S4095 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4095-il) Xfoil prediction polar at RE=200,000 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: 200,000 Max Cl/Cd: 53.48 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4095-il-200000-n5.txt Download as CSV file: xf-s4095-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4845 0.11218 0.10891 0.0109 1.0007 0.0244
-9.250 -0.4864 0.10760 0.10435 0.0098 1.0007 0.0230
-8.750 -0.6365 0.10368 0.10030 0.0189 1.0007 0.0196
-8.500 -0.6389 0.09953 0.09618 0.0175 1.0007 0.0193
-8.250 -0.6405 0.09462 0.09129 0.0144 1.0007 0.0191
-8.000 -0.6379 0.08883 0.08551 0.0094 1.0007 0.0188
-7.750 -0.6314 0.08208 0.07872 0.0029 1.0007 0.0185
-7.500 -0.6201 0.07377 0.07032 -0.0052 1.0007 0.0185
-7.250 -0.6026 0.06318 0.05950 -0.0146 1.0007 0.0188
-7.000 -0.5798 0.05200 0.04788 -0.0224 1.0007 0.0187
-6.750 -0.5524 0.04198 0.03717 -0.0283 1.0007 0.0182
-6.500 -0.5212 0.03485 0.02921 -0.0321 1.0007 0.0180
-6.250 -0.4897 0.03054 0.02423 -0.0341 1.0007 0.0181
-6.000 -0.4585 0.02763 0.02081 -0.0355 1.0007 0.0184
-5.750 -0.4275 0.02546 0.01821 -0.0364 1.0007 0.0188
-5.500 -0.3969 0.02376 0.01621 -0.0372 1.0007 0.0192
-5.250 -0.3666 0.02246 0.01466 -0.0378 1.0007 0.0197
-5.000 -0.3367 0.02109 0.01319 -0.0385 1.0007 0.0208
-4.750 -0.3069 0.02018 0.01223 -0.0391 1.0007 0.0219
-4.500 -0.2769 0.01926 0.01123 -0.0397 1.0007 0.0225
-4.250 -0.2468 0.01844 0.01035 -0.0403 1.0007 0.0233
-4.000 -0.2166 0.01773 0.00958 -0.0408 1.0007 0.0242
-3.750 -0.1863 0.01713 0.00891 -0.0414 1.0007 0.0254
-3.500 -0.1559 0.01656 0.00829 -0.0420 1.0007 0.0270
-3.250 -0.1256 0.01608 0.00782 -0.0426 1.0007 0.0300
-3.000 -0.0953 0.01565 0.00743 -0.0433 1.0007 0.0373
-2.750 -0.0648 0.01519 0.00707 -0.0440 1.0007 0.0577
-2.500 -0.0301 0.01518 0.00717 -0.0456 0.9527 0.0924
-2.250 0.0012 0.01513 0.00722 -0.0463 0.9035 0.1350
-2.000 0.0278 0.01499 0.00723 -0.0458 0.8632 0.1967
-1.750 0.0542 0.01471 0.00720 -0.0455 0.8296 0.2887
-1.500 0.0811 0.01444 0.00716 -0.0452 0.8002 0.3868
-1.250 0.1082 0.01406 0.00715 -0.0451 0.7738 0.5217
-0.750 0.1518 0.01217 0.00623 -0.0409 0.7284 0.9993
-0.500 0.1808 0.01231 0.00614 -0.0410 0.7073 0.9993
-0.250 0.2101 0.01244 0.00607 -0.0412 0.6873 0.9993
0.000 0.2394 0.01257 0.00603 -0.0415 0.6681 0.9993
0.250 0.2687 0.01271 0.00600 -0.0417 0.6499 0.9993
0.500 0.2981 0.01286 0.00598 -0.0420 0.6323 0.9993
0.750 0.3276 0.01300 0.00598 -0.0423 0.6151 0.9993
1.000 0.3570 0.01314 0.00600 -0.0427 0.5980 0.9993
1.250 0.3865 0.01329 0.00602 -0.0430 0.5810 0.9993
1.500 0.4159 0.01344 0.00607 -0.0434 0.5640 0.9993
1.750 0.4453 0.01360 0.00612 -0.0437 0.5470 0.9993
2.000 0.4747 0.01377 0.00619 -0.0441 0.5301 0.9993
2.250 0.5041 0.01394 0.00626 -0.0444 0.5127 0.9993
2.500 0.5335 0.01411 0.00636 -0.0448 0.4947 0.9993
2.750 0.5628 0.01430 0.00647 -0.0452 0.4763 0.9993
3.000 0.5921 0.01450 0.00658 -0.0456 0.4578 0.9993
3.250 0.6213 0.01471 0.00672 -0.0460 0.4394 0.9993
3.500 0.6505 0.01493 0.00688 -0.0464 0.4200 0.9993
3.750 0.6797 0.01517 0.00705 -0.0468 0.4012 0.9993
4.000 0.7087 0.01544 0.00723 -0.0472 0.3827 0.9993
4.250 0.7378 0.01570 0.00744 -0.0476 0.3645 0.9993
4.500 0.7667 0.01597 0.00768 -0.0480 0.3462 0.9993
4.750 0.7956 0.01627 0.00793 -0.0484 0.3283 0.9993
5.000 0.8244 0.01659 0.00819 -0.0488 0.3107 0.9993
5.250 0.8532 0.01691 0.00850 -0.0492 0.2935 0.9993
5.500 0.8819 0.01725 0.00881 -0.0496 0.2762 0.9993
5.750 0.9105 0.01761 0.00914 -0.0500 0.2594 0.9993
6.000 0.9390 0.01798 0.00949 -0.0504 0.2432 0.9993
6.250 0.9673 0.01839 0.00989 -0.0508 0.2272 0.9993
6.500 0.9956 0.01880 0.01030 -0.0512 0.2124 0.9993
6.750 1.0237 0.01924 0.01073 -0.0516 0.1977 0.9993
7.000 1.0516 0.01970 0.01119 -0.0520 0.1833 0.9993
7.250 1.0794 0.02019 0.01170 -0.0524 0.1696 0.9993
7.500 1.1070 0.02070 0.01222 -0.0527 0.1560 0.9993
7.750 1.1345 0.02123 0.01277 -0.0530 0.1431 0.9993
8.000 1.1617 0.02179 0.01335 -0.0534 0.1310 0.9993
8.250 1.1887 0.02238 0.01399 -0.0536 0.1199 0.9993
8.500 1.2154 0.02301 0.01466 -0.0539 0.1095 0.9993
8.750 1.2416 0.02371 0.01537 -0.0541 0.0997 0.9993
9.000 1.2677 0.02438 0.01611 -0.0544 0.0896 0.9993
9.250 1.2934 0.02510 0.01687 -0.0545 0.0794 0.9993
9.500 1.3186 0.02587 0.01769 -0.0547 0.0691 0.9993
9.750 1.3433 0.02671 0.01855 -0.0548 0.0600 0.9993
10.000 1.3672 0.02762 0.01949 -0.0549 0.0519 0.9993
10.250 1.3910 0.02850 0.02044 -0.0548 0.0444 0.9993
10.500 1.4140 0.02945 0.02149 -0.0547 0.0383 0.9993
10.750 1.4357 0.03056 0.02269 -0.0545 0.0318 0.9993
11.000 1.4558 0.03186 0.02404 -0.0541 0.0247 0.9993
11.250 1.4738 0.03337 0.02561 -0.0535 0.0185 0.9993
11.750 1.5043 0.03668 0.02919 -0.0517 0.0128 0.9993
12.000 1.5156 0.03854 0.03120 -0.0504 0.0116 0.9993
12.250 1.5222 0.04071 0.03353 -0.0487 0.0109 0.9993
12.500 1.5261 0.04291 0.03597 -0.0467 0.0104 0.9993
12.750 1.5214 0.04550 0.03876 -0.0440 0.0101 0.9993
13.000 1.5103 0.04883 0.04229 -0.0415 0.0098 0.9993
13.250 1.5005 0.05290 0.04657 -0.0410 0.0097 0.9993
13.500 1.4905 0.05767 0.05155 -0.0418 0.0095 0.9993
13.750 1.4792 0.06310 0.05718 -0.0434 0.0093 0.9993
14.000 1.4660 0.06912 0.06341 -0.0456 0.0092 0.9993
14.250 1.4507 0.07569 0.07018 -0.0482 0.0092 0.9993
14.500 1.4336 0.08273 0.07741 -0.0511 0.0091 0.9993
14.750 1.4148 0.09018 0.08504 -0.0543 0.0091 0.9993
15.000 1.3949 0.09801 0.09304 -0.0578 0.0091 0.9993
15.250 1.3747 0.10603 0.10123 -0.0614 0.0091 0.9993
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Polar data table (+)
Polar graphs
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