GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 50,000 Max Cl/Cd: 35.32 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe509-il-50000-n5.txt Download as CSV file: xf-goe509-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 509 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3428 0.10921 0.10314 -0.0308 1.0000 0.1114
-8.000 -0.3622 0.10832 0.10240 -0.0288 1.0000 0.1116
-7.750 -0.3815 0.10726 0.10145 -0.0272 1.0000 0.1118
-7.500 -0.3976 0.10587 0.10015 -0.0260 1.0000 0.1120
-6.750 -0.3825 0.09150 0.08573 -0.0300 0.9911 0.0797
-6.500 -0.3633 0.08878 0.08308 -0.0288 0.9863 0.0907
-6.000 -0.3313 0.07532 0.06920 -0.0430 0.9663 0.0656
-5.750 -0.3129 0.07127 0.06506 -0.0452 0.9582 0.0646
-5.500 -0.2914 0.06666 0.06025 -0.0485 0.9500 0.0639
-5.250 -0.2744 0.06208 0.05542 -0.0508 0.9397 0.0646
-5.000 -0.2545 0.05687 0.04976 -0.0533 0.9303 0.0657
-4.750 -0.2317 0.05226 0.04465 -0.0550 0.9215 0.0660
-4.500 -0.2141 0.04857 0.04057 -0.0548 0.9109 0.0667
-4.250 -0.1897 0.04688 0.03893 -0.0552 0.9011 0.0703
-4.000 -0.1603 0.04383 0.03542 -0.0563 0.8925 0.0738
-3.750 -0.1388 0.04091 0.03198 -0.0555 0.8814 0.0753
-3.500 -0.1134 0.03835 0.02871 -0.0550 0.8718 0.0793
-3.250 -0.0808 0.03609 0.02607 -0.0559 0.8649 0.0830
-3.000 -0.0568 0.03463 0.02434 -0.0552 0.8553 0.0859
-2.750 -0.0180 0.03302 0.02228 -0.0568 0.8496 0.0927
-2.250 0.0499 0.03037 0.01911 -0.0583 0.8332 0.1029
-2.000 0.0874 0.02946 0.01784 -0.0595 0.8240 0.1117
-1.750 0.1447 0.02811 0.01639 -0.0644 0.8194 0.1234
-1.500 0.1782 0.02743 0.01567 -0.0652 0.8086 0.1385
-1.250 0.2231 0.02646 0.01478 -0.0677 0.8017 0.1640
-1.000 0.2531 0.02588 0.01453 -0.0677 0.7905 0.2145
-0.750 0.2818 0.02548 0.01427 -0.0674 0.7792 0.3077
-0.500 0.4354 0.02268 0.01320 -0.0917 0.7758 1.0000
-0.250 0.4654 0.02265 0.01284 -0.0916 0.7623 1.0000
0.000 0.4955 0.02260 0.01251 -0.0915 0.7488 1.0000
0.250 0.5254 0.02256 0.01221 -0.0914 0.7351 1.0000
0.500 0.5537 0.02256 0.01197 -0.0910 0.7208 1.0000
0.750 0.5778 0.02265 0.01187 -0.0899 0.7050 1.0000
1.000 0.6015 0.02277 0.01182 -0.0888 0.6894 1.0000
1.250 0.6247 0.02292 0.01181 -0.0876 0.6741 1.0000
1.500 0.6475 0.02311 0.01184 -0.0864 0.6592 1.0000
1.750 0.6700 0.02332 0.01192 -0.0852 0.6448 1.0000
2.000 0.6926 0.02356 0.01203 -0.0841 0.6312 1.0000
2.250 0.7163 0.02379 0.01213 -0.0831 0.6189 1.0000
2.500 0.7427 0.02396 0.01216 -0.0826 0.6082 1.0000
2.750 0.7620 0.02436 0.01250 -0.0811 0.5959 1.0000
3.000 0.7836 0.02472 0.01278 -0.0799 0.5850 1.0000
3.250 0.8102 0.02493 0.01287 -0.0795 0.5761 1.0000
3.500 0.8280 0.02543 0.01337 -0.0778 0.5655 1.0000
3.750 0.8510 0.02577 0.01366 -0.0768 0.5564 1.0000
4.000 0.8730 0.02613 0.01396 -0.0757 0.5469 1.0000
4.250 0.8916 0.02656 0.01437 -0.0740 0.5362 1.0000
4.500 0.9133 0.02682 0.01457 -0.0727 0.5252 1.0000
4.750 0.9353 0.02705 0.01472 -0.0714 0.5138 1.0000
5.000 0.9513 0.02750 0.01515 -0.0693 0.5017 1.0000
5.250 0.9702 0.02789 0.01553 -0.0677 0.4907 1.0000
5.500 0.9946 0.02817 0.01572 -0.0669 0.4811 1.0000
5.750 1.0100 0.02880 0.01642 -0.0649 0.4715 1.0000
6.000 1.0327 0.02924 0.01687 -0.0639 0.4631 1.0000
6.250 1.0502 0.02985 0.01753 -0.0623 0.4540 1.0000
6.500 1.0703 0.03041 0.01812 -0.0610 0.4454 1.0000
6.750 1.0894 0.03101 0.01877 -0.0596 0.4365 1.0000
7.000 1.1063 0.03171 0.01957 -0.0580 0.4278 1.0000
7.250 1.1265 0.03233 0.02024 -0.0568 0.4192 1.0000
7.500 1.1401 0.03316 0.02120 -0.0547 0.4105 1.0000
7.750 1.1608 0.03378 0.02187 -0.0536 0.4017 1.0000
8.000 1.1692 0.03476 0.02304 -0.0508 0.3925 1.0000
8.250 1.1917 0.03532 0.02362 -0.0499 0.3840 1.0000
8.500 1.1934 0.03650 0.02501 -0.0463 0.3744 1.0000
8.750 1.2152 0.03705 0.02559 -0.0453 0.3663 1.0000
9.000 1.2130 0.03842 0.02721 -0.0413 0.3571 1.0000
9.250 1.2341 0.03903 0.02787 -0.0403 0.3499 1.0000
9.500 1.2262 0.04065 0.02972 -0.0357 0.3419 1.0000
9.750 1.2472 0.04128 0.03042 -0.0348 0.3355 1.0000
10.000 1.2359 0.04322 0.03258 -0.0302 0.3285 1.0000
10.250 1.2450 0.04431 0.03378 -0.0280 0.3221 1.0000
10.500 1.2445 0.04587 0.03551 -0.0250 0.3156 1.0000
10.750 1.2377 0.04786 0.03766 -0.0218 0.3089 1.0000
11.000 1.2525 0.04847 0.03834 -0.0203 0.3026 1.0000
11.250 1.2254 0.05232 0.04240 -0.0167 0.2967 1.0000
11.500 1.2520 0.05174 0.04187 -0.0157 0.2897 1.0000
11.750 1.2147 0.05725 0.04758 -0.0130 0.2852 1.0000
12.000 1.1688 0.06466 0.05513 -0.0118 0.2803 1.0000
12.250 1.2162 0.06127 0.05182 -0.0104 0.2734 1.0000
12.500 1.0234 0.09308 0.08350 -0.0185 0.2658 1.0000
12.750 1.0544 0.09076 0.08135 -0.0163 0.2622 1.0000
13.250 1.0170 0.10419 0.09487 -0.0197 0.2485 1.0000
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Polar data table (+)
Polar graphs
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