S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Reynolds number: 50,000 Max Cl/Cd: 27.69 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4096-il-50000.txt Download as CSV file: xf-s4096-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6240 0.12728 0.12061 0.0219 1.0011 0.2649
-8.500 -0.5977 0.12185 0.11515 0.0230 1.0011 0.2749
-8.000 -0.6315 0.11522 0.10873 0.0214 1.0011 0.2961
-7.750 -0.6197 0.11087 0.10438 0.0223 1.0011 0.3101
-7.500 -0.6148 0.10671 0.10026 0.0225 1.0011 0.3251
-7.250 -0.6192 0.10278 0.09638 0.0214 1.0011 0.3419
-7.000 -0.5998 0.09822 0.09184 0.0240 1.0011 0.3596
-6.750 -0.5786 0.06735 0.05929 -0.0284 1.0011 0.1463
-6.500 -0.5498 0.05975 0.05124 -0.0322 1.0011 0.1336
-6.250 -0.5196 0.05451 0.04555 -0.0347 1.0011 0.1287
-6.000 -0.4872 0.04916 0.03958 -0.0373 1.0011 0.1236
-5.750 -0.4521 0.04436 0.03388 -0.0395 1.0011 0.1199
-5.500 -0.4197 0.04092 0.02995 -0.0406 1.0011 0.1204
-5.250 -0.3888 0.03833 0.02709 -0.0412 1.0011 0.1260
-5.000 -0.3563 0.03586 0.02409 -0.0418 1.0011 0.1327
-4.750 -0.3264 0.03355 0.02177 -0.0420 1.0011 0.1414
-4.500 -0.2963 0.03152 0.01968 -0.0419 1.0011 0.1570
-4.250 -0.2669 0.02959 0.01782 -0.0417 1.0011 0.1904
-4.000 -0.2387 0.02720 0.01637 -0.0415 1.0011 0.3130
-3.750 -0.2198 0.02498 0.01580 -0.0386 1.0011 0.5671
-3.500 -0.2093 0.02374 0.01547 -0.0321 1.0011 0.7457
-3.250 -0.1669 0.02223 0.01415 -0.0318 1.0011 0.9989
-3.000 -0.1367 0.02177 0.01308 -0.0342 1.0011 0.9989
-2.750 -0.1076 0.02167 0.01254 -0.0354 1.0011 0.9989
-2.500 -0.0792 0.02169 0.01219 -0.0363 1.0011 0.9989
-2.250 -0.0514 0.02181 0.01201 -0.0370 1.0011 0.9989
-2.000 -0.0241 0.02201 0.01196 -0.0375 1.0011 0.9989
-1.750 0.0026 0.02230 0.01202 -0.0380 1.0011 0.9989
-1.500 0.0285 0.02270 0.01225 -0.0383 1.0011 0.9989
-1.250 0.0534 0.02324 0.01264 -0.0386 1.0011 0.9989
-1.000 0.0773 0.02392 0.01318 -0.0388 1.0011 0.9989
-0.750 0.0999 0.02478 0.01393 -0.0389 1.0011 0.9989
-0.500 0.1212 0.02583 0.01490 -0.0389 1.0011 0.9989
-0.250 0.1414 0.02708 0.01606 -0.0390 1.0011 0.9989
0.000 0.1607 0.02848 0.01739 -0.0392 1.0011 0.9989
0.250 0.1792 0.03000 0.01885 -0.0395 1.0011 0.9989
0.500 0.1970 0.03161 0.02042 -0.0399 1.0011 0.9989
0.750 0.2144 0.03328 0.02206 -0.0404 1.0011 0.9989
1.000 0.2348 0.03482 0.02358 -0.0416 0.9998 0.9989
1.250 0.2982 0.03457 0.02328 -0.0502 0.9852 0.9989
1.500 0.3576 0.03410 0.02279 -0.0579 0.9677 0.9989
1.750 0.4179 0.03351 0.02221 -0.0654 0.9502 0.9989
2.000 0.4811 0.03266 0.02141 -0.0732 0.9335 0.9989
2.250 0.5414 0.03179 0.02060 -0.0798 0.9160 0.9989
2.500 0.5905 0.03130 0.02019 -0.0839 0.8953 0.9989
2.750 0.6302 0.03117 0.02013 -0.0857 0.8722 0.9989
3.000 0.6648 0.03123 0.02025 -0.0863 0.8494 0.9989
3.250 0.6939 0.03152 0.02059 -0.0856 0.8252 0.9989
3.500 0.7203 0.03193 0.02105 -0.0844 0.8010 0.9989
3.750 0.7458 0.03230 0.02145 -0.0828 0.7778 0.9989
4.000 0.7700 0.03284 0.02208 -0.0813 0.7528 0.9989
4.250 0.7944 0.03320 0.02244 -0.0792 0.7306 0.9989
4.500 0.8184 0.03379 0.02310 -0.0778 0.7048 0.9989
4.750 0.8427 0.03424 0.02360 -0.0760 0.6814 0.9989
5.000 0.8672 0.03472 0.02412 -0.0745 0.6568 0.9989
5.250 0.8918 0.03527 0.02473 -0.0731 0.6315 0.9989
5.500 0.9168 0.03561 0.02503 -0.0713 0.6087 0.9989
5.750 0.9418 0.03622 0.02576 -0.0703 0.5821 0.9989
6.000 0.9669 0.03675 0.02633 -0.0691 0.5567 0.9989
6.250 0.9925 0.03709 0.02662 -0.0676 0.5330 0.9989
6.500 1.0178 0.03775 0.02740 -0.0668 0.5062 0.9989
6.750 1.0431 0.03836 0.02805 -0.0659 0.4802 0.9989
7.000 1.0690 0.03882 0.02845 -0.0647 0.4561 0.9989
7.250 1.0943 0.03954 0.02922 -0.0639 0.4299 0.9989
7.500 1.1193 0.04046 0.03023 -0.0632 0.4039 0.9989
7.750 1.1446 0.04134 0.03108 -0.0624 0.3798 0.9989
8.000 1.1696 0.04235 0.03208 -0.0617 0.3552 0.9989
8.250 1.1935 0.04379 0.03367 -0.0611 0.3313 0.9989
8.500 1.2187 0.04488 0.03465 -0.0604 0.3094 0.9989
8.750 1.2410 0.04677 0.03679 -0.0599 0.2873 0.9989
9.000 1.2647 0.04830 0.03833 -0.0593 0.2672 0.9989
9.250 1.2881 0.05012 0.04016 -0.0587 0.2489 0.9989
9.500 1.3075 0.05257 0.04295 -0.0580 0.2314 0.9989
9.750 1.3268 0.05505 0.04567 -0.0573 0.2157 0.9989
10.000 1.3450 0.05778 0.04863 -0.0564 0.2019 0.9989
10.250 1.3626 0.06057 0.05160 -0.0556 0.1894 0.9989
10.500 1.3826 0.06316 0.05423 -0.0549 0.1776 0.9989
10.750 1.3786 0.06853 0.06042 -0.0527 0.1704 0.9989
11.000 1.3893 0.07192 0.06400 -0.0514 0.1614 0.9989
11.250 1.3720 0.07798 0.07067 -0.0486 0.1576 0.9989
11.500 1.3889 0.08084 0.07351 -0.0476 0.1490 0.9989
11.750 1.3581 0.08751 0.08065 -0.0444 0.1485 0.9989
12.000 1.3237 0.09434 0.08776 -0.0418 0.1489 0.9989
12.250 1.2878 0.10120 0.09478 -0.0396 0.1498 0.9989
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Polar data table (+)
Polar graphs
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