GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 50,000 Max Cl/Cd: 13.69 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe504-il-50000-n5.txt Download as CSV file: xf-goe504-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 504 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2434 0.11149 0.10525 -0.0700 0.9663 0.0643
-10.500 -0.2394 0.10566 0.09943 -0.0748 0.9607 0.0640
-10.250 -0.2432 0.09976 0.09356 -0.0789 0.9523 0.0641
-10.000 -0.2490 0.09234 0.08615 -0.0850 0.9461 0.0642
-9.750 -0.2685 0.08440 0.07824 -0.0903 0.9358 0.0637
-9.500 -0.3016 0.07471 0.06845 -0.0986 0.9252 0.0626
-9.250 -0.3425 0.06793 0.06148 -0.1025 0.9126 0.0612
-9.000 -0.3665 0.06382 0.05713 -0.1020 0.9000 0.0613
-8.750 -0.3830 0.06049 0.05354 -0.1003 0.8879 0.0615
-8.500 -0.3888 0.05729 0.05001 -0.0992 0.8785 0.0623
-8.250 -0.3876 0.05424 0.04657 -0.0983 0.8701 0.0635
-8.000 -0.3884 0.05184 0.04380 -0.0960 0.8603 0.0644
-7.750 -0.3745 0.04899 0.04046 -0.0957 0.8541 0.0654
-7.500 -0.3696 0.04722 0.03830 -0.0931 0.8446 0.0666
-7.250 -0.3469 0.04535 0.03626 -0.0933 0.8391 0.0692
-7.000 -0.3353 0.04423 0.03501 -0.0914 0.8307 0.0714
-6.750 -0.3124 0.04267 0.03318 -0.0911 0.8246 0.0739
-6.500 -0.2911 0.04130 0.03151 -0.0903 0.8182 0.0760
-6.250 -0.2739 0.04029 0.03020 -0.0887 0.8105 0.0784
-6.000 -0.2434 0.03889 0.02879 -0.0895 0.8065 0.0829
-5.750 -0.2361 0.03841 0.02821 -0.0865 0.7965 0.0864
-5.500 -0.2065 0.03730 0.02683 -0.0867 0.7919 0.0917
-5.250 -0.1949 0.03668 0.02619 -0.0843 0.7836 0.0957
-5.000 -0.1720 0.03578 0.02517 -0.0836 0.7775 0.1036
-4.750 -0.1393 0.03445 0.02384 -0.0846 0.7740 0.1216
-4.500 -0.1366 0.03417 0.02379 -0.0811 0.7636 0.1399
-4.250 -0.1068 0.03338 0.02340 -0.0816 0.7592 0.2156
-4.000 -0.0969 0.03370 0.02359 -0.0788 0.7500 0.2558
-3.750 -0.0721 0.03369 0.02348 -0.0783 0.7445 0.2992
-3.500 -0.0488 0.03370 0.02338 -0.0774 0.7389 0.3317
-3.250 -0.0377 0.03401 0.02364 -0.0749 0.7300 0.3555
-3.000 -0.0061 0.03374 0.02331 -0.0752 0.7262 0.3895
-2.750 -0.0021 0.03429 0.02384 -0.0717 0.7163 0.4094
-2.500 0.0271 0.03404 0.02355 -0.0717 0.7117 0.4359
-2.250 0.0468 0.03415 0.02357 -0.0705 0.7048 0.4530
-2.000 0.0674 0.03427 0.02358 -0.0696 0.6977 0.4667
-1.750 0.1050 0.03382 0.02301 -0.0709 0.6942 0.4837
-1.500 0.1117 0.03447 0.02362 -0.0682 0.6844 0.4967
-1.250 0.1431 0.03418 0.02331 -0.0686 0.6798 0.5173
-1.000 0.1815 0.03360 0.02273 -0.0699 0.6770 0.5470
-0.750 0.1796 0.03456 0.02382 -0.0660 0.6659 0.5701
-0.500 0.2135 0.03398 0.02344 -0.0663 0.6624 0.6248
-0.250 0.2203 0.03468 0.02446 -0.0633 0.6531 0.6933
0.000 0.3300 0.03421 0.02428 -0.0771 0.6503 0.9253
0.250 0.4086 0.03404 0.02375 -0.0864 0.6474 1.0000
0.750 0.4199 0.03528 0.02461 -0.0802 0.6322 1.0000
1.000 0.4579 0.03493 0.02401 -0.0815 0.6292 1.0000
1.250 0.4361 0.03667 0.02569 -0.0750 0.6172 1.0000
1.500 0.4713 0.03636 0.02516 -0.0757 0.6140 1.0000
1.750 0.4558 0.03819 0.02692 -0.0705 0.6023 1.0000
2.000 0.4878 0.03799 0.02655 -0.0707 0.5988 1.0000
2.500 0.5066 0.03976 0.02810 -0.0664 0.5837 1.0000
2.750 0.5402 0.03947 0.02766 -0.0668 0.5806 1.0000
3.000 0.5260 0.04176 0.02992 -0.0626 0.5686 1.0000
3.250 0.5618 0.04127 0.02929 -0.0630 0.5659 1.0000
3.750 0.5797 0.04350 0.03139 -0.0593 0.5507 1.0000
4.250 0.5984 0.04586 0.03365 -0.0560 0.5353 1.0000
4.750 0.6161 0.04852 0.03622 -0.0529 0.5200 1.0000
5.000 0.6513 0.04786 0.03549 -0.0530 0.5178 1.0000
5.500 0.6279 0.05415 0.04179 -0.0483 0.4942 1.0000
5.750 0.6504 0.05445 0.04205 -0.0477 0.4894 1.0000
6.000 0.6819 0.05394 0.04150 -0.0474 0.4868 1.0000
6.500 0.6954 0.05743 0.04497 -0.0450 0.4714 1.0000
7.000 0.7079 0.06117 0.04872 -0.0429 0.4560 1.0000
7.500 0.7183 0.06529 0.05287 -0.0410 0.4408 1.0000
7.750 0.7488 0.06478 0.05236 -0.0406 0.4387 1.0000
8.000 0.7265 0.06982 0.05744 -0.0393 0.4259 1.0000
8.250 0.7552 0.06948 0.05711 -0.0389 0.4235 1.0000
8.750 0.7593 0.07465 0.06234 -0.0375 0.4085 1.0000
9.250 0.7607 0.08034 0.06812 -0.0364 0.3938 1.0000
9.750 0.7600 0.08646 0.07434 -0.0357 0.3795 1.0000
10.000 0.7844 0.08670 0.07461 -0.0353 0.3772 1.0000
10.250 0.7584 0.09301 0.08098 -0.0353 0.3663 1.0000
10.500 0.7782 0.09376 0.08179 -0.0350 0.3631 1.0000
10.750 0.8042 0.09375 0.08182 -0.0345 0.3610 1.0000
11.000 0.7718 0.10115 0.08929 -0.0351 0.3500 1.0000
11.250 0.7911 0.10205 0.09025 -0.0348 0.3472 1.0000
11.750 0.7831 0.10980 0.09813 -0.0354 0.3345 1.0000
12.000 0.8016 0.11083 0.09924 -0.0352 0.3318 1.0000
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Polar data table (+)
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