EPPLER 479 AIRFOIL (e479-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: EPPLER 479 AIRFOIL (e479-il) Reynolds number: 50,000 Max Cl/Cd: 15.93 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e479-il-50000.txt Download as CSV file: xf-e479-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4152 0.11252 0.10364 0.0180 1.0000 0.4580
-9.500 -0.3962 0.10855 0.09964 0.0174 1.0000 0.4655
-9.250 -0.4143 0.10805 0.09917 0.0183 1.0000 0.4770
-9.000 -0.3756 0.10317 0.09424 0.0172 1.0000 0.4883
-8.750 -0.3726 0.10067 0.09175 0.0174 1.0000 0.4985
-8.500 -0.3781 0.09943 0.09053 0.0182 1.0000 0.5116
-8.250 -0.3459 0.09513 0.08618 0.0171 1.0000 0.5211
-8.000 -0.3439 0.09296 0.08403 0.0176 1.0000 0.5332
-7.750 -0.4399 0.08183 0.07292 0.0090 1.0000 0.4264
-7.500 -0.4434 0.07755 0.06863 0.0078 1.0000 0.4224
-7.250 -0.4579 0.07320 0.06432 0.0070 1.0000 0.4231
-7.000 -0.4295 0.07187 0.06297 0.0078 1.0000 0.4334
-6.750 -0.4412 0.06798 0.05911 0.0075 1.0000 0.4357
-6.500 -0.4706 0.06321 0.05443 0.0076 1.0000 0.4388
-6.250 -0.5530 0.05466 0.04601 0.0083 1.0000 0.4418
-6.000 -0.4850 0.05711 0.04844 0.0099 1.0000 0.4523
-5.750 -0.5587 0.04932 0.04071 0.0114 1.0000 0.4586
-5.500 -0.5159 0.05018 0.04163 0.0130 1.0000 0.4676
-5.250 -0.5646 0.04478 0.03623 0.0157 1.0000 0.4763
-5.000 -0.5359 0.04496 0.03650 0.0176 1.0000 0.4842
-4.750 -0.5667 0.04164 0.03315 0.0212 1.0000 0.4933
-4.500 -0.5597 0.04115 0.03276 0.0243 1.0000 0.5004
-4.250 -0.5741 0.03948 0.03105 0.0277 1.0000 0.5087
-4.000 -0.5797 0.03830 0.02987 0.0305 1.0000 0.5163
-3.750 -0.5808 0.03748 0.02905 0.0329 1.0000 0.5250
-3.500 -0.5811 0.03648 0.02801 0.0348 1.0000 0.5337
-3.250 -0.5551 0.03556 0.02695 0.0318 0.9906 0.5471
-3.000 -0.4874 0.03568 0.02710 0.0242 0.9678 0.5627
-2.750 -0.4278 0.03554 0.02697 0.0182 0.9446 0.5769
-2.500 -0.3668 0.03522 0.02663 0.0120 0.9232 0.5923
-2.250 -0.3012 0.03475 0.02614 0.0054 0.9035 0.6082
-2.000 -0.2457 0.03422 0.02558 0.0006 0.8836 0.6237
-1.750 -0.2088 0.03360 0.02491 -0.0014 0.8620 0.6382
-1.500 -0.1691 0.03327 0.02455 -0.0030 0.8418 0.6525
-1.250 -0.1292 0.03312 0.02442 -0.0039 0.8223 0.6651
-1.000 -0.0991 0.03282 0.02410 -0.0038 0.8035 0.6787
-0.750 -0.0752 0.03253 0.02377 -0.0031 0.7857 0.6931
-0.500 -0.0539 0.03230 0.02350 -0.0020 0.7686 0.7081
-0.250 -0.0251 0.03237 0.02360 -0.0011 0.7518 0.7215
0.000 0.0000 0.03239 0.02362 0.0000 0.7361 0.7362
0.250 0.0251 0.03237 0.02360 0.0011 0.7216 0.7517
0.500 0.0539 0.03230 0.02350 0.0020 0.7081 0.7686
0.750 0.0752 0.03253 0.02377 0.0031 0.6931 0.7856
1.000 0.0991 0.03282 0.02410 0.0038 0.6786 0.8035
1.250 0.1293 0.03312 0.02442 0.0039 0.6650 0.8224
1.500 0.1692 0.03327 0.02455 0.0030 0.6526 0.8418
1.750 0.2087 0.03361 0.02491 0.0014 0.6383 0.8620
2.000 0.2456 0.03422 0.02557 -0.0006 0.6237 0.8837
2.250 0.3010 0.03475 0.02614 -0.0054 0.6083 0.9035
2.500 0.3668 0.03522 0.02663 -0.0120 0.5923 0.9232
2.750 0.4278 0.03553 0.02696 -0.0182 0.5768 0.9446
3.000 0.4875 0.03568 0.02709 -0.0242 0.5626 0.9679
3.250 0.5551 0.03554 0.02693 -0.0318 0.5471 0.9906
3.500 0.5811 0.03647 0.02800 -0.0348 0.5337 1.0000
3.750 0.5807 0.03747 0.02904 -0.0329 0.5251 1.0000
4.000 0.5794 0.03831 0.02988 -0.0305 0.5163 1.0000
4.250 0.5741 0.03947 0.03104 -0.0276 0.5087 1.0000
4.500 0.5592 0.04118 0.03278 -0.0243 0.5005 1.0000
4.750 0.5666 0.04164 0.03315 -0.0212 0.4933 1.0000
5.000 0.5358 0.04497 0.03651 -0.0176 0.4842 1.0000
5.250 0.5648 0.04476 0.03620 -0.0157 0.4763 1.0000
5.500 0.5157 0.05020 0.04164 -0.0130 0.4676 1.0000
5.750 0.5591 0.04930 0.04069 -0.0114 0.4586 1.0000
6.000 0.4856 0.05707 0.04840 -0.0100 0.4522 1.0000
6.250 0.5539 0.05460 0.04594 -0.0083 0.4418 1.0000
6.500 0.4711 0.06319 0.05441 -0.0077 0.4388 1.0000
6.750 0.4418 0.06795 0.05909 -0.0076 0.4357 1.0000
7.000 0.4300 0.07187 0.06297 -0.0079 0.4334 1.0000
7.250 0.4582 0.07320 0.06431 -0.0071 0.4230 1.0000
7.500 0.4441 0.07753 0.06861 -0.0078 0.4224 1.0000
7.750 0.4414 0.08178 0.07286 -0.0091 0.4263 1.0000
8.000 0.4534 0.08534 0.07645 -0.0097 0.4250 1.0000
8.250 0.3468 0.09512 0.08617 -0.0172 0.5210 1.0000
8.500 0.3780 0.09937 0.09045 -0.0183 0.5115 1.0000
8.750 0.3731 0.10064 0.09171 -0.0175 0.4987 1.0000
9.000 0.3765 0.10317 0.09424 -0.0174 0.4883 1.0000
9.250 0.4150 0.10802 0.09914 -0.0184 0.4770 1.0000
9.500 0.3971 0.10855 0.09964 -0.0176 0.4655 1.0000
9.750 0.4164 0.11254 0.10365 -0.0182 0.4580 1.0000
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Polar data table (+)
Polar graphs
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