Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf) Reynolds number: 50,000 Max Cl/Cd: 17.82 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0015-jf-50000.txt Download as CSV file: xf-joukowsk0015-jf-50000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=15%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5750 0.10333 0.09509 0.0158 1.0000 0.2977
-9.500 -0.5712 0.09813 0.08985 0.0140 1.0000 0.2951
-9.250 -0.5770 0.09257 0.08430 0.0117 1.0000 0.2943
-9.000 -0.5918 0.08624 0.07799 0.0087 1.0000 0.2943
-8.750 -0.6222 0.07814 0.06996 0.0044 1.0000 0.2949
-8.500 -0.6288 0.07310 0.06495 0.0029 1.0000 0.3004
-8.250 -0.6753 0.06324 0.05517 -0.0023 1.0000 0.3033
-8.000 -0.7427 0.05225 0.04407 -0.0061 1.0000 0.3070
-7.750 -0.7805 0.04473 0.03614 -0.0071 1.0000 0.3155
-7.500 -0.7446 0.04531 0.03688 -0.0056 1.0000 0.3281
-7.250 -0.7229 0.04438 0.03598 -0.0044 1.0000 0.3404
-7.000 -0.7212 0.04118 0.03258 -0.0041 1.0000 0.3533
-6.750 -0.7063 0.03964 0.03095 -0.0032 1.0000 0.3677
-6.500 -0.6752 0.03989 0.03137 -0.0016 1.0000 0.3806
-6.250 -0.6559 0.03890 0.03039 -0.0003 1.0000 0.3947
-6.000 -0.6425 0.03730 0.02873 0.0006 1.0000 0.4095
-5.750 -0.6297 0.03583 0.02718 0.0018 1.0000 0.4253
-5.500 -0.6059 0.03575 0.02722 0.0036 1.0000 0.4390
-5.250 -0.5865 0.03541 0.02698 0.0056 1.0000 0.4526
-5.000 -0.5776 0.03434 0.02591 0.0077 1.0000 0.4667
-4.750 -0.5738 0.03313 0.02464 0.0100 1.0000 0.4818
-4.500 -0.5601 0.03318 0.02481 0.0130 1.0000 0.4939
-4.250 -0.5529 0.03261 0.02427 0.0157 1.0000 0.5068
-4.000 -0.5480 0.03177 0.02339 0.0180 1.0000 0.5218
-3.750 -0.5403 0.03118 0.02276 0.0200 1.0000 0.5369
-3.500 -0.5287 0.03123 0.02292 0.0228 1.0000 0.5491
-3.250 -0.5194 0.03080 0.02250 0.0247 1.0000 0.5640
-3.000 -0.5095 0.03032 0.02199 0.0263 1.0000 0.5800
-2.750 -0.4984 0.02994 0.02159 0.0276 1.0000 0.5969
-2.500 -0.4822 0.03002 0.02173 0.0290 0.9982 0.6120
-2.250 -0.4276 0.03033 0.02202 0.0235 0.9795 0.6362
-2.000 -0.3783 0.03076 0.02248 0.0198 0.9606 0.6572
-1.750 -0.3281 0.03116 0.02289 0.0162 0.9422 0.6782
-1.500 -0.2776 0.03152 0.02328 0.0129 0.9243 0.6991
-1.250 -0.2257 0.03184 0.02360 0.0095 0.9066 0.7198
-1.000 -0.1726 0.03209 0.02387 0.0062 0.8890 0.7403
-0.750 -0.1255 0.03225 0.02403 0.0039 0.8711 0.7600
-0.500 -0.0813 0.03234 0.02412 0.0022 0.8530 0.7791
-0.250 -0.0400 0.03239 0.02417 0.0010 0.8348 0.7979
0.000 0.0000 0.03239 0.02418 0.0000 0.8164 0.8164
0.250 0.0399 0.03239 0.02417 -0.0010 0.7979 0.8348
0.500 0.0812 0.03233 0.02412 -0.0022 0.7790 0.8530
0.750 0.1256 0.03225 0.02403 -0.0039 0.7599 0.8711
1.000 0.1728 0.03209 0.02386 -0.0062 0.7402 0.8890
1.250 0.2255 0.03183 0.02360 -0.0095 0.7197 0.9066
1.500 0.2776 0.03152 0.02327 -0.0129 0.6991 0.9243
1.750 0.3282 0.03115 0.02289 -0.0163 0.6782 0.9422
2.000 0.3784 0.03075 0.02246 -0.0198 0.6571 0.9607
2.250 0.4276 0.03034 0.02202 -0.0235 0.6362 0.9795
2.500 0.4822 0.03002 0.02172 -0.0290 0.6121 0.9982
2.750 0.4984 0.02994 0.02158 -0.0276 0.5969 1.0000
3.000 0.5094 0.03031 0.02199 -0.0263 0.5800 1.0000
3.250 0.5194 0.03079 0.02249 -0.0247 0.5640 1.0000
3.500 0.5287 0.03122 0.02291 -0.0228 0.5491 1.0000
3.750 0.5403 0.03117 0.02275 -0.0200 0.5370 1.0000
4.000 0.5479 0.03177 0.02339 -0.0179 0.5218 1.0000
4.250 0.5528 0.03262 0.02427 -0.0157 0.5069 1.0000
4.500 0.5600 0.03317 0.02480 -0.0130 0.4939 1.0000
4.750 0.5737 0.03313 0.02464 -0.0100 0.4818 1.0000
5.000 0.5776 0.03435 0.02591 -0.0077 0.4668 1.0000
5.250 0.5865 0.03541 0.02698 -0.0056 0.4526 1.0000
5.500 0.6058 0.03576 0.02723 -0.0036 0.4390 1.0000
5.750 0.6297 0.03583 0.02718 -0.0018 0.4253 1.0000
6.000 0.6425 0.03730 0.02872 -0.0006 0.4095 1.0000
6.250 0.6560 0.03889 0.03038 0.0003 0.3947 1.0000
6.500 0.6752 0.03989 0.03137 0.0015 0.3807 1.0000
6.750 0.7063 0.03964 0.03095 0.0031 0.3676 1.0000
7.000 0.7212 0.04119 0.03259 0.0041 0.3533 1.0000
7.250 0.7230 0.04438 0.03598 0.0044 0.3404 1.0000
7.500 0.7447 0.04531 0.03688 0.0056 0.3281 1.0000
7.750 0.7804 0.04475 0.03617 0.0071 0.3155 1.0000
8.000 0.7431 0.05223 0.04405 0.0061 0.3069 1.0000
8.250 0.6739 0.06344 0.05537 0.0021 0.3033 1.0000
8.500 0.6283 0.07324 0.06509 -0.0030 0.3004 1.0000
8.750 0.7824 0.05816 0.05004 0.0085 0.2782 1.0000
9.000 0.6972 0.07162 0.06353 0.0029 0.2792 1.0000
9.250 0.4859 0.11021 0.10196 -0.0287 0.4237 1.0000
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Polar data table (+)
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