S4094 (root airfoil designed for and used on the E-flite UMX ASK-21 scale RC sailplane) (s4094-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| 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: 500,000 Max Cl/Cd: 73.29 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4094-il-500000-n5.txt Download as CSV file: xf-s4094-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6518 0.08551 0.08342 0.0086 1.0004 0.0102
-8.500 -0.6613 0.07609 0.07400 -0.0009 1.0004 0.0102
-8.250 -0.7026 0.03394 0.03031 -0.0296 1.0004 0.0102
-8.000 -0.6796 0.02963 0.02545 -0.0313 1.0004 0.0103
-7.750 -0.6535 0.02699 0.02240 -0.0323 1.0004 0.0105
-7.500 -0.6259 0.02543 0.02056 -0.0330 1.0004 0.0107
-7.250 -0.5984 0.02303 0.01779 -0.0339 1.0004 0.0110
-7.000 -0.5703 0.02113 0.01564 -0.0347 1.0004 0.0113
-6.750 -0.5416 0.01982 0.01415 -0.0353 1.0004 0.0115
-6.500 -0.5126 0.01875 0.01296 -0.0359 1.0004 0.0118
-6.250 -0.4834 0.01783 0.01193 -0.0364 1.0004 0.0120
-6.000 -0.4541 0.01699 0.01099 -0.0369 1.0004 0.0123
-5.750 -0.4246 0.01623 0.01014 -0.0373 1.0004 0.0127
-5.500 -0.3951 0.01552 0.00934 -0.0378 1.0004 0.0130
-5.250 -0.3654 0.01487 0.00863 -0.0383 1.0004 0.0134
-5.000 -0.3340 0.01441 0.00809 -0.0391 0.9644 0.0137
-4.750 -0.3071 0.01417 0.00772 -0.0386 0.9112 0.0140
-4.500 -0.2818 0.01393 0.00730 -0.0378 0.8716 0.0144
-4.250 -0.2547 0.01373 0.00694 -0.0374 0.8400 0.0148
-4.000 -0.2263 0.01333 0.00638 -0.0375 0.8126 0.0155
-3.750 -0.1974 0.01301 0.00593 -0.0376 0.7881 0.0162
-3.500 -0.1683 0.01277 0.00556 -0.0378 0.7656 0.0169
-3.250 -0.1390 0.01258 0.00525 -0.0380 0.7450 0.0178
-3.000 -0.1096 0.01242 0.00497 -0.0383 0.7260 0.0188
-2.750 -0.0801 0.01229 0.00474 -0.0386 0.7083 0.0201
-2.500 -0.0505 0.01212 0.00450 -0.0389 0.6917 0.0244
-2.250 -0.0208 0.01188 0.00431 -0.0393 0.6762 0.0486
-1.750 0.0386 0.01146 0.00404 -0.0402 0.6471 0.1183
-1.500 0.0683 0.01129 0.00394 -0.0407 0.6334 0.1576
-1.250 0.0980 0.01111 0.00386 -0.0412 0.6202 0.2037
-1.000 0.1277 0.01086 0.00380 -0.0417 0.6073 0.2758
-0.750 0.1574 0.01059 0.00376 -0.0423 0.5950 0.3638
-0.500 0.1871 0.01027 0.00375 -0.0429 0.5829 0.4725
-0.250 0.2164 0.00993 0.00376 -0.0435 0.5706 0.5974
0.000 0.2451 0.00964 0.00379 -0.0437 0.5582 0.7075
0.250 0.2703 0.00926 0.00381 -0.0428 0.5461 0.8387
0.500 0.2940 0.00861 0.00333 -0.0413 0.5338 0.9996
0.750 0.3237 0.00871 0.00333 -0.0416 0.5206 0.9996
1.000 0.3534 0.00881 0.00335 -0.0420 0.5065 0.9996
1.250 0.3830 0.00893 0.00337 -0.0424 0.4920 0.9996
1.500 0.4126 0.00905 0.00340 -0.0428 0.4768 0.9996
1.750 0.4422 0.00918 0.00344 -0.0431 0.4601 0.9996
2.000 0.4717 0.00933 0.00350 -0.0435 0.4433 0.9996
2.500 0.5306 0.00966 0.00365 -0.0443 0.4091 0.9996
2.750 0.5600 0.00983 0.00374 -0.0447 0.3915 0.9996
3.000 0.5893 0.01002 0.00385 -0.0451 0.3745 0.9996
3.250 0.6186 0.01021 0.00396 -0.0454 0.3578 0.9996
3.500 0.6479 0.01042 0.00410 -0.0458 0.3411 0.9996
3.750 0.6771 0.01063 0.00424 -0.0462 0.3248 0.9996
4.000 0.7062 0.01085 0.00439 -0.0466 0.3089 0.9996
4.250 0.7353 0.01107 0.00456 -0.0470 0.2934 0.9996
4.500 0.7644 0.01131 0.00474 -0.0474 0.2775 0.9996
4.750 0.7934 0.01155 0.00493 -0.0477 0.2620 0.9996
5.000 0.8223 0.01181 0.00513 -0.0481 0.2465 0.9996
5.250 0.8511 0.01208 0.00536 -0.0485 0.2318 0.9996
5.500 0.8798 0.01236 0.00559 -0.0489 0.2170 0.9996
5.750 0.9085 0.01264 0.00583 -0.0492 0.2045 0.9996
6.000 0.9371 0.01294 0.00609 -0.0496 0.1906 0.9996
6.250 0.9656 0.01326 0.00638 -0.0499 0.1777 0.9996
6.500 0.9939 0.01359 0.00668 -0.0503 0.1652 0.9996
6.750 1.0221 0.01395 0.00700 -0.0506 0.1517 0.9996
7.000 1.0502 0.01433 0.00734 -0.0509 0.1383 0.9996
7.250 1.0781 0.01473 0.00771 -0.0512 0.1256 0.9996
7.500 1.1058 0.01515 0.00809 -0.0515 0.1129 0.9996
7.750 1.1332 0.01561 0.00850 -0.0518 0.0995 0.9996
8.000 1.1605 0.01609 0.00894 -0.0521 0.0868 0.9996
8.250 1.1876 0.01657 0.00940 -0.0523 0.0768 0.9996
8.500 1.2147 0.01703 0.00986 -0.0525 0.0683 0.9996
8.750 1.2413 0.01755 0.01036 -0.0527 0.0595 0.9996
9.000 1.2675 0.01812 0.01091 -0.0528 0.0505 0.9996
9.250 1.2934 0.01874 0.01152 -0.0530 0.0424 0.9996
9.500 1.3187 0.01940 0.01215 -0.0530 0.0342 0.9996
9.750 1.3437 0.02008 0.01283 -0.0530 0.0271 0.9996
10.000 1.3682 0.02081 0.01356 -0.0530 0.0209 0.9996
10.250 1.3914 0.02172 0.01445 -0.0528 0.0130 0.9996
10.500 1.4135 0.02274 0.01547 -0.0525 0.0084 0.9996
10.750 1.4360 0.02359 0.01641 -0.0521 0.0071 0.9996
11.000 1.4578 0.02448 0.01739 -0.0517 0.0064 0.9996
11.250 1.4782 0.02549 0.01849 -0.0511 0.0058 0.9996
11.500 1.4981 0.02646 0.01957 -0.0504 0.0054 0.9996
11.750 1.5171 0.02743 0.02066 -0.0496 0.0051 0.9996
12.000 1.5344 0.02849 0.02184 -0.0487 0.0049 0.9996
12.250 1.5499 0.02965 0.02314 -0.0475 0.0047 0.9996
12.500 1.5628 0.03094 0.02455 -0.0461 0.0045 0.9996
12.750 1.5726 0.03238 0.02613 -0.0443 0.0044 0.9996
13.000 1.5782 0.03403 0.02790 -0.0422 0.0042 0.9996
13.250 1.5739 0.03604 0.03005 -0.0389 0.0042 0.9996
13.500 1.5682 0.03866 0.03281 -0.0367 0.0041 0.9996
13.750 1.5629 0.04187 0.03618 -0.0359 0.0040 0.9996
14.000 1.5566 0.04574 0.04022 -0.0362 0.0040 0.9996
14.250 1.5485 0.05022 0.04486 -0.0372 0.0039 0.9996
14.500 1.5382 0.05530 0.05011 -0.0387 0.0039 0.9996
14.750 1.5253 0.06096 0.05594 -0.0407 0.0038 0.9996
15.000 1.5095 0.06718 0.06233 -0.0429 0.0038 0.9996
15.250 1.4922 0.07381 0.06911 -0.0455 0.0038 0.9996
15.500 1.4729 0.08087 0.07633 -0.0482 0.0038 0.9996
15.750 1.4526 0.08826 0.08388 -0.0512 0.0038 0.9996
16.000 1.4318 0.09587 0.09164 -0.0543 0.0038 0.9996
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Polar data table (+)
Polar graphs
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