EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 479 AIRFOIL (e479-il) Reynolds number: 50,000 Max Cl/Cd: 23.78 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e479-il-50000-n5.txt Download as CSV file: xf-e479-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 479 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7269 0.09398 0.08516 -0.0116 1.0000 0.1802
-12.250 -0.6971 0.09561 0.08674 -0.0095 1.0000 0.1828
-12.000 -0.7935 0.07570 0.06686 -0.0203 1.0000 0.1950
-11.750 -0.7412 0.08082 0.07194 -0.0160 1.0000 0.1971
-11.500 -0.7174 0.08142 0.07251 -0.0145 1.0000 0.2008
-11.250 -0.8421 0.06002 0.05107 -0.0259 1.0000 0.2128
-11.000 -0.8178 0.06025 0.05129 -0.0246 1.0000 0.2178
-10.750 -0.9099 0.04905 0.03986 -0.0269 1.0000 0.2235
-10.500 -0.9060 0.04754 0.03834 -0.0255 1.0000 0.2288
-10.250 -0.8989 0.04641 0.03717 -0.0238 1.0000 0.2348
-10.000 -0.9273 0.04270 0.03317 -0.0209 1.0000 0.2411
-9.750 -0.8974 0.04291 0.03350 -0.0202 1.0000 0.2469
-9.500 -0.8977 0.04107 0.03151 -0.0182 1.0000 0.2542
-9.250 -0.8850 0.04005 0.03044 -0.0168 1.0000 0.2608
-9.000 -0.8714 0.03911 0.02944 -0.0153 1.0000 0.2679
-8.750 -0.8640 0.03769 0.02787 -0.0136 1.0000 0.2755
-8.500 -0.8443 0.03720 0.02740 -0.0124 1.0000 0.2826
-8.250 -0.8370 0.03572 0.02574 -0.0106 1.0000 0.2908
-8.000 -0.8146 0.03540 0.02546 -0.0095 1.0000 0.2977
-7.750 -0.8061 0.03405 0.02392 -0.0077 1.0000 0.3067
-7.500 -0.7829 0.03377 0.02373 -0.0067 1.0000 0.3133
-7.250 -0.7734 0.03252 0.02227 -0.0049 1.0000 0.3227
-7.000 -0.7499 0.03231 0.02216 -0.0038 1.0000 0.3293
-6.750 -0.7377 0.03129 0.02099 -0.0020 1.0000 0.3385
-6.500 -0.7166 0.03094 0.02073 -0.0008 1.0000 0.3452
-6.250 -0.7025 0.03017 0.01987 0.0009 1.0000 0.3543
-6.000 -0.6840 0.02972 0.01947 0.0024 1.0000 0.3613
-5.750 -0.6687 0.02913 0.01885 0.0041 1.0000 0.3698
-5.500 -0.6532 0.02863 0.01837 0.0058 1.0000 0.3774
-5.250 -0.6389 0.02821 0.01796 0.0076 1.0000 0.3852
-5.000 -0.6277 0.02770 0.01743 0.0097 1.0000 0.3930
-4.750 -0.6004 0.02743 0.01719 0.0091 0.9911 0.4018
-4.500 -0.5551 0.02703 0.01674 0.0053 0.9692 0.4126
-4.250 -0.5124 0.02653 0.01611 0.0018 0.9466 0.4249
-4.000 -0.4664 0.02629 0.01596 -0.0014 0.9258 0.4344
-3.750 -0.4234 0.02586 0.01546 -0.0043 0.9044 0.4456
-3.500 -0.3837 0.02552 0.01507 -0.0063 0.8814 0.4567
-3.250 -0.3469 0.02524 0.01477 -0.0076 0.8577 0.4663
-3.000 -0.3139 0.02489 0.01430 -0.0084 0.8346 0.4779
-2.750 -0.2826 0.02473 0.01412 -0.0084 0.8116 0.4869
-2.500 -0.2556 0.02449 0.01379 -0.0080 0.7886 0.4974
-2.250 -0.2286 0.02434 0.01358 -0.0073 0.7671 0.5077
-2.000 -0.2024 0.02418 0.01336 -0.0065 0.7468 0.5176
-1.750 -0.1775 0.02402 0.01307 -0.0057 0.7275 0.5293
-1.500 -0.1515 0.02395 0.01300 -0.0048 0.7091 0.5391
-1.250 -0.1265 0.02383 0.01280 -0.0040 0.6912 0.5506
-1.000 -0.1014 0.02375 0.01268 -0.0032 0.6740 0.5625
-0.750 -0.0758 0.02371 0.01264 -0.0024 0.6576 0.5738
-0.500 -0.0506 0.02365 0.01255 -0.0016 0.6418 0.5865
-0.250 -0.0256 0.02362 0.01247 -0.0009 0.6269 0.6005
0.000 0.0000 0.02363 0.01250 0.0000 0.6131 0.6132
0.250 0.0255 0.02362 0.01247 0.0009 0.6004 0.6269
0.500 0.0506 0.02365 0.01255 0.0016 0.5865 0.6418
0.750 0.0758 0.02371 0.01264 0.0024 0.5738 0.6576
1.000 0.1014 0.02375 0.01268 0.0032 0.5625 0.6740
1.250 0.1265 0.02383 0.01280 0.0040 0.5506 0.6912
1.500 0.1515 0.02395 0.01300 0.0048 0.5391 0.7091
1.750 0.1776 0.02402 0.01307 0.0057 0.5294 0.7275
2.000 0.2024 0.02418 0.01336 0.0065 0.5176 0.7468
2.250 0.2286 0.02434 0.01358 0.0073 0.5076 0.7671
2.500 0.2556 0.02449 0.01379 0.0080 0.4975 0.7886
2.750 0.2826 0.02473 0.01412 0.0084 0.4869 0.8116
3.000 0.3139 0.02489 0.01430 0.0084 0.4779 0.8347
3.250 0.3469 0.02524 0.01477 0.0076 0.4663 0.8577
3.500 0.3837 0.02552 0.01507 0.0063 0.4567 0.8815
3.750 0.4234 0.02586 0.01546 0.0043 0.4456 0.9043
4.000 0.4664 0.02628 0.01595 0.0014 0.4343 0.9258
4.250 0.5124 0.02653 0.01611 -0.0018 0.4248 0.9467
4.500 0.5551 0.02702 0.01674 -0.0053 0.4126 0.9693
4.750 0.6004 0.02743 0.01719 -0.0091 0.4018 0.9912
5.000 0.6276 0.02770 0.01743 -0.0097 0.3930 1.0000
5.250 0.6388 0.02821 0.01796 -0.0076 0.3852 1.0000
5.500 0.6531 0.02864 0.01838 -0.0058 0.3774 1.0000
5.750 0.6687 0.02913 0.01884 -0.0041 0.3698 1.0000
6.000 0.6839 0.02972 0.01947 -0.0024 0.3614 1.0000
6.250 0.7025 0.03017 0.01987 -0.0009 0.3543 1.0000
6.500 0.7166 0.03094 0.02073 0.0008 0.3453 1.0000
6.750 0.7377 0.03129 0.02098 0.0020 0.3385 1.0000
7.000 0.7499 0.03230 0.02216 0.0038 0.3293 1.0000
7.250 0.7734 0.03252 0.02227 0.0049 0.3227 1.0000
7.500 0.7829 0.03377 0.02372 0.0067 0.3133 1.0000
7.750 0.8061 0.03406 0.02392 0.0077 0.3067 1.0000
8.000 0.8147 0.03540 0.02546 0.0095 0.2977 1.0000
8.250 0.8371 0.03572 0.02573 0.0106 0.2908 1.0000
8.500 0.8444 0.03719 0.02739 0.0124 0.2826 1.0000
8.750 0.8640 0.03769 0.02788 0.0136 0.2755 1.0000
9.000 0.8716 0.03911 0.02943 0.0153 0.2679 1.0000
9.250 0.8853 0.04004 0.03043 0.0167 0.2608 1.0000
9.500 0.8979 0.04107 0.03151 0.0182 0.2542 1.0000
9.750 0.8977 0.04291 0.03351 0.0201 0.2469 1.0000
10.000 0.9277 0.04269 0.03315 0.0208 0.2411 1.0000
10.250 0.8994 0.04640 0.03716 0.0237 0.2347 1.0000
10.500 0.9061 0.04759 0.03839 0.0254 0.2289 1.0000
10.750 0.9103 0.04906 0.03987 0.0269 0.2235 1.0000
11.000 0.8197 0.06011 0.05114 0.0245 0.2178 1.0000
11.250 0.8469 0.05952 0.05057 0.0261 0.2127 1.0000
11.500 0.7198 0.08116 0.07224 0.0145 0.2008 1.0000
11.750 0.7440 0.08051 0.07163 0.0161 0.1971 1.0000
12.000 0.7966 0.07535 0.06651 0.0204 0.1950 1.0000
12.250 0.6991 0.09545 0.08658 0.0094 0.1828 1.0000
12.500 0.7288 0.09386 0.08504 0.0115 0.1802 1.0000
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Polar data table (+)
Polar graphs
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