GOE 419 AIRFOIL (goe419-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 419 AIRFOIL (goe419-il) Reynolds number: 100,000 Max Cl/Cd: 59.99 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe419-il-100000.txt Download as CSV file: xf-goe419-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 419 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3702 0.09513 0.09040 -0.0233 1.0000 0.0472
-7.500 -0.3720 0.09294 0.08830 -0.0232 1.0000 0.0483
-7.250 -0.3721 0.09062 0.08605 -0.0240 1.0000 0.0495
-7.000 -0.3694 0.08843 0.08393 -0.0263 1.0000 0.0507
-6.750 -0.3631 0.08692 0.08246 -0.0317 1.0000 0.0517
-6.500 -0.3523 0.08514 0.08066 -0.0367 1.0000 0.0521
-6.250 -0.3447 0.08165 0.07720 -0.0383 1.0000 0.0525
-6.000 -0.3492 0.07625 0.07193 -0.0321 1.0000 0.0539
-5.750 -0.3465 0.07315 0.06888 -0.0300 1.0000 0.0559
-5.500 -0.3409 0.07042 0.06616 -0.0298 1.0000 0.0583
-5.250 -0.3306 0.06779 0.06343 -0.0315 1.0000 0.0624
-5.000 -0.2990 0.06635 0.06166 -0.0402 1.0000 0.0656
-4.750 -0.3085 0.06154 0.05712 -0.0341 1.0000 0.0686
-4.500 -0.2962 0.05891 0.05444 -0.0344 1.0000 0.0752
-4.250 -0.2722 0.05561 0.05093 -0.0384 1.0000 0.0803
-4.000 -0.2639 0.05259 0.04795 -0.0368 1.0000 0.0844
-3.750 -0.2356 0.04979 0.04485 -0.0404 1.0000 0.0935
-3.500 -0.2250 0.04680 0.04191 -0.0391 1.0000 0.0991
-3.250 -0.2019 0.04395 0.03887 -0.0407 1.0000 0.1090
-3.000 -0.1792 0.04155 0.03626 -0.0418 1.0000 0.1213
-2.750 -0.1588 0.03916 0.03374 -0.0421 1.0000 0.1351
-2.500 -0.1384 0.03689 0.03136 -0.0423 1.0000 0.1500
-2.250 -0.1169 0.03493 0.02917 -0.0426 1.0000 0.1756
-1.750 -0.0183 0.02776 0.02053 -0.0489 0.9931 0.1024
-1.500 0.0327 0.02424 0.01593 -0.0512 0.9870 0.0776
-1.250 0.0784 0.02228 0.01364 -0.0546 0.9797 0.0866
-1.000 0.1230 0.02078 0.01179 -0.0574 0.9719 0.0980
-0.750 0.1638 0.01985 0.01072 -0.0599 0.9631 0.1156
-0.500 0.2082 0.01893 0.00979 -0.0631 0.9560 0.1344
-0.250 0.2477 0.01796 0.00901 -0.0653 0.9469 0.1944
0.000 0.3069 0.01571 0.00840 -0.0715 0.9439 1.0000
0.250 0.3482 0.01576 0.00821 -0.0743 0.9329 1.0000
0.500 0.3888 0.01579 0.00810 -0.0770 0.9219 1.0000
0.750 0.4312 0.01576 0.00796 -0.0799 0.9116 1.0000
1.000 0.4837 0.01552 0.00766 -0.0846 0.9051 1.0000
1.250 0.5245 0.01543 0.00755 -0.0870 0.8937 1.0000
1.500 0.5649 0.01531 0.00745 -0.0892 0.8821 1.0000
1.750 0.6044 0.01519 0.00743 -0.0912 0.8701 1.0000
2.000 0.6422 0.01508 0.00739 -0.0927 0.8571 1.0000
2.250 0.6773 0.01501 0.00740 -0.0937 0.8429 1.0000
2.500 0.7103 0.01497 0.00747 -0.0941 0.8277 1.0000
2.750 0.7424 0.01492 0.00755 -0.0942 0.8119 1.0000
3.000 0.7632 0.01371 0.00632 -0.0890 0.7521 1.0000
3.250 0.7844 0.01338 0.00595 -0.0859 0.7038 1.0000
3.500 0.8020 0.01337 0.00562 -0.0820 0.6253 1.0000
3.750 0.8108 0.01408 0.00554 -0.0770 0.4715 1.0000
4.000 0.8160 0.01593 0.00603 -0.0727 0.2470 1.0000
4.250 0.8229 0.01853 0.00737 -0.0695 0.0566 1.0000
4.500 0.8439 0.01940 0.00845 -0.0679 0.0516 1.0000
4.750 0.8630 0.02045 0.00972 -0.0659 0.0490 1.0000
5.000 0.8795 0.02169 0.01116 -0.0636 0.0476 1.0000
5.250 0.8902 0.02359 0.01320 -0.0605 0.0446 1.0000
5.500 0.9095 0.02498 0.01466 -0.0587 0.0422 1.0000
5.750 0.9345 0.02707 0.01670 -0.0576 0.0432 1.0000
6.000 0.9687 0.03018 0.01973 -0.0580 0.0451 1.0000
6.250 0.9981 0.03106 0.02105 -0.0564 0.0500 1.0000
6.500 1.0357 0.03600 0.02606 -0.0571 0.0568 1.0000
6.750 1.0677 0.03949 0.03005 -0.0557 0.0688 1.0000
7.000 1.0580 0.02983 0.02236 -0.0465 0.1031 1.0000
9.750 0.9234 0.11123 0.10673 -0.0579 0.2287 1.0000
11.750 0.7723 0.14366 0.13939 -0.0590 0.1650 1.0000
12.000 0.7963 0.14818 0.14394 -0.0568 0.1574 1.0000
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Polar data table (+)
Polar graphs
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