S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=1,000,000 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: 1,000,000 Max Cl/Cd: 65.55 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4096-il-1000000.txt Download as CSV file: xf-s4096-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7241 0.10273 0.10122 0.0122 1.0011 0.0132
-9.500 -0.8317 0.05629 0.05421 -0.0172 1.0011 0.0115
-9.250 -0.8392 0.03728 0.03382 -0.0228 1.0011 0.0111
-9.000 -0.8136 0.03423 0.03039 -0.0239 1.0011 0.0116
-8.750 -0.7865 0.03193 0.02777 -0.0248 1.0011 0.0119
-8.500 -0.7584 0.03019 0.02577 -0.0256 1.0011 0.0120
-8.250 -0.7297 0.02907 0.02439 -0.0264 1.0011 0.0123
-8.000 -0.7019 0.02552 0.02048 -0.0275 1.0011 0.0125
-7.750 -0.6733 0.02358 0.01838 -0.0284 1.0011 0.0128
-7.500 -0.6441 0.02255 0.01728 -0.0291 1.0011 0.0131
-7.250 -0.6147 0.02173 0.01640 -0.0299 1.0011 0.0134
-7.000 -0.5850 0.02111 0.01573 -0.0306 1.0011 0.0139
-6.750 -0.5552 0.02051 0.01508 -0.0313 1.0011 0.0144
-6.500 -0.5253 0.01985 0.01436 -0.0320 1.0011 0.0148
-6.250 -0.4952 0.01924 0.01368 -0.0327 1.0011 0.0152
-6.000 -0.4651 0.01869 0.01309 -0.0334 1.0011 0.0155
-5.750 -0.4349 0.01824 0.01259 -0.0341 1.0011 0.0157
-5.500 -0.4046 0.01786 0.01218 -0.0348 1.0011 0.0159
-5.250 -0.3741 0.01701 0.01127 -0.0357 1.0011 0.0164
-5.000 -0.3434 0.01650 0.01072 -0.0365 1.0011 0.0170
-4.750 -0.3129 0.01618 0.01040 -0.0373 1.0011 0.0179
-4.500 -0.2823 0.01593 0.01014 -0.0381 1.0011 0.0187
-4.250 -0.2516 0.01570 0.00989 -0.0389 1.0011 0.0195
-4.000 -0.2208 0.01550 0.00968 -0.0397 1.0011 0.0201
-3.750 -0.1900 0.01530 0.00946 -0.0405 1.0011 0.0210
-3.500 -0.1577 0.01526 0.00941 -0.0417 0.9935 0.0231
-3.250 -0.1259 0.01533 0.00945 -0.0425 0.9534 0.0258
-3.000 -0.1006 0.01526 0.00944 -0.0418 0.9099 0.0594
-2.750 -0.0727 0.01506 0.00941 -0.0419 0.8754 0.1325
-2.500 -0.0435 0.01489 0.00942 -0.0425 0.8456 0.2123
-2.250 -0.0139 0.01478 0.00943 -0.0431 0.8185 0.2811
-2.000 0.0160 0.01471 0.00944 -0.0438 0.7933 0.3350
-1.750 0.0462 0.01464 0.00946 -0.0446 0.7705 0.3928
-1.500 0.0765 0.01455 0.00951 -0.0454 0.7490 0.4631
-1.250 0.1068 0.01444 0.00961 -0.0463 0.7293 0.5555
-1.000 0.1371 0.01426 0.00984 -0.0472 0.7110 0.6947
-0.500 0.1860 0.01340 0.00968 -0.0451 0.6786 0.9989
-0.250 0.2166 0.01344 0.00962 -0.0459 0.6627 0.9989
0.000 0.2473 0.01348 0.00956 -0.0467 0.6474 0.9989
0.250 0.2779 0.01353 0.00951 -0.0475 0.6331 0.9989
0.500 0.3084 0.01357 0.00947 -0.0482 0.6190 0.9989
0.750 0.3390 0.01361 0.00943 -0.0490 0.6052 0.9989
1.000 0.3695 0.01366 0.00940 -0.0498 0.5912 0.9989
1.250 0.4000 0.01371 0.00938 -0.0505 0.5776 0.9989
1.500 0.4304 0.01376 0.00937 -0.0513 0.5639 0.9989
1.750 0.4609 0.01382 0.00936 -0.0520 0.5499 0.9989
2.000 0.4913 0.01388 0.00935 -0.0528 0.5352 0.9989
2.250 0.5216 0.01394 0.00935 -0.0535 0.5200 0.9989
2.500 0.5519 0.01402 0.00935 -0.0543 0.5033 0.9989
2.750 0.5822 0.01409 0.00936 -0.0550 0.4859 0.9989
3.000 0.6124 0.01417 0.00937 -0.0558 0.4674 0.9989
3.250 0.6425 0.01427 0.00939 -0.0565 0.4474 0.9989
3.500 0.6725 0.01438 0.00941 -0.0573 0.4275 0.9989
3.750 0.7026 0.01449 0.00944 -0.0580 0.4072 0.9989
4.000 0.7325 0.01462 0.00949 -0.0587 0.3870 0.9989
4.250 0.7624 0.01477 0.00955 -0.0595 0.3669 0.9989
4.500 0.7922 0.01491 0.00962 -0.0602 0.3469 0.9989
4.750 0.8220 0.01507 0.00970 -0.0609 0.3276 0.9989
5.000 0.8517 0.01526 0.00980 -0.0616 0.3085 0.9989
5.250 0.8814 0.01543 0.00991 -0.0623 0.2902 0.9989
5.500 0.9110 0.01562 0.01004 -0.0630 0.2725 0.9989
5.750 0.9404 0.01584 0.01018 -0.0637 0.2538 0.9989
6.000 0.9698 0.01606 0.01033 -0.0644 0.2370 0.9989
6.250 0.9991 0.01631 0.01051 -0.0651 0.2188 0.9989
6.500 1.0283 0.01657 0.01069 -0.0658 0.2002 0.9989
6.750 1.0574 0.01683 0.01089 -0.0664 0.1839 0.9989
7.000 1.0865 0.01710 0.01111 -0.0671 0.1698 0.9989
7.250 1.1154 0.01740 0.01135 -0.0677 0.1555 0.9989
7.500 1.1441 0.01773 0.01161 -0.0683 0.1399 0.9989
7.750 1.1727 0.01810 0.01190 -0.0689 0.1243 0.9989
8.000 1.2012 0.01847 0.01220 -0.0695 0.1111 0.9989
8.250 1.2296 0.01883 0.01252 -0.0701 0.0995 0.9989
8.500 1.2577 0.01924 0.01286 -0.0706 0.0870 0.9989
8.750 1.2857 0.01965 0.01323 -0.0712 0.0763 0.9989
9.000 1.3137 0.02004 0.01360 -0.0717 0.0678 0.9989
9.250 1.3413 0.02050 0.01401 -0.0722 0.0590 0.9989
9.500 1.3686 0.02100 0.01446 -0.0726 0.0505 0.9989
9.750 1.3960 0.02143 0.01489 -0.0730 0.0450 0.9989
10.000 1.4232 0.02190 0.01536 -0.0734 0.0394 0.9989
10.250 1.4498 0.02246 0.01589 -0.0738 0.0337 0.9989
10.500 1.4765 0.02295 0.01638 -0.0741 0.0293 0.9989
10.750 1.5024 0.02357 0.01698 -0.0744 0.0240 0.9989
11.000 1.5270 0.02443 0.01777 -0.0744 0.0158 0.9989
11.250 1.5507 0.02540 0.01871 -0.0744 0.0097 0.9989
11.500 1.5749 0.02621 0.01956 -0.0744 0.0080 0.9989
11.750 1.5982 0.02714 0.02054 -0.0742 0.0070 0.9989
12.000 1.6218 0.02792 0.02139 -0.0740 0.0066 0.9989
12.250 1.6448 0.02873 0.02228 -0.0738 0.0062 0.9989
12.500 1.6669 0.02962 0.02325 -0.0735 0.0059 0.9989
12.750 1.6875 0.03063 0.02434 -0.0729 0.0056 0.9989
13.000 1.7061 0.03183 0.02563 -0.0721 0.0053 0.9989
13.250 1.7212 0.03336 0.02728 -0.0708 0.0051 0.9989
13.500 1.7343 0.03493 0.02898 -0.0693 0.0049 0.9989
13.750 1.7484 0.03624 0.03038 -0.0678 0.0049 0.9989
14.000 1.7589 0.03773 0.03198 -0.0659 0.0048 0.9989
14.250 1.7643 0.03950 0.03387 -0.0632 0.0047 0.9989
14.500 1.7515 0.04206 0.03657 -0.0576 0.0047 0.9989
14.750 1.7413 0.04509 0.03973 -0.0538 0.0046 0.9989
15.000 1.7334 0.04854 0.04332 -0.0515 0.0046 0.9989
15.250 1.7257 0.05244 0.04737 -0.0502 0.0045 0.9989
15.500 1.7171 0.05687 0.05194 -0.0497 0.0045 0.9989
15.750 1.7070 0.06180 0.05702 -0.0498 0.0044 0.9989
16.000 1.6946 0.06732 0.06269 -0.0506 0.0044 0.9989
16.250 1.6803 0.07332 0.06885 -0.0518 0.0044 0.9989
16.500 1.6632 0.07991 0.07559 -0.0534 0.0043 0.9989
16.750 1.6435 0.08704 0.08288 -0.0554 0.0043 0.9989
17.000 1.6218 0.09460 0.09059 -0.0578 0.0043 0.9989
17.250 1.5993 0.10259 0.09874 -0.0607 0.0043 0.9989
17.500 1.5769 0.11088 0.10718 -0.0640 0.0043 0.9989
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Polar data table (+)
Polar graphs
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