GOE 559 AIRFOIL (goe559-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 559 AIRFOIL (goe559-il) Reynolds number: 1,000,000 Max Cl/Cd: 74.23 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe559-il-1000000-n5.txt Download as CSV file: xf-goe559-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 559 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2340 0.08389 0.08107 -0.0666 0.6642 0.0006
-8.250 -0.2313 0.08062 0.07778 -0.0681 0.6533 0.0006
-8.000 -0.2302 0.07732 0.07444 -0.0695 0.6375 0.0006
-7.750 -0.2283 0.07430 0.07141 -0.0712 0.6272 0.0006
-7.500 -0.2327 0.07072 0.06782 -0.0732 0.6139 0.0006
-7.250 -0.2375 0.06746 0.06452 -0.0753 0.5997 0.0006
-7.000 -0.2345 0.06388 0.06087 -0.0776 0.5863 0.0006
-6.750 -0.2309 0.06013 0.05702 -0.0790 0.5742 0.0006
-6.500 -0.2236 0.05693 0.05372 -0.0800 0.5626 0.0006
-6.250 -0.2161 0.05317 0.04983 -0.0805 0.5536 0.0006
-4.750 -0.1320 0.03496 0.03063 -0.0772 0.5125 0.0006
-4.500 -0.1180 0.03164 0.02712 -0.0762 0.5080 0.0007
-4.250 -0.1002 0.02913 0.02439 -0.0752 0.5026 0.0008
-4.000 -0.0795 0.02694 0.02198 -0.0740 0.4976 0.0009
-3.750 -0.0574 0.02486 0.01968 -0.0727 0.4927 0.0013
-3.500 -0.0294 0.02361 0.01821 -0.0710 0.4876 0.0017
-3.250 -0.0100 0.02100 0.01533 -0.0697 0.4835 0.0020
-3.000 0.0132 0.01930 0.01341 -0.0687 0.4796 0.0023
-2.750 0.0380 0.01783 0.01172 -0.0676 0.4755 0.0025
-2.500 0.0636 0.01650 0.01019 -0.0667 0.4715 0.0028
-2.250 0.0903 0.01546 0.00898 -0.0658 0.4681 0.0033
-2.000 0.1182 0.01500 0.00832 -0.0651 0.4646 0.0036
-1.750 0.1446 0.01417 0.00730 -0.0645 0.4609 0.0036
-1.500 0.1696 0.01224 0.00531 -0.0639 0.4572 0.0042
-1.250 0.1953 0.01146 0.00447 -0.0635 0.4539 0.0050
-1.000 0.2233 0.01156 0.00438 -0.0633 0.4503 0.0066
-0.750 0.2459 0.01025 0.00308 -0.0623 0.4470 0.0075
-0.500 0.2691 0.00955 0.00232 -0.0612 0.4439 0.0027
-0.250 0.2938 0.00915 0.00181 -0.0605 0.4409 0.0018
0.000 0.3195 0.00886 0.00143 -0.0602 0.4386 0.0017
0.250 0.3458 0.00870 0.00117 -0.0600 0.4359 0.0017
0.750 0.3708 0.00635 0.00106 -0.0545 0.4311 0.8259
1.000 0.4037 0.00618 0.00117 -0.0558 0.4282 0.9353
1.250 0.4408 0.00625 0.00123 -0.0582 0.4257 0.9494
1.500 0.4758 0.00641 0.00128 -0.0603 0.4014 0.9596
1.750 0.4918 0.00875 0.00222 -0.0594 0.0020 0.9712
2.000 0.5247 0.00895 0.00249 -0.0609 0.0016 0.9762
2.250 0.5539 0.00929 0.00293 -0.0615 0.0016 0.9816
2.500 0.5827 0.00968 0.00339 -0.0620 0.0019 0.9865
2.750 0.6107 0.01039 0.00423 -0.0623 0.0028 0.9907
4.250 0.7213 0.01633 0.01055 -0.0527 0.0016 1.0000
4.500 0.7426 0.01766 0.01188 -0.0512 0.0016 1.0000
4.750 0.7681 0.01872 0.01298 -0.0503 0.0015 1.0000
5.000 0.7959 0.01954 0.01384 -0.0494 0.0009 1.0000
5.250 0.8248 0.02124 0.01557 -0.0490 0.0008 1.0000
5.500 0.8522 0.02308 0.01749 -0.0484 0.0007 1.0000
5.750 0.8789 0.02511 0.01960 -0.0476 0.0007 1.0000
6.000 0.8994 0.02792 0.02252 -0.0466 0.0006 1.0000
6.250 0.9195 0.03107 0.02582 -0.0448 0.0006 1.0000
6.500 0.9389 0.03323 0.02812 -0.0429 0.0006 1.0000
6.750 0.9563 0.03566 0.03072 -0.0407 0.0005 1.0000
7.000 0.9721 0.03820 0.03345 -0.0383 0.0005 1.0000
7.250 0.9864 0.04077 0.03621 -0.0358 0.0005 1.0000
7.500 0.9989 0.04339 0.03901 -0.0332 0.0005 1.0000
7.750 1.0098 0.04607 0.04187 -0.0306 0.0005 1.0000
8.000 1.0189 0.04890 0.04489 -0.0277 0.0005 1.0000
8.250 1.0269 0.05146 0.04763 -0.0250 0.0005 1.0000
8.500 1.0316 0.05438 0.05072 -0.0221 0.0005 1.0000
8.750 1.0339 0.05744 0.05396 -0.0191 0.0005 1.0000
9.000 1.0345 0.06034 0.05702 -0.0161 0.0005 1.0000
9.250 1.0328 0.06309 0.05993 -0.0132 0.0005 1.0000
9.500 1.0273 0.06594 0.06293 -0.0100 0.0005 1.0000
9.750 1.0200 0.06847 0.06560 -0.0069 0.0005 1.0000
10.000 1.0049 0.07088 0.06812 -0.0029 0.0005 1.0000
10.250 0.9890 0.07336 0.07071 0.0003 0.0005 1.0000
10.500 0.9727 0.07608 0.07353 0.0024 0.0005 1.0000
10.750 0.9555 0.07922 0.07677 0.0036 0.0005 1.0000
11.000 0.9365 0.08296 0.08062 0.0039 0.0005 1.0000
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Polar data table (+)
Polar graphs
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