S8065 (11% version of S8064) (s8065-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8065 (11% version of S8064) (s8065-il) Reynolds number: 50,000 Max Cl/Cd: 31.2 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8065-il-50000-n5.txt Download as CSV file: xf-s8065-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8065 (11% version of S8064)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5253 0.09649 0.08943 -0.0405 1.0000 0.0369
-10.500 -0.5305 0.09057 0.08357 -0.0437 1.0000 0.0366
-10.250 -0.5391 0.08436 0.07739 -0.0476 1.0000 0.0362
-10.000 -0.5526 0.07834 0.07139 -0.0515 1.0000 0.0358
-9.750 -0.5691 0.07321 0.06625 -0.0543 1.0000 0.0354
-9.500 -0.5873 0.06905 0.06206 -0.0552 1.0000 0.0350
-9.250 -0.6081 0.06572 0.05868 -0.0540 1.0000 0.0348
-9.000 -0.6264 0.06274 0.05562 -0.0516 1.0000 0.0346
-8.750 -0.6424 0.05990 0.05265 -0.0487 1.0000 0.0345
-8.500 -0.6570 0.05710 0.04965 -0.0453 1.0000 0.0346
-8.250 -0.6685 0.05432 0.04664 -0.0417 1.0000 0.0349
-8.000 -0.6766 0.05155 0.04356 -0.0381 1.0000 0.0354
-7.750 -0.6810 0.04874 0.04038 -0.0347 1.0000 0.0361
-7.500 -0.6814 0.04596 0.03715 -0.0314 1.0000 0.0369
-7.250 -0.6779 0.04327 0.03398 -0.0283 1.0000 0.0381
-7.000 -0.6700 0.04097 0.03155 -0.0261 1.0000 0.0398
-6.750 -0.6591 0.03886 0.02919 -0.0239 1.0000 0.0416
-6.500 -0.6455 0.03662 0.02663 -0.0218 1.0000 0.0436
-6.250 -0.6293 0.03458 0.02415 -0.0198 1.0000 0.0470
-6.000 -0.6133 0.03281 0.02224 -0.0180 1.0000 0.0521
-5.750 -0.5957 0.03131 0.02050 -0.0162 1.0000 0.0592
-5.500 -0.5788 0.02989 0.01905 -0.0145 1.0000 0.0684
-5.250 -0.5616 0.02856 0.01764 -0.0127 1.0000 0.0818
-5.000 -0.5444 0.02732 0.01629 -0.0109 1.0000 0.0996
-4.750 -0.5282 0.02609 0.01513 -0.0091 1.0000 0.1215
-4.500 -0.5119 0.02493 0.01402 -0.0075 1.0000 0.1538
-4.250 -0.4959 0.02367 0.01304 -0.0061 1.0000 0.2035
-4.000 -0.4820 0.02228 0.01222 -0.0045 1.0000 0.2940
-3.750 -0.4715 0.02109 0.01185 -0.0017 1.0000 0.4393
-3.500 -0.4596 0.02057 0.01191 0.0021 1.0000 0.5768
-3.250 -0.4460 0.02057 0.01217 0.0062 1.0000 0.6732
-3.000 -0.4318 0.02071 0.01224 0.0098 1.0000 0.7428
-2.750 -0.4112 0.02095 0.01237 0.0122 0.9980 0.7990
-2.500 -0.3780 0.02140 0.01264 0.0125 0.9938 0.8495
-2.250 -0.3335 0.02191 0.01288 0.0104 0.9908 0.8932
-2.000 -0.2766 0.02244 0.01308 0.0053 0.9891 0.9276
-1.750 -0.2120 0.02281 0.01312 -0.0021 0.9878 0.9482
-1.500 -0.1539 0.02303 0.01304 -0.0088 0.9854 0.9649
-1.250 -0.0996 0.02317 0.01294 -0.0150 0.9823 0.9801
-1.000 -0.0482 0.02324 0.01281 -0.0208 0.9786 0.9945
-0.750 -0.0090 0.02332 0.01275 -0.0246 0.9729 1.0000
-0.500 0.0171 0.02336 0.01268 -0.0257 0.9644 1.0000
-0.250 0.0492 0.02352 0.01274 -0.0278 0.9574 1.0000
0.000 0.0720 0.02360 0.01276 -0.0281 0.9479 1.0000
0.250 0.0987 0.02376 0.01286 -0.0290 0.9396 1.0000
0.500 0.1275 0.02395 0.01302 -0.0302 0.9315 1.0000
0.750 0.1496 0.02412 0.01316 -0.0301 0.9218 1.0000
1.000 0.1814 0.02437 0.01339 -0.0316 0.9143 1.0000
1.250 0.2043 0.02458 0.01360 -0.0315 0.9043 1.0000
1.500 0.2276 0.02481 0.01385 -0.0314 0.8944 1.0000
1.750 0.2637 0.02507 0.01415 -0.0335 0.8872 1.0000
2.000 0.2831 0.02530 0.01440 -0.0325 0.8757 1.0000
2.250 0.3060 0.02554 0.01469 -0.0320 0.8647 1.0000
2.500 0.3362 0.02575 0.01501 -0.0328 0.8551 1.0000
2.750 0.3680 0.02593 0.01528 -0.0337 0.8451 1.0000
3.000 0.3906 0.02610 0.01555 -0.0329 0.8324 1.0000
3.250 0.4155 0.02623 0.01582 -0.0324 0.8194 1.0000
3.500 0.4417 0.02630 0.01603 -0.0320 0.8060 1.0000
3.750 0.4687 0.02627 0.01615 -0.0316 0.7918 1.0000
4.000 0.4969 0.02611 0.01620 -0.0311 0.7765 1.0000
4.250 0.5283 0.02572 0.01602 -0.0307 0.7602 1.0000
4.500 0.5534 0.02532 0.01582 -0.0292 0.7399 1.0000
4.750 0.5857 0.02450 0.01523 -0.0281 0.7177 1.0000
5.000 0.6132 0.02372 0.01468 -0.0262 0.6887 1.0000
5.250 0.6361 0.02311 0.01423 -0.0236 0.6507 1.0000
5.500 0.6633 0.02247 0.01366 -0.0214 0.5997 1.0000
5.750 0.6868 0.02219 0.01326 -0.0189 0.5245 1.0000
6.000 0.7041 0.02257 0.01319 -0.0158 0.4194 1.0000
6.250 0.7104 0.02374 0.01371 -0.0121 0.3191 1.0000
6.500 0.7150 0.02524 0.01465 -0.0088 0.2437 1.0000
6.750 0.7230 0.02676 0.01581 -0.0062 0.1938 1.0000
7.000 0.7339 0.02823 0.01703 -0.0042 0.1598 1.0000
7.250 0.7486 0.02965 0.01836 -0.0024 0.1378 1.0000
7.500 0.7656 0.03103 0.01975 -0.0011 0.1191 1.0000
7.750 0.7878 0.03250 0.02127 -0.0003 0.1051 1.0000
8.000 0.8131 0.03406 0.02293 0.0001 0.0924 1.0000
8.250 0.8410 0.03589 0.02489 0.0002 0.0819 1.0000
8.500 0.8656 0.03783 0.02686 0.0005 0.0731 1.0000
8.750 0.8880 0.03989 0.02928 0.0012 0.0652 1.0000
9.000 0.9075 0.04226 0.03186 0.0020 0.0592 1.0000
9.250 0.9237 0.04477 0.03475 0.0033 0.0541 1.0000
9.500 0.9377 0.04708 0.03711 0.0044 0.0504 1.0000
9.750 0.9441 0.05013 0.04066 0.0065 0.0477 1.0000
10.000 0.9458 0.05331 0.04431 0.0089 0.0455 1.0000
10.250 0.9438 0.05667 0.04806 0.0114 0.0443 1.0000
10.500 0.9364 0.05989 0.05159 0.0141 0.0437 1.0000
10.750 0.9244 0.06328 0.05525 0.0166 0.0432 1.0000
11.000 0.9093 0.06694 0.05917 0.0185 0.0430 1.0000
11.250 0.8912 0.07099 0.06345 0.0196 0.0428 1.0000
11.500 0.8695 0.07571 0.06838 0.0196 0.0430 1.0000
11.750 0.8446 0.08137 0.07422 0.0180 0.0435 1.0000
12.000 0.8181 0.08819 0.08116 0.0147 0.0441 1.0000
12.250 0.7917 0.09645 0.08950 0.0097 0.0449 1.0000
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Polar data table (+)
Polar graphs
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