GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 100,000 Max Cl/Cd: 52.22 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe509-il-100000-n5.txt Download as CSV file: xf-goe509-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3016 0.10941 0.10477 -0.0342 1.0000 0.0527
-9.000 -0.3132 0.10751 0.10298 -0.0343 1.0000 0.0532
-8.750 -0.3236 0.10557 0.10112 -0.0336 1.0000 0.0534
-8.500 -0.3251 0.10253 0.09815 -0.0359 0.9972 0.0535
-8.000 -0.3036 0.08863 0.08420 -0.0461 0.9847 0.0350
-7.750 -0.2901 0.08458 0.08013 -0.0497 0.9766 0.0345
-7.500 -0.2782 0.07883 0.07435 -0.0567 0.9658 0.0349
-7.250 -0.2664 0.07317 0.06862 -0.0624 0.9552 0.0351
-7.000 -0.2536 0.06715 0.06249 -0.0678 0.9452 0.0353
-6.500 -0.2303 0.05696 0.05203 -0.0728 0.9244 0.0352
-6.250 -0.2221 0.05085 0.04565 -0.0741 0.9128 0.0353
-6.000 -0.2005 0.04820 0.04291 -0.0753 0.9063 0.0364
-5.750 -0.1862 0.04667 0.04129 -0.0744 0.8952 0.0381
-5.500 -0.1736 0.04242 0.03671 -0.0740 0.8851 0.0397
-5.250 -0.1563 0.03728 0.03099 -0.0740 0.8787 0.0408
-5.000 -0.1447 0.03347 0.02656 -0.0717 0.8687 0.0421
-4.750 -0.1196 0.03051 0.02300 -0.0716 0.8637 0.0449
-4.500 -0.0982 0.02928 0.02163 -0.0706 0.8546 0.0470
-4.250 -0.0663 0.02725 0.01915 -0.0712 0.8498 0.0498
-4.000 -0.0420 0.02578 0.01716 -0.0701 0.8406 0.0534
-3.750 -0.0070 0.02400 0.01511 -0.0713 0.8351 0.0559
-3.500 0.0207 0.02315 0.01413 -0.0711 0.8256 0.0596
-3.250 0.0577 0.02201 0.01269 -0.0724 0.8199 0.0637
-3.000 0.0866 0.02121 0.01162 -0.0722 0.8112 0.0663
-2.750 0.1218 0.02021 0.01064 -0.0736 0.8046 0.0712
-2.500 0.1503 0.01958 0.00991 -0.0734 0.7949 0.0752
-2.250 0.1859 0.01890 0.00905 -0.0745 0.7872 0.0798
-2.000 0.2111 0.01838 0.00856 -0.0738 0.7763 0.0858
-1.750 0.2419 0.01793 0.00800 -0.0741 0.7670 0.0939
-1.500 0.2698 0.01746 0.00754 -0.0739 0.7566 0.1030
-1.250 0.2978 0.01707 0.00718 -0.0737 0.7454 0.1202
-1.000 0.3307 0.01654 0.00692 -0.0745 0.7343 0.1732
-0.750 0.3590 0.01636 0.00694 -0.0744 0.7217 0.2751
-0.500 0.3839 0.01631 0.00686 -0.0736 0.7077 0.3196
-0.250 0.4092 0.01619 0.00674 -0.0729 0.6936 0.3533
0.000 0.4340 0.01601 0.00659 -0.0722 0.6792 0.3933
0.250 0.4564 0.01560 0.00639 -0.0710 0.6642 0.4582
0.500 0.6273 0.01493 0.00657 -0.1002 0.6365 0.9966
0.750 0.6571 0.01504 0.00649 -0.1006 0.6170 1.0000
1.000 0.6783 0.01518 0.00645 -0.0991 0.5988 1.0000
1.250 0.6992 0.01533 0.00643 -0.0976 0.5810 1.0000
1.500 0.7199 0.01551 0.00644 -0.0961 0.5638 1.0000
1.750 0.7404 0.01571 0.00648 -0.0946 0.5480 1.0000
2.000 0.7609 0.01593 0.00654 -0.0931 0.5335 1.0000
2.250 0.7812 0.01616 0.00663 -0.0916 0.5202 1.0000
2.500 0.8016 0.01640 0.00673 -0.0901 0.5080 1.0000
2.750 0.8219 0.01667 0.00684 -0.0886 0.4968 1.0000
3.000 0.8423 0.01694 0.00702 -0.0871 0.4862 1.0000
3.250 0.8628 0.01723 0.00721 -0.0857 0.4766 1.0000
3.500 0.8833 0.01753 0.00740 -0.0843 0.4675 1.0000
3.750 0.9035 0.01783 0.00764 -0.0829 0.4584 1.0000
4.000 0.9243 0.01817 0.00787 -0.0815 0.4501 1.0000
4.250 0.9447 0.01846 0.00816 -0.0802 0.4425 1.0000
4.500 0.9661 0.01879 0.00845 -0.0790 0.4362 1.0000
4.750 0.9878 0.01913 0.00877 -0.0779 0.4305 1.0000
5.000 1.0083 0.01945 0.00913 -0.0766 0.4242 1.0000
5.250 1.0299 0.01981 0.00945 -0.0755 0.4183 1.0000
5.500 1.0500 0.02016 0.00983 -0.0742 0.4119 1.0000
5.750 1.0698 0.02051 0.01023 -0.0728 0.4051 1.0000
6.000 1.0908 0.02089 0.01059 -0.0716 0.3990 1.0000
6.250 1.1084 0.02123 0.01105 -0.0698 0.3917 1.0000
6.500 1.1278 0.02160 0.01144 -0.0683 0.3849 1.0000
6.750 1.1452 0.02196 0.01190 -0.0665 0.3777 1.0000
7.000 1.1626 0.02233 0.01233 -0.0647 0.3705 1.0000
7.250 1.1796 0.02270 0.01278 -0.0629 0.3631 1.0000
7.500 1.1943 0.02306 0.01325 -0.0606 0.3544 1.0000
7.750 1.2086 0.02343 0.01370 -0.0583 0.3455 1.0000
8.000 1.2214 0.02379 0.01411 -0.0557 0.3361 1.0000
8.250 1.2328 0.02419 0.01463 -0.0529 0.3251 1.0000
8.500 1.2433 0.02460 0.01509 -0.0500 0.3151 1.0000
8.750 1.2517 0.02501 0.01557 -0.0467 0.3053 1.0000
9.000 1.2606 0.02549 0.01613 -0.0436 0.2951 1.0000
9.250 1.2681 0.02602 0.01669 -0.0404 0.2847 1.0000
9.500 1.2745 0.02661 0.01727 -0.0371 0.2742 1.0000
9.750 1.2815 0.02730 0.01800 -0.0342 0.2630 1.0000
10.000 1.2897 0.02805 0.01882 -0.0315 0.2542 1.0000
10.250 1.2961 0.02888 0.01965 -0.0288 0.2461 1.0000
10.500 1.3048 0.02975 0.02062 -0.0265 0.2382 1.0000
11.000 1.3197 0.03169 0.02271 -0.0219 0.2255 1.0000
11.250 1.3253 0.03280 0.02387 -0.0196 0.2194 1.0000
11.500 1.3308 0.03400 0.02520 -0.0175 0.2122 1.0000
11.750 1.3333 0.03539 0.02664 -0.0153 0.2050 1.0000
12.000 1.3379 0.03679 0.02816 -0.0135 0.1986 1.0000
12.250 1.3413 0.03832 0.02980 -0.0117 0.1928 1.0000
12.500 1.3429 0.04003 0.03159 -0.0100 0.1869 1.0000
12.750 1.3445 0.04186 0.03360 -0.0086 0.1801 1.0000
13.000 1.3426 0.04401 0.03579 -0.0071 0.1739 1.0000
13.250 1.3414 0.04629 0.03829 -0.0060 0.1660 1.0000
13.500 1.3345 0.04914 0.04119 -0.0050 0.1580 1.0000
13.750 1.3288 0.05220 0.04445 -0.0044 0.1472 1.0000
14.000 1.3218 0.05554 0.04796 -0.0041 0.1359 1.0000
14.250 1.3120 0.05943 0.05199 -0.0041 0.1158 1.0000
14.500 1.2921 0.06468 0.05717 -0.0047 0.0958 1.0000
14.750 1.2709 0.07048 0.06291 -0.0058 0.0876 1.0000
15.000 1.2510 0.07641 0.06883 -0.0071 0.0792 1.0000
15.500 1.2180 0.08784 0.08040 -0.0099 0.0629 1.0000
15.750 1.2022 0.09365 0.08629 -0.0115 0.0570 1.0000
16.000 1.1847 0.09983 0.09253 -0.0134 0.0527 1.0000
16.250 1.1681 0.10602 0.09879 -0.0154 0.0504 1.0000
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Polar data table (+)
Polar graphs
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