GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 50,000 Max Cl/Cd: 28.6 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe513-il-50000-n5.txt Download as CSV file: xf-goe513-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3551 0.11255 0.10605 -0.0326 1.0000 0.0819
-9.250 -0.3675 0.10855 0.10212 -0.0335 0.9988 0.0806
-9.000 -0.3979 0.09778 0.09133 -0.0437 0.9911 0.0772
-8.750 -0.3957 0.09270 0.08623 -0.0484 0.9834 0.0766
-8.500 -0.4031 0.08752 0.08102 -0.0516 0.9743 0.0761
-8.000 -0.4294 0.07554 0.06878 -0.0560 0.9543 0.0749
-7.750 -0.4471 0.06951 0.06250 -0.0557 0.9424 0.0745
-7.500 -0.4618 0.06444 0.05709 -0.0540 0.9316 0.0745
-7.250 -0.4655 0.05947 0.05164 -0.0530 0.9234 0.0752
-7.000 -0.4710 0.05594 0.04770 -0.0498 0.9126 0.0757
-6.750 -0.4678 0.05258 0.04380 -0.0475 0.9038 0.0765
-6.500 -0.4577 0.04973 0.04043 -0.0456 0.8951 0.0771
-6.250 -0.4450 0.04769 0.03812 -0.0437 0.8860 0.0777
-6.000 -0.4214 0.04583 0.03604 -0.0434 0.8782 0.0786
-5.750 -0.4056 0.04435 0.03436 -0.0416 0.8681 0.0795
-5.500 -0.3765 0.04268 0.03244 -0.0419 0.8611 0.0811
-5.250 -0.3606 0.04152 0.03107 -0.0399 0.8499 0.0829
-5.000 -0.3262 0.03996 0.02917 -0.0409 0.8436 0.0859
-4.750 -0.3085 0.03897 0.02800 -0.0390 0.8314 0.0880
-4.500 -0.2810 0.03794 0.02695 -0.0389 0.8220 0.0906
-4.250 -0.2502 0.03688 0.02575 -0.0391 0.8128 0.0937
-4.000 -0.2230 0.03602 0.02471 -0.0387 0.8020 0.0970
-3.750 -0.1837 0.03493 0.02361 -0.0404 0.7943 0.1034
-3.500 -0.1529 0.03423 0.02285 -0.0407 0.7829 0.1117
-3.250 -0.1039 0.03314 0.02191 -0.0442 0.7763 0.1272
-3.000 -0.0740 0.03265 0.02172 -0.0444 0.7647 0.1535
-2.750 -0.0413 0.03225 0.02141 -0.0444 0.7571 0.2071
-2.500 -0.0275 0.03241 0.02144 -0.0414 0.7436 0.2395
-2.250 0.0036 0.03209 0.02086 -0.0409 0.7369 0.2705
-2.000 0.0136 0.03229 0.02102 -0.0375 0.7226 0.2919
-1.750 0.0367 0.03201 0.02067 -0.0359 0.7149 0.3249
-1.500 0.0566 0.03194 0.02064 -0.0344 0.7023 0.3495
-1.250 0.1056 0.03127 0.01981 -0.0378 0.6951 0.3691
-1.000 0.1398 0.03115 0.01950 -0.0390 0.6831 0.3779
-0.750 0.1906 0.03060 0.01884 -0.0430 0.6747 0.3876
-0.500 0.2257 0.03042 0.01852 -0.0442 0.6635 0.3961
-0.250 0.2611 0.03019 0.01825 -0.0455 0.6531 0.4044
0.000 0.3007 0.02982 0.01778 -0.0474 0.6439 0.4158
0.250 0.3242 0.02977 0.01776 -0.0467 0.6326 0.4260
0.500 0.3659 0.02919 0.01715 -0.0488 0.6244 0.4409
1.000 0.4171 0.02849 0.01673 -0.0478 0.6049 0.4928
1.500 0.7179 0.02832 0.01700 -0.0932 0.5715 1.0000
1.750 0.7320 0.02869 0.01724 -0.0908 0.5604 1.0000
2.000 0.7583 0.02882 0.01712 -0.0903 0.5504 1.0000
2.250 0.7754 0.02917 0.01735 -0.0884 0.5402 1.0000
2.500 0.7986 0.02944 0.01743 -0.0876 0.5308 1.0000
2.750 0.8160 0.02983 0.01771 -0.0857 0.5210 1.0000
3.000 0.8386 0.03015 0.01788 -0.0848 0.5122 1.0000
3.250 0.8517 0.03065 0.01832 -0.0823 0.5026 1.0000
3.500 0.8768 0.03095 0.01846 -0.0818 0.4944 1.0000
3.750 0.8826 0.03160 0.01913 -0.0781 0.4851 1.0000
4.000 0.9110 0.03185 0.01920 -0.0782 0.4773 1.0000
4.250 0.9105 0.03264 0.02006 -0.0735 0.4683 1.0000
4.500 0.9292 0.03304 0.02036 -0.0719 0.4603 1.0000
4.750 0.9376 0.03369 0.02100 -0.0687 0.4525 1.0000
5.000 0.9455 0.03433 0.02164 -0.0655 0.4444 1.0000
5.250 0.9686 0.03467 0.02184 -0.0647 0.4375 1.0000
5.500 0.9603 0.03563 0.02290 -0.0588 0.4294 1.0000
5.750 0.9770 0.03604 0.02324 -0.0570 0.4226 1.0000
6.000 0.9781 0.03682 0.02404 -0.0528 0.4154 1.0000
6.250 0.9789 0.03763 0.02488 -0.0486 0.4082 1.0000
6.500 1.0050 0.03784 0.02496 -0.0482 0.4025 1.0000
6.750 0.9898 0.03925 0.02649 -0.0420 0.3954 1.0000
7.000 0.9971 0.04007 0.02732 -0.0391 0.3893 1.0000
7.250 1.0267 0.04017 0.02729 -0.0392 0.3844 1.0000
7.500 1.0016 0.04226 0.02956 -0.0324 0.3775 1.0000
7.750 1.0090 0.04319 0.03049 -0.0298 0.3717 1.0000
8.000 1.0390 0.04318 0.03036 -0.0299 0.3673 1.0000
8.250 1.0046 0.04622 0.03361 -0.0231 0.3605 1.0000
8.500 1.0057 0.04769 0.03512 -0.0203 0.3552 1.0000
8.750 1.0303 0.04792 0.03528 -0.0198 0.3516 1.0000
9.000 0.9973 0.05175 0.03927 -0.0147 0.3458 1.0000
9.250 0.9605 0.05649 0.04416 -0.0105 0.3392 1.0000
9.500 0.9793 0.05705 0.04469 -0.0095 0.3358 1.0000
9.750 1.0188 0.05601 0.04358 -0.0096 0.3335 1.0000
10.000 0.8764 0.07251 0.06044 -0.0051 0.3194 1.0000
10.250 0.9039 0.07190 0.05980 -0.0041 0.3175 1.0000
10.750 0.8149 0.09042 0.07853 -0.0053 0.3009 1.0000
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Polar data table (+)
Polar graphs
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