S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Reynolds number: 100,000 Max Cl/Cd: 44.88 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4094-il-100000.txt Download as CSV file: xf-s4094-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4094 (root airfoil designed for and used on the
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4285 0.09997 0.09555 0.0006 1.0004 0.1091
-8.250 -0.4471 0.09613 0.09178 -0.0035 1.0004 0.1127
-8.000 -0.4786 0.09216 0.08791 -0.0096 1.0004 0.1135
-7.750 -0.4442 0.08695 0.08268 -0.0044 1.0004 0.1167
-7.500 -0.4374 0.08330 0.07905 -0.0039 1.0004 0.1206
-7.250 -0.5528 0.08639 0.08189 -0.0083 1.0004 0.1153
-7.000 -0.5385 0.08340 0.07892 -0.0049 1.0004 0.1184
-6.750 -0.5303 0.07650 0.07176 -0.0196 1.0004 0.1289
-6.500 -0.5151 0.07313 0.06853 -0.0154 1.0004 0.1312
-6.250 -0.4984 0.06963 0.06501 -0.0163 1.0004 0.1375
-6.000 -0.4751 0.06475 0.05954 -0.0282 1.0004 0.1574
-5.750 -0.4593 0.05996 0.05505 -0.0256 1.0004 0.1599
-5.500 -0.4376 0.05641 0.05141 -0.0276 1.0004 0.1747
-5.250 -0.3803 0.03866 0.03188 -0.0403 1.0004 0.0819
-5.000 -0.3441 0.03280 0.02494 -0.0422 1.0004 0.0706
-4.750 -0.3130 0.02944 0.02117 -0.0431 1.0004 0.0691
-4.500 -0.2814 0.02675 0.01803 -0.0437 1.0004 0.0688
-4.250 -0.2501 0.02467 0.01555 -0.0440 1.0004 0.0702
-4.000 -0.2201 0.02277 0.01349 -0.0444 1.0004 0.0747
-3.750 -0.1905 0.02136 0.01204 -0.0446 1.0004 0.0802
-3.500 -0.1608 0.01986 0.01045 -0.0446 1.0004 0.0872
-3.250 -0.1319 0.01852 0.00930 -0.0448 1.0004 0.1040
-3.000 -0.1030 0.01701 0.00817 -0.0452 1.0004 0.1611
-2.750 -0.0752 0.01577 0.00763 -0.0458 1.0004 0.2767
-2.500 -0.0505 0.01445 0.00740 -0.0457 1.0004 0.4822
-2.250 -0.0337 0.01340 0.00743 -0.0425 1.0004 0.7373
-2.000 -0.0171 0.01302 0.00739 -0.0398 1.0004 0.9996
-1.750 0.0046 0.01364 0.00775 -0.0399 1.0004 0.9996
-1.250 0.0942 0.01386 0.00742 -0.0486 0.9821 0.9996
-1.000 0.1458 0.01368 0.00700 -0.0537 0.9641 0.9996
-0.750 0.1925 0.01360 0.00673 -0.0576 0.9442 0.9996
-0.500 0.2291 0.01368 0.00663 -0.0591 0.9196 0.9996
-0.250 0.2585 0.01388 0.00666 -0.0588 0.8957 0.9996
0.000 0.2841 0.01414 0.00676 -0.0578 0.8719 0.9996
0.250 0.3088 0.01440 0.00687 -0.0565 0.8505 0.9996
0.500 0.3338 0.01466 0.00700 -0.0555 0.8293 0.9996
0.750 0.3589 0.01493 0.00712 -0.0543 0.8101 0.9996
1.000 0.3845 0.01519 0.00725 -0.0534 0.7915 0.9996
1.250 0.4110 0.01545 0.00740 -0.0528 0.7721 0.9996
1.500 0.4375 0.01570 0.00754 -0.0521 0.7536 0.9996
1.750 0.4640 0.01596 0.00768 -0.0515 0.7357 0.9996
2.000 0.4906 0.01622 0.00783 -0.0508 0.7183 0.9996
2.250 0.5180 0.01647 0.00801 -0.0504 0.6997 0.9996
2.500 0.5454 0.01673 0.00820 -0.0501 0.6808 0.9996
2.750 0.5727 0.01698 0.00839 -0.0497 0.6624 0.9996
3.000 0.6000 0.01724 0.00855 -0.0492 0.6445 0.9996
3.250 0.6274 0.01750 0.00874 -0.0489 0.6260 0.9996
3.500 0.6552 0.01776 0.00899 -0.0487 0.6059 0.9996
3.750 0.6828 0.01801 0.00918 -0.0484 0.5867 0.9996
4.000 0.7102 0.01828 0.00936 -0.0481 0.5681 0.9996
4.250 0.7381 0.01855 0.00963 -0.0480 0.5470 0.9996
4.500 0.7657 0.01882 0.00987 -0.0477 0.5267 0.9996
4.750 0.7932 0.01910 0.01007 -0.0475 0.5070 0.9996
5.000 0.8210 0.01939 0.01038 -0.0474 0.4848 0.9996
5.250 0.8483 0.01969 0.01062 -0.0472 0.4645 0.9996
5.500 0.8759 0.02005 0.01100 -0.0471 0.4421 0.9996
5.750 0.9031 0.02044 0.01130 -0.0469 0.4210 0.9996
6.000 0.9304 0.02089 0.01177 -0.0469 0.3988 0.9996
6.250 0.9573 0.02138 0.01221 -0.0468 0.3776 0.9996
6.500 0.9842 0.02194 0.01277 -0.0467 0.3560 0.9996
6.750 1.0108 0.02252 0.01332 -0.0466 0.3348 0.9996
7.000 1.0371 0.02318 0.01396 -0.0465 0.3147 0.9996
7.250 1.0633 0.02386 0.01469 -0.0464 0.2939 0.9996
7.500 1.0891 0.02460 0.01537 -0.0463 0.2749 0.9996
7.750 1.1146 0.02542 0.01621 -0.0462 0.2560 0.9996
8.000 1.1397 0.02627 0.01716 -0.0460 0.2374 0.9996
8.250 1.1644 0.02716 0.01806 -0.0458 0.2199 0.9996
8.500 1.1887 0.02815 0.01904 -0.0456 0.2037 0.9996
8.750 1.2126 0.02921 0.02009 -0.0453 0.1883 0.9996
9.000 1.2360 0.03039 0.02132 -0.0450 0.1739 0.9996
9.250 1.2587 0.03161 0.02262 -0.0446 0.1603 0.9996
9.500 1.2809 0.03296 0.02412 -0.0440 0.1479 0.9996
9.750 1.3020 0.03443 0.02578 -0.0434 0.1362 0.9996
10.000 1.3224 0.03614 0.02764 -0.0428 0.1259 0.9996
10.250 1.3426 0.03784 0.02939 -0.0421 0.1163 0.9996
10.500 1.3613 0.03931 0.03077 -0.0415 0.1056 0.9996
10.750 1.3737 0.04019 0.03196 -0.0402 0.0947 0.9996
11.000 1.3838 0.04167 0.03371 -0.0387 0.0845 0.9996
11.250 1.3925 0.04371 0.03593 -0.0370 0.0755 0.9996
11.500 1.4000 0.04591 0.03809 -0.0353 0.0673 0.9996
11.750 1.4002 0.04804 0.04052 -0.0328 0.0602 0.9996
12.000 1.3989 0.05105 0.04367 -0.0304 0.0550 0.9996
12.250 1.3914 0.05389 0.04682 -0.0274 0.0514 0.9996
12.500 1.3883 0.05659 0.04957 -0.0252 0.0486 0.9996
12.750 1.3841 0.06079 0.05388 -0.0235 0.0465 0.9996
13.000 1.3682 0.06504 0.05851 -0.0223 0.0457 0.9996
13.250 1.3510 0.06997 0.06379 -0.0222 0.0451 0.9996
13.500 1.3322 0.07556 0.06968 -0.0232 0.0446 0.9996
13.750 1.3112 0.08185 0.07627 -0.0252 0.0445 0.9996
14.000 1.2880 0.08891 0.08360 -0.0283 0.0445 0.9996
14.250 1.2626 0.09681 0.09174 -0.0323 0.0448 0.9996
14.500 1.2359 0.10549 0.10061 -0.0373 0.0453 0.9996
14.750 1.2084 0.11498 0.11028 -0.0431 0.0458 0.9996
15.000 1.1811 0.12517 0.12060 -0.0495 0.0465 0.9996
15.250 1.0256 0.18509 0.18046 -0.0870 0.0700 0.9996
15.500 1.0270 0.19149 0.18686 -0.0897 0.0695 0.9996
15.750 1.0308 0.19737 0.19273 -0.0918 0.0691 0.9996
16.000 1.0361 0.20325 0.19862 -0.0936 0.0687 0.9996
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Polar data table (+)
Polar graphs
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