S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 200,000 Max Cl/Cd: 48.29 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4096-il-200000-n5.txt Download as CSV file: xf-s4096-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4096 (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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7035 0.10396 0.10053 0.0075 1.0011 0.0179
-9.500 -0.7713 0.07419 0.07055 -0.0129 1.0011 0.0167
-9.250 -0.7861 0.06224 0.05802 -0.0191 1.0011 0.0168
-9.000 -0.7818 0.05390 0.04903 -0.0224 1.0011 0.0170
-8.750 -0.7657 0.04812 0.04272 -0.0244 1.0011 0.0171
-8.500 -0.7441 0.04361 0.03773 -0.0260 1.0011 0.0173
-8.250 -0.7194 0.04020 0.03391 -0.0274 1.0011 0.0175
-8.000 -0.6929 0.03742 0.03078 -0.0285 1.0011 0.0178
-7.750 -0.6653 0.03505 0.02808 -0.0295 1.0011 0.0182
-7.500 -0.6370 0.03298 0.02571 -0.0304 1.0011 0.0185
-7.250 -0.6083 0.03127 0.02374 -0.0312 1.0011 0.0191
-7.000 -0.5793 0.02987 0.02211 -0.0319 1.0011 0.0200
-6.750 -0.5499 0.02844 0.02044 -0.0326 1.0011 0.0208
-6.500 -0.5204 0.02707 0.01886 -0.0332 1.0011 0.0212
-6.250 -0.4910 0.02587 0.01749 -0.0338 1.0011 0.0215
-6.000 -0.4614 0.02484 0.01634 -0.0344 1.0011 0.0219
-5.750 -0.4322 0.02364 0.01511 -0.0351 1.0011 0.0225
-5.500 -0.4026 0.02276 0.01420 -0.0358 1.0011 0.0232
-5.250 -0.3729 0.02206 0.01346 -0.0365 1.0011 0.0241
-5.000 -0.3430 0.02147 0.01283 -0.0373 1.0011 0.0254
-4.750 -0.3130 0.02096 0.01228 -0.0380 1.0011 0.0272
-4.500 -0.2828 0.02042 0.01169 -0.0387 1.0011 0.0288
-4.250 -0.2526 0.01994 0.01119 -0.0395 1.0011 0.0309
-4.000 -0.2223 0.01956 0.01077 -0.0403 1.0011 0.0341
-3.750 -0.1920 0.01916 0.01040 -0.0410 1.0011 0.0419
-3.500 -0.1617 0.01869 0.01009 -0.0419 1.0011 0.0726
-3.250 -0.1316 0.01818 0.00990 -0.0430 1.0011 0.1391
-3.000 -0.1016 0.01769 0.00983 -0.0441 1.0011 0.2278
-2.750 -0.0716 0.01737 0.00983 -0.0451 1.0011 0.3069
-2.500 -0.0388 0.01728 0.01005 -0.0467 0.9884 0.3918
-2.250 -0.0035 0.01691 0.01021 -0.0489 0.9578 0.5191
-2.000 0.0284 0.01661 0.01036 -0.0497 0.9258 0.6400
-1.750 0.0535 0.01637 0.01046 -0.0486 0.8943 0.7497
-1.500 0.0714 0.01603 0.01036 -0.0451 0.8659 0.8780
-1.250 0.1006 0.01518 0.00942 -0.0449 0.8368 0.9989
-1.000 0.1292 0.01526 0.00930 -0.0449 0.8123 0.9989
-0.750 0.1580 0.01535 0.00919 -0.0451 0.7902 0.9989
-0.500 0.1871 0.01544 0.00911 -0.0454 0.7691 0.9989
-0.250 0.2164 0.01554 0.00904 -0.0458 0.7495 0.9989
0.000 0.2459 0.01565 0.00898 -0.0462 0.7312 0.9989
0.250 0.2756 0.01576 0.00895 -0.0467 0.7134 0.9989
0.500 0.3053 0.01587 0.00893 -0.0472 0.6962 0.9989
0.750 0.3350 0.01598 0.00892 -0.0477 0.6796 0.9989
1.000 0.3648 0.01610 0.00893 -0.0483 0.6636 0.9989
1.250 0.3946 0.01623 0.00895 -0.0489 0.6479 0.9989
1.500 0.4244 0.01636 0.00898 -0.0494 0.6324 0.9989
1.750 0.4542 0.01649 0.00903 -0.0500 0.6169 0.9989
2.000 0.4840 0.01663 0.00908 -0.0506 0.6013 0.9989
2.250 0.5138 0.01678 0.00916 -0.0512 0.5856 0.9989
2.500 0.5435 0.01694 0.00924 -0.0518 0.5696 0.9989
2.750 0.5732 0.01710 0.00933 -0.0524 0.5535 0.9989
3.000 0.6028 0.01727 0.00944 -0.0530 0.5367 0.9989
3.250 0.6325 0.01744 0.00956 -0.0536 0.5191 0.9989
3.500 0.6621 0.01762 0.00968 -0.0542 0.5005 0.9989
3.750 0.6916 0.01782 0.00984 -0.0548 0.4811 0.9989
4.000 0.7210 0.01805 0.00999 -0.0554 0.4612 0.9989
4.250 0.7504 0.01828 0.01016 -0.0560 0.4402 0.9989
4.500 0.7796 0.01855 0.01036 -0.0565 0.4188 0.9989
4.750 0.8088 0.01883 0.01059 -0.0571 0.3981 0.9989
5.000 0.8378 0.01913 0.01083 -0.0577 0.3773 0.9989
5.250 0.8668 0.01947 0.01109 -0.0583 0.3567 0.9989
5.500 0.8957 0.01979 0.01140 -0.0589 0.3362 0.9989
5.750 0.9244 0.02016 0.01171 -0.0595 0.3158 0.9989
6.000 0.9531 0.02054 0.01204 -0.0601 0.2964 0.9989
6.250 0.9816 0.02093 0.01240 -0.0606 0.2766 0.9989
6.500 1.0099 0.02136 0.01280 -0.0612 0.2579 0.9989
6.750 1.0381 0.02181 0.01321 -0.0617 0.2402 0.9989
7.000 1.0663 0.02226 0.01364 -0.0623 0.2227 0.9989
7.250 1.0942 0.02274 0.01412 -0.0628 0.2053 0.9989
7.500 1.1218 0.02325 0.01461 -0.0633 0.1888 0.9989
7.750 1.1492 0.02380 0.01514 -0.0637 0.1725 0.9989
8.000 1.1764 0.02439 0.01571 -0.0642 0.1570 0.9989
8.250 1.2032 0.02499 0.01632 -0.0646 0.1425 0.9989
8.500 1.2299 0.02561 0.01694 -0.0649 0.1295 0.9989
8.750 1.2564 0.02624 0.01761 -0.0652 0.1180 0.9989
9.000 1.2825 0.02691 0.01832 -0.0655 0.1073 0.9989
9.250 1.3082 0.02763 0.01909 -0.0657 0.0973 0.9989
9.500 1.3332 0.02843 0.01991 -0.0659 0.0880 0.9989
9.750 1.3579 0.02923 0.02075 -0.0660 0.0787 0.9989
10.000 1.3822 0.03005 0.02161 -0.0660 0.0693 0.9989
10.250 1.4057 0.03094 0.02253 -0.0660 0.0603 0.9989
10.500 1.4283 0.03192 0.02353 -0.0659 0.0525 0.9989
10.750 1.4504 0.03290 0.02456 -0.0657 0.0456 0.9989
11.000 1.4721 0.03388 0.02564 -0.0654 0.0407 0.9989
11.250 1.4918 0.03506 0.02688 -0.0648 0.0358 0.9989
11.500 1.5116 0.03615 0.02809 -0.0643 0.0310 0.9989
11.750 1.5286 0.03751 0.02952 -0.0634 0.0263 0.9989
12.000 1.5431 0.03906 0.03115 -0.0622 0.0218 0.9989
12.250 1.5560 0.04064 0.03287 -0.0608 0.0181 0.9989
12.500 1.5643 0.04257 0.03491 -0.0588 0.0157 0.9989
12.750 1.5689 0.04464 0.03714 -0.0563 0.0140 0.9989
13.000 1.5628 0.04720 0.03984 -0.0524 0.0131 0.9989
13.250 1.5527 0.05030 0.04310 -0.0487 0.0125 0.9989
13.500 1.5452 0.05371 0.04671 -0.0464 0.0120 0.9989
13.750 1.5374 0.05758 0.05078 -0.0450 0.0115 0.9989
14.000 1.5291 0.06189 0.05528 -0.0445 0.0111 0.9989
14.250 1.5196 0.06668 0.06025 -0.0446 0.0108 0.9989
14.500 1.5087 0.07194 0.06570 -0.0453 0.0105 0.9989
14.750 1.4961 0.07768 0.07163 -0.0465 0.0103 0.9989
15.000 1.4814 0.08391 0.07805 -0.0482 0.0101 0.9989
15.250 1.4653 0.09056 0.08488 -0.0503 0.0100 0.9989
15.500 1.4480 0.09761 0.09211 -0.0528 0.0099 0.9989
15.750 1.4302 0.10495 0.09963 -0.0558 0.0099 0.9989
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