GOE 564 AIRFOIL (goe564-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 564 AIRFOIL (goe564-il) Reynolds number: 50,000 Max Cl/Cd: 37.5 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe564-il-50000-n5.txt Download as CSV file: xf-goe564-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 564 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4574 0.09485 0.08771 -0.0353 1.0000 0.0639
-8.500 -0.4587 0.09147 0.08439 -0.0351 1.0000 0.0634
-8.250 -0.4650 0.08809 0.08111 -0.0354 1.0000 0.0632
-8.000 -0.4705 0.08423 0.07733 -0.0366 1.0000 0.0632
-7.750 -0.4769 0.07995 0.07310 -0.0385 1.0000 0.0634
-7.500 -0.4822 0.07548 0.06863 -0.0402 1.0000 0.0637
-7.250 -0.4864 0.07080 0.06391 -0.0416 1.0000 0.0639
-7.000 -0.4891 0.06604 0.05903 -0.0426 1.0000 0.0642
-6.750 -0.4864 0.06237 0.05531 -0.0422 1.0000 0.0650
-6.500 -0.4829 0.05825 0.05104 -0.0421 1.0000 0.0652
-6.250 -0.4764 0.05472 0.04736 -0.0416 1.0000 0.0659
-6.000 -0.4667 0.05230 0.04482 -0.0406 1.0000 0.0680
-5.750 -0.4562 0.04934 0.04163 -0.0401 1.0000 0.0713
-5.500 -0.4447 0.04543 0.03727 -0.0400 1.0000 0.0735
-5.250 -0.4305 0.04159 0.03291 -0.0396 1.0000 0.0746
-5.000 -0.4139 0.03807 0.02879 -0.0391 1.0000 0.0760
-4.750 -0.3963 0.03596 0.02639 -0.0382 1.0000 0.0794
-4.500 -0.3778 0.03465 0.02493 -0.0372 1.0000 0.0838
-4.250 -0.3571 0.03248 0.02228 -0.0365 1.0000 0.0869
-4.000 -0.3348 0.03037 0.01961 -0.0356 1.0000 0.0897
-3.750 -0.3128 0.02879 0.01774 -0.0348 1.0000 0.0927
-3.500 -0.2910 0.02766 0.01646 -0.0339 1.0000 0.0968
-3.250 -0.2680 0.02666 0.01508 -0.0330 1.0000 0.1047
-3.000 -0.2465 0.02592 0.01435 -0.0322 1.0000 0.1133
-2.750 -0.2227 0.02500 0.01321 -0.0314 1.0000 0.1229
-2.500 -0.1994 0.02426 0.01229 -0.0305 1.0000 0.1348
-2.250 -0.1768 0.02373 0.01172 -0.0298 1.0000 0.1517
-2.000 -0.1546 0.02330 0.01132 -0.0292 1.0000 0.1727
-1.750 -0.1323 0.02292 0.01092 -0.0285 1.0000 0.1976
-1.500 -0.1101 0.02253 0.01057 -0.0279 1.0000 0.2199
-1.250 -0.0791 0.02219 0.01032 -0.0291 0.9960 0.2496
-1.000 -0.0434 0.02177 0.01012 -0.0312 0.9895 0.2965
-0.750 0.0020 0.01941 0.01016 -0.0341 0.9867 1.0000
-0.500 0.0394 0.01978 0.01007 -0.0363 0.9785 1.0000
-0.250 0.0756 0.02013 0.01012 -0.0384 0.9700 1.0000
0.000 0.1128 0.02050 0.01025 -0.0407 0.9616 1.0000
0.250 0.1491 0.02084 0.01039 -0.0428 0.9524 1.0000
0.500 0.1827 0.02113 0.01053 -0.0443 0.9420 1.0000
0.750 0.2185 0.02143 0.01072 -0.0462 0.9323 1.0000
1.000 0.2563 0.02172 0.01091 -0.0484 0.9226 1.0000
1.250 0.2886 0.02195 0.01109 -0.0495 0.9108 1.0000
1.500 0.3224 0.02218 0.01129 -0.0509 0.8993 1.0000
1.750 0.3584 0.02237 0.01147 -0.0525 0.8883 1.0000
2.000 0.3978 0.02246 0.01159 -0.0546 0.8769 1.0000
2.250 0.4342 0.02235 0.01152 -0.0557 0.8597 1.0000
2.500 0.4771 0.02190 0.01112 -0.0573 0.8392 1.0000
2.750 0.5193 0.02137 0.01067 -0.0586 0.8186 1.0000
3.000 0.5489 0.02120 0.01057 -0.0580 0.7975 1.0000
3.250 0.5804 0.02105 0.01053 -0.0579 0.7788 1.0000
3.500 0.6098 0.02094 0.01051 -0.0574 0.7580 1.0000
3.750 0.6367 0.02086 0.01054 -0.0564 0.7343 1.0000
4.000 0.6641 0.02077 0.01058 -0.0554 0.7077 1.0000
4.250 0.6943 0.02063 0.01051 -0.0548 0.6780 1.0000
4.500 0.7270 0.02048 0.01037 -0.0544 0.6439 1.0000
4.750 0.7552 0.02056 0.01045 -0.0534 0.6026 1.0000
5.000 0.7790 0.02085 0.01064 -0.0518 0.5522 1.0000
5.250 0.7988 0.02130 0.01094 -0.0497 0.4931 1.0000
5.500 0.8172 0.02195 0.01128 -0.0475 0.4351 1.0000
5.750 0.8346 0.02278 0.01186 -0.0454 0.3863 1.0000
6.000 0.8528 0.02368 0.01256 -0.0438 0.3491 1.0000
6.250 0.8728 0.02456 0.01338 -0.0425 0.3220 1.0000
6.500 0.8937 0.02548 0.01426 -0.0413 0.2998 1.0000
6.750 0.9149 0.02641 0.01526 -0.0403 0.2786 1.0000
7.000 0.9366 0.02740 0.01627 -0.0393 0.2595 1.0000
7.250 0.9597 0.02845 0.01742 -0.0386 0.2416 1.0000
7.500 0.9780 0.02949 0.01855 -0.0372 0.2196 1.0000
7.750 0.9907 0.03043 0.01951 -0.0351 0.1947 1.0000
8.000 1.0028 0.03137 0.02054 -0.0330 0.1716 1.0000
8.250 1.0175 0.03247 0.02182 -0.0312 0.1499 1.0000
8.500 1.0276 0.03357 0.02292 -0.0289 0.1276 1.0000
8.750 1.0386 0.03495 0.02435 -0.0267 0.1060 1.0000
9.000 1.0475 0.03662 0.02589 -0.0245 0.0908 1.0000
9.250 1.0594 0.03866 0.02797 -0.0226 0.0788 1.0000
9.500 1.0724 0.04080 0.03031 -0.0209 0.0693 1.0000
9.750 1.0813 0.04282 0.03233 -0.0189 0.0630 1.0000
10.000 1.0951 0.04522 0.03513 -0.0172 0.0577 1.0000
10.250 1.1020 0.04723 0.03731 -0.0151 0.0539 1.0000
10.500 1.1081 0.04970 0.04000 -0.0132 0.0506 1.0000
10.750 1.1120 0.05251 0.04316 -0.0111 0.0480 1.0000
11.000 1.1134 0.05550 0.04644 -0.0091 0.0464 1.0000
11.250 1.1117 0.05846 0.04963 -0.0073 0.0451 1.0000
11.500 1.1083 0.06131 0.05261 -0.0058 0.0437 1.0000
11.750 1.1050 0.06448 0.05588 -0.0046 0.0426 1.0000
12.000 1.0908 0.06869 0.06039 -0.0039 0.0422 1.0000
12.250 1.0733 0.07352 0.06553 -0.0041 0.0419 1.0000
12.500 1.0541 0.07895 0.07122 -0.0053 0.0418 1.0000
12.750 1.0334 0.08518 0.07766 -0.0078 0.0419 1.0000
13.000 1.0130 0.09202 0.08467 -0.0113 0.0422 1.0000
13.250 0.9912 0.09994 0.09272 -0.0159 0.0425 1.0000
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Polar data table (+)
Polar graphs
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