0468 0.0671 0.9996
10.750 1.4018 0.02933 0.02196 -0.0462 0.0589 0.9996
11.000 1.4191 0.03054 0.02329 -0.0453 0.0496 0.9996
11.250 1.4305 0.03230 0.02508 -0.0439 0.0392 0.9996
11.500 1.4376 0.03434 0.02721 -0.0419 0.0317 0.9996
11.750 1.4371 0.03683 0.02981 -0.0392 0.0281 0.9996
12.000 1.4369 0.03895 0.03209 -0.0365 0.0259 0.9996
12.250 1.4308 0.04147 0.03473 -0.0337 0.0246 0.9996
12.500 1.4226 0.04476 0.03812 -0.0321 0.0236 0.9996
12.750 1.4117 0.04884 0.04228 -0.0310 0.0228 0.9996
13.000 1.4097 0.05222 0.04588 -0.0308 0.0221 0.9996
13.250 1.4061 0.05595 0.04980 -0.0309 0.0215 0.9996
13.500 1.4015 0.05990 0.05393 -0.0312 0.0209 0.9996
13.750 1.3960 0.06408 0.05828 -0.0318 0.0204 0.9996
14.000 1.3897 0.06846 0.06283 -0.0326 0.0200 0.9996
14.250 1.3823 0.07306 0.06759 -0.0336 0.0197 0.9996
14.500 1.3742 0.07787 0.07255 -0.0348 0.0194 0.9996
14.750 1.3650 0.08292 0.07776 -0.0363 0.0192 0.9996
15.000 1.3546 0.08826 0.08327 -0.0381 0.0190 0.9996
15.250 1.3433 0.09389 0.08906 -0.0402 0.0188 0.9996
15.500 1.3311 0.09988 0.09521 -0.0427 0.0187 0.9996
15.750 1.3182 0.10628 0.10179 -0.0456 0.0186 0.9996
16.000 1.3041 0.11325 0.10895 -0.0492 0.0185 0.9996
16.250 1.2880 0.12101 0.11691 -0.0535 0.0186 0.9996
16.500 1.2675 0.13019 0.12631 -0.0590 0.0187 0.9996
16.750 1.2395 0.14193 0.13833 -0.0665 0.0191 0.9996
17.000 1.1989 0.15823 0.15493 -0.0773 0.0199 0.9996
17.250 1.0854 0.20534 0.20218 -0.1052 0.0236 0.9996
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Polar data table (+)
Polar graphs
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