S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Reynolds number: 100,000 Max Cl/Cd: 43.52 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4095-il-100000-n5.txt Download as CSV file: xf-s4095-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4095 (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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5036 0.08950 0.08500 -0.0010 1.0007 0.0332
-8.000 -0.6178 0.09309 0.08838 0.0044 1.0007 0.0334
-7.750 -0.6107 0.08865 0.08393 0.0022 1.0007 0.0327
-7.500 -0.6018 0.08314 0.07838 -0.0019 1.0007 0.0320
-7.250 -0.5897 0.07667 0.07183 -0.0074 1.0007 0.0311
-7.000 -0.5735 0.06916 0.06415 -0.0137 1.0007 0.0301
-6.750 -0.5519 0.06001 0.05466 -0.0210 1.0007 0.0289
-6.500 -0.5242 0.04946 0.04343 -0.0280 1.0007 0.0278
-6.250 -0.4932 0.04204 0.03520 -0.0325 1.0007 0.0275
-6.000 -0.4640 0.03888 0.03165 -0.0344 1.0007 0.0283
-5.750 -0.4338 0.03609 0.02847 -0.0360 1.0007 0.0299
-5.500 -0.4021 0.03296 0.02479 -0.0376 1.0007 0.0310
-5.250 -0.3703 0.03014 0.02146 -0.0387 1.0007 0.0315
-5.000 -0.3390 0.02787 0.01878 -0.0395 1.0007 0.0321
-4.750 -0.3081 0.02601 0.01659 -0.0401 1.0007 0.0329
-4.500 -0.2777 0.02450 0.01483 -0.0406 1.0007 0.0338
-4.250 -0.2480 0.02306 0.01336 -0.0412 1.0007 0.0353
-4.000 -0.2183 0.02212 0.01241 -0.0417 1.0007 0.0384
-3.750 -0.1884 0.02129 0.01148 -0.0422 1.0007 0.0429
-3.500 -0.1584 0.02032 0.01050 -0.0428 1.0007 0.0474
-3.250 -0.1282 0.01952 0.00965 -0.0433 1.0007 0.0559
-3.000 -0.0980 0.01868 0.00895 -0.0440 1.0007 0.0780
-2.750 -0.0683 0.01804 0.00853 -0.0447 1.0007 0.1237
-2.500 -0.0392 0.01734 0.00829 -0.0455 1.0007 0.2036
-2.250 -0.0101 0.01676 0.00805 -0.0461 1.0007 0.2874
-2.000 0.0187 0.01616 0.00791 -0.0467 1.0007 0.4057
-1.750 0.0451 0.01537 0.00788 -0.0466 1.0007 0.5996
-1.500 0.0695 0.01394 0.00732 -0.0445 0.9684 0.9993
-1.250 0.1079 0.01418 0.00728 -0.0467 0.9305 0.9993
-1.000 0.1411 0.01440 0.00723 -0.0476 0.8928 0.9993
-0.750 0.1698 0.01462 0.00719 -0.0473 0.8584 0.9993
-0.500 0.1969 0.01482 0.00716 -0.0467 0.8277 0.9993
-0.250 0.2241 0.01502 0.00713 -0.0462 0.8001 0.9993
0.000 0.2515 0.01521 0.00711 -0.0458 0.7749 0.9993
0.250 0.2791 0.01540 0.00710 -0.0455 0.7517 0.9993
0.500 0.3073 0.01558 0.00711 -0.0453 0.7293 0.9993
0.750 0.3355 0.01577 0.00713 -0.0452 0.7084 0.9993
1.000 0.3638 0.01597 0.00717 -0.0452 0.6883 0.9993
1.250 0.3923 0.01616 0.00724 -0.0452 0.6685 0.9993
1.500 0.4207 0.01637 0.00731 -0.0452 0.6494 0.9993
1.750 0.4492 0.01659 0.00740 -0.0452 0.6308 0.9993
2.000 0.4780 0.01679 0.00752 -0.0454 0.6118 0.9993
2.250 0.5067 0.01701 0.00764 -0.0455 0.5930 0.9993
2.500 0.5353 0.01724 0.00777 -0.0456 0.5746 0.9993
2.750 0.5641 0.01748 0.00793 -0.0458 0.5560 0.9993
3.000 0.5929 0.01771 0.00811 -0.0460 0.5368 0.9993
3.250 0.6216 0.01796 0.00829 -0.0462 0.5177 0.9993
3.500 0.6502 0.01822 0.00850 -0.0464 0.4988 0.9993
3.750 0.6790 0.01848 0.00873 -0.0466 0.4787 0.9993
4.000 0.7075 0.01877 0.00896 -0.0468 0.4589 0.9993
4.250 0.7360 0.01907 0.00921 -0.0471 0.4394 0.9993
4.500 0.7646 0.01939 0.00952 -0.0473 0.4190 0.9993
4.750 0.7929 0.01974 0.00982 -0.0476 0.3992 0.9993
5.000 0.8213 0.02011 0.01016 -0.0478 0.3797 0.9993
5.250 0.8496 0.02050 0.01057 -0.0481 0.3599 0.9993
5.500 0.8777 0.02092 0.01096 -0.0484 0.3410 0.9993
5.750 0.9057 0.02136 0.01139 -0.0487 0.3222 0.9993
6.000 0.9337 0.02182 0.01187 -0.0490 0.3035 0.9993
6.250 0.9614 0.02232 0.01239 -0.0493 0.2851 0.9993
6.500 0.9890 0.02285 0.01292 -0.0495 0.2677 0.9993
6.750 1.0164 0.02341 0.01350 -0.0498 0.2505 0.9993
7.000 1.0437 0.02399 0.01412 -0.0501 0.2337 0.9993
7.250 1.0707 0.02460 0.01481 -0.0503 0.2175 0.9993
7.500 1.0975 0.02526 0.01552 -0.0505 0.2021 0.9993
7.750 1.1240 0.02596 0.01628 -0.0508 0.1873 0.9993
8.000 1.1501 0.02671 0.01708 -0.0509 0.1730 0.9993
8.250 1.1759 0.02750 0.01797 -0.0511 0.1596 0.9993
8.500 1.2012 0.02834 0.01889 -0.0512 0.1467 0.9993
8.750 1.2260 0.02925 0.01988 -0.0513 0.1351 0.9993
9.000 1.2502 0.03022 0.02092 -0.0513 0.1243 0.9993
9.250 1.2737 0.03126 0.02205 -0.0512 0.1143 0.9993
9.500 1.2970 0.03232 0.02331 -0.0510 0.1048 0.9993
9.750 1.3189 0.03351 0.02462 -0.0508 0.0965 0.9993
10.000 1.3398 0.03478 0.02601 -0.0504 0.0892 0.9993
10.250 1.3603 0.03609 0.02751 -0.0500 0.0813 0.9993
10.500 1.3788 0.03742 0.02895 -0.0496 0.0729 0.9993
10.750 1.3957 0.03879 0.03039 -0.0491 0.0636 0.9993
11.000 1.4129 0.04013 0.03196 -0.0486 0.0540 0.9993
11.250 1.4267 0.04182 0.03387 -0.0477 0.0470 0.9993
11.500 1.4355 0.04389 0.03604 -0.0464 0.0414 0.9993
11.750 1.4420 0.04607 0.03845 -0.0449 0.0358 0.9993
12.000 1.4401 0.04888 0.04139 -0.0429 0.0323 0.9993
12.250 1.4314 0.05196 0.04472 -0.0402 0.0298 0.9993
12.500 1.4189 0.05584 0.04880 -0.0387 0.0282 0.9993
12.750 1.4058 0.06057 0.05372 -0.0388 0.0270 0.9993
13.000 1.3908 0.06620 0.05951 -0.0402 0.0261 0.9993
13.250 1.3752 0.07236 0.06583 -0.0423 0.0254 0.9993
13.500 1.3607 0.07868 0.07240 -0.0446 0.0247 0.9993
13.750 1.3447 0.08544 0.07937 -0.0473 0.0242 0.9993
14.000 1.3277 0.09253 0.08667 -0.0503 0.0237 0.9993
14.250 1.3104 0.09990 0.09422 -0.0536 0.0234 0.9993
14.500 1.2929 0.10745 0.10195 -0.0571 0.0231 0.9993
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Polar data table (+)
Polar graphs
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