S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il) Xfoil prediction polar at RE=100,000 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: 100,000 Max Cl/Cd: 40.47 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4096-il-100000-n5.txt Download as CSV file: xf-s4096-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5004 0.13270 0.12790 -0.0001 1.0011 0.0354
-11.000 -0.4968 0.12970 0.12490 -0.0002 1.0011 0.0347
-10.750 -0.6614 0.13565 0.13061 0.0151 1.0011 0.0354
-10.500 -0.6543 0.13228 0.12725 0.0154 1.0011 0.0345
-10.250 -0.6523 0.12764 0.12263 0.0140 1.0011 0.0336
-10.000 -0.6534 0.12233 0.11735 0.0119 1.0011 0.0328
-9.750 -0.6576 0.11637 0.11143 0.0092 1.0011 0.0319
-9.250 -0.7139 0.08777 0.08284 -0.0109 1.0011 0.0279
-9.000 -0.7187 0.08078 0.07572 -0.0146 1.0011 0.0277
-8.750 -0.7198 0.07352 0.06821 -0.0182 1.0011 0.0275
-8.500 -0.7147 0.06621 0.06054 -0.0216 1.0011 0.0273
-8.250 -0.7026 0.05931 0.05314 -0.0246 1.0011 0.0271
-8.000 -0.6840 0.05285 0.04597 -0.0273 1.0011 0.0275
-7.750 -0.6607 0.04779 0.04022 -0.0293 1.0011 0.0284
-7.500 -0.6354 0.04474 0.03688 -0.0307 1.0011 0.0292
-7.250 -0.6080 0.04146 0.03316 -0.0319 1.0011 0.0296
-7.000 -0.5795 0.03858 0.02984 -0.0329 1.0011 0.0299
-6.750 -0.5504 0.03612 0.02703 -0.0338 1.0011 0.0304
-6.500 -0.5211 0.03398 0.02458 -0.0345 1.0011 0.0311
-6.250 -0.4917 0.03212 0.02245 -0.0351 1.0011 0.0318
-6.000 -0.4623 0.03056 0.02067 -0.0357 1.0011 0.0331
-5.750 -0.4327 0.02932 0.01920 -0.0362 1.0011 0.0351
-5.500 -0.4038 0.02793 0.01777 -0.0367 1.0011 0.0368
-5.250 -0.3747 0.02680 0.01660 -0.0373 1.0011 0.0384
-5.000 -0.3454 0.02583 0.01558 -0.0379 1.0011 0.0403
-4.750 -0.3158 0.02496 0.01462 -0.0384 1.0011 0.0429
-4.500 -0.2860 0.02415 0.01373 -0.0391 1.0011 0.0464
-4.250 -0.2563 0.02345 0.01300 -0.0398 1.0011 0.0545
-4.000 -0.2264 0.02262 0.01229 -0.0406 1.0011 0.0724
-3.750 -0.1967 0.02174 0.01172 -0.0414 1.0011 0.1282
-3.500 -0.1678 0.02095 0.01142 -0.0424 1.0011 0.2283
-3.250 -0.1398 0.02021 0.01135 -0.0431 1.0011 0.3690
-3.000 -0.1123 0.01966 0.01131 -0.0434 1.0011 0.4847
-2.750 -0.0853 0.01925 0.01130 -0.0433 1.0011 0.5866
-2.500 -0.0611 0.01887 0.01135 -0.0422 1.0011 0.7029
-2.250 -0.0413 0.01847 0.01133 -0.0394 1.0011 0.8419
-2.000 -0.0122 0.01770 0.01065 -0.0396 1.0011 0.9989
-1.750 0.0160 0.01802 0.01081 -0.0403 1.0011 0.9989
-1.500 0.0549 0.01816 0.01075 -0.0432 0.9865 0.9989
-1.250 0.0949 0.01809 0.01050 -0.0463 0.9638 0.9989
-1.000 0.1338 0.01807 0.01030 -0.0490 0.9402 0.9989
-0.750 0.1700 0.01809 0.01016 -0.0509 0.9150 0.9989
-0.500 0.2024 0.01816 0.01007 -0.0518 0.8885 0.9989
-0.250 0.2322 0.01827 0.01002 -0.0520 0.8631 0.9989
0.000 0.2607 0.01840 0.00999 -0.0520 0.8392 0.9989
0.250 0.2890 0.01853 0.00998 -0.0519 0.8165 0.9989
0.500 0.3171 0.01868 0.00999 -0.0519 0.7954 0.9989
0.750 0.3455 0.01883 0.01001 -0.0519 0.7757 0.9989
1.000 0.3741 0.01898 0.01005 -0.0520 0.7561 0.9989
1.250 0.4027 0.01914 0.01010 -0.0521 0.7375 0.9989
1.500 0.4313 0.01932 0.01018 -0.0523 0.7196 0.9989
1.750 0.4599 0.01950 0.01026 -0.0524 0.7022 0.9989
2.000 0.4888 0.01969 0.01036 -0.0527 0.6849 0.9989
2.250 0.5178 0.01988 0.01049 -0.0530 0.6674 0.9989
2.500 0.5468 0.02008 0.01062 -0.0534 0.6501 0.9989
2.750 0.5757 0.02028 0.01076 -0.0537 0.6327 0.9989
3.000 0.6046 0.02050 0.01093 -0.0540 0.6153 0.9989
3.250 0.6335 0.02072 0.01109 -0.0543 0.5978 0.9989
3.500 0.6623 0.02095 0.01127 -0.0546 0.5800 0.9989
3.750 0.6913 0.02118 0.01149 -0.0550 0.5613 0.9989
4.000 0.7201 0.02142 0.01172 -0.0554 0.5421 0.9989
4.250 0.7488 0.02168 0.01194 -0.0558 0.5227 0.9989
4.500 0.7776 0.02195 0.01219 -0.0561 0.5024 0.9989
4.750 0.8062 0.02224 0.01248 -0.0565 0.4812 0.9989
5.000 0.8347 0.02255 0.01275 -0.0569 0.4600 0.9989
5.250 0.8631 0.02289 0.01307 -0.0572 0.4376 0.9989
5.500 0.8912 0.02326 0.01342 -0.0576 0.4158 0.9989
5.750 0.9194 0.02366 0.01381 -0.0580 0.3933 0.9989
6.000 0.9472 0.02411 0.01421 -0.0583 0.3718 0.9989
6.250 0.9751 0.02458 0.01467 -0.0587 0.3495 0.9989
6.500 1.0026 0.02510 0.01518 -0.0591 0.3284 0.9989
6.750 1.0301 0.02562 0.01572 -0.0594 0.3069 0.9989
7.000 1.0572 0.02620 0.01628 -0.0598 0.2864 0.9989
7.250 1.0842 0.02681 0.01692 -0.0601 0.2664 0.9989
7.500 1.1109 0.02745 0.01758 -0.0604 0.2470 0.9989
7.750 1.1372 0.02815 0.01828 -0.0607 0.2285 0.9989
8.000 1.1632 0.02889 0.01902 -0.0609 0.2110 0.9989
8.250 1.1890 0.02964 0.01985 -0.0611 0.1937 0.9989
8.500 1.2143 0.03045 0.02071 -0.0613 0.1775 0.9989
8.750 1.2390 0.03132 0.02163 -0.0614 0.1621 0.9989
9.000 1.2633 0.03225 0.02261 -0.0614 0.1479 0.9989
9.250 1.2869 0.03323 0.02365 -0.0614 0.1348 0.9989
9.500 1.3098 0.03428 0.02480 -0.0612 0.1231 0.9989
9.750 1.3316 0.03543 0.02600 -0.0609 0.1128 0.9989
10.000 1.3527 0.03663 0.02730 -0.0606 0.1035 0.9989
10.250 1.3733 0.03787 0.02870 -0.0601 0.0947 0.9989
10.500 1.3915 0.03930 0.03018 -0.0593 0.0875 0.9989
10.750 1.4096 0.04070 0.03179 -0.0585 0.0804 0.9989
11.000 1.4250 0.04232 0.03352 -0.0574 0.0744 0.9989
11.250 1.4395 0.04385 0.03520 -0.0563 0.0674 0.9989
11.500 1.4521 0.04550 0.03701 -0.0550 0.0602 0.9989
11.750 1.4599 0.04740 0.03895 -0.0534 0.0540 0.9989
12.000 1.4686 0.04921 0.04102 -0.0517 0.0478 0.9989
12.250 1.4658 0.05178 0.04366 -0.0488 0.0444 0.9989
12.500 1.4606 0.05445 0.04659 -0.0455 0.0412 0.9989
12.750 1.4534 0.05766 0.04999 -0.0430 0.0384 0.9989
13.000 1.4432 0.06157 0.05406 -0.0414 0.0363 0.9989
13.250 1.4341 0.06582 0.05852 -0.0406 0.0341 0.9989
13.500 1.4250 0.07041 0.06334 -0.0404 0.0319 0.9989
13.750 1.4139 0.07554 0.06866 -0.0410 0.0302 0.9989
14.000 1.4007 0.08122 0.07451 -0.0422 0.0291 0.9989
14.250 1.3852 0.08746 0.08089 -0.0439 0.0283 0.9989
14.500 1.3709 0.09371 0.08733 -0.0457 0.0273 0.9989
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