GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 424 AIRFOIL (goe424-il) Reynolds number: 100,000 Max Cl/Cd: 37.38 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe424-il-100000-n5.txt Download as CSV file: xf-goe424-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 424 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2840 0.09338 0.08845 -0.0824 0.9760 0.0482
-11.750 -0.3661 0.07220 0.06697 -0.1000 0.9681 0.0465
-11.500 -0.4085 0.06334 0.05775 -0.1076 0.9558 0.0460
-11.250 -0.4283 0.05879 0.05293 -0.1095 0.9414 0.0461
-11.000 -0.4424 0.05551 0.04941 -0.1087 0.9252 0.0463
-10.750 -0.4518 0.05284 0.04651 -0.1068 0.9084 0.0467
-10.500 -0.4550 0.05038 0.04380 -0.1049 0.8919 0.0474
-10.250 -0.4563 0.04794 0.04104 -0.1029 0.8754 0.0483
-10.000 -0.4562 0.04550 0.03818 -0.1007 0.8590 0.0493
-9.750 -0.4545 0.04317 0.03531 -0.0983 0.8428 0.0502
-9.500 -0.4444 0.04102 0.03273 -0.0966 0.8270 0.0509
-9.250 -0.4209 0.03917 0.03080 -0.0967 0.8118 0.0518
-9.000 -0.3998 0.03764 0.02909 -0.0963 0.7961 0.0531
-8.750 -0.3809 0.03617 0.02733 -0.0954 0.7800 0.0545
-8.500 -0.3619 0.03474 0.02553 -0.0944 0.7640 0.0557
-8.250 -0.3414 0.03340 0.02382 -0.0934 0.7485 0.0566
-8.000 -0.3203 0.03226 0.02229 -0.0924 0.7340 0.0576
-7.750 -0.2946 0.03094 0.02093 -0.0924 0.7201 0.0590
-7.500 -0.2697 0.02993 0.01981 -0.0921 0.7075 0.0604
-7.250 -0.2440 0.02898 0.01868 -0.0919 0.6970 0.0616
-7.000 -0.2185 0.02811 0.01764 -0.0916 0.6870 0.0627
-6.750 -0.1930 0.02738 0.01671 -0.0912 0.6785 0.0640
-6.500 -0.1676 0.02664 0.01585 -0.0909 0.6702 0.0656
-6.250 -0.1418 0.02582 0.01504 -0.0907 0.6632 0.0671
-6.000 -0.1181 0.02520 0.01440 -0.0902 0.6557 0.0683
-5.750 -0.0942 0.02463 0.01375 -0.0896 0.6494 0.0696
-5.500 -0.0714 0.02415 0.01320 -0.0889 0.6436 0.0712
-5.250 -0.0492 0.02376 0.01272 -0.0880 0.6377 0.0731
-5.000 -0.0281 0.02326 0.01219 -0.0871 0.6329 0.0750
-4.750 -0.0057 0.02286 0.01169 -0.0863 0.6288 0.0770
-4.500 0.0155 0.02254 0.01133 -0.0854 0.6240 0.0790
-4.250 0.0380 0.02227 0.01097 -0.0846 0.6193 0.0813
-4.000 0.0610 0.02198 0.01059 -0.0839 0.6151 0.0847
-3.750 0.0853 0.02170 0.01021 -0.0834 0.6115 0.0896
-3.500 0.1079 0.02149 0.00997 -0.0826 0.6072 0.0955
-3.250 0.1304 0.02123 0.00973 -0.0819 0.6031 0.1062
-3.000 0.1486 0.02039 0.00942 -0.0808 0.5997 0.2152
-2.750 0.1648 0.01953 0.00934 -0.0792 0.5966 0.3856
-2.500 0.1875 0.01932 0.00936 -0.0783 0.5939 0.4699
-2.250 0.2098 0.01927 0.00950 -0.0772 0.5907 0.5268
-2.000 0.2321 0.01930 0.00965 -0.0762 0.5869 0.5686
-1.750 0.2555 0.01936 0.00978 -0.0752 0.5833 0.6064
-1.500 0.2805 0.01944 0.00987 -0.0746 0.5801 0.6377
-1.250 0.3066 0.01954 0.00996 -0.0741 0.5775 0.6665
-1.000 0.3333 0.01965 0.01009 -0.0737 0.5752 0.6990
-0.750 0.3571 0.01983 0.01032 -0.0728 0.5723 0.7288
-0.500 0.3803 0.02004 0.01062 -0.0718 0.5689 0.7562
-0.250 0.4039 0.02025 0.01089 -0.0707 0.5656 0.7870
0.000 0.4307 0.02049 0.01116 -0.0702 0.5627 0.8149
0.250 0.4591 0.02073 0.01135 -0.0701 0.5601 0.8387
0.500 0.4902 0.02096 0.01151 -0.0706 0.5579 0.8571
0.750 0.5226 0.02121 0.01167 -0.0716 0.5556 0.8722
1.000 0.5486 0.02155 0.01207 -0.0715 0.5521 0.8884
1.250 0.5776 0.02188 0.01240 -0.0721 0.5488 0.9042
1.500 0.6087 0.02220 0.01269 -0.0731 0.5459 0.9195
1.750 0.6445 0.02249 0.01292 -0.0749 0.5431 0.9324
2.000 0.6835 0.02274 0.01308 -0.0775 0.5406 0.9433
2.250 0.7225 0.02297 0.01321 -0.0800 0.5383 0.9546
2.500 0.7576 0.02342 0.01369 -0.0822 0.5351 0.9660
2.750 0.7944 0.02387 0.01419 -0.0849 0.5315 0.9764
3.000 0.8337 0.02423 0.01455 -0.0880 0.5280 0.9867
3.250 0.8766 0.02451 0.01480 -0.0917 0.5250 0.9962
3.500 0.9060 0.02472 0.01495 -0.0927 0.5225 1.0000
3.750 0.9261 0.02489 0.01504 -0.0917 0.5203 1.0000
4.000 0.9295 0.02540 0.01562 -0.0879 0.5170 1.0000
4.250 0.9312 0.02597 0.01627 -0.0838 0.5131 1.0000
4.500 0.9405 0.02639 0.01670 -0.0810 0.5097 1.0000
4.750 0.9567 0.02667 0.01695 -0.0793 0.5067 1.0000
5.000 0.9788 0.02684 0.01707 -0.0785 0.5041 1.0000
5.250 1.0069 0.02694 0.01709 -0.0788 0.5018 1.0000
5.500 0.9923 0.02798 0.01830 -0.0722 0.4965 1.0000
5.750 0.9995 0.02855 0.01891 -0.0691 0.4922 1.0000
6.000 1.0205 0.02872 0.01906 -0.0682 0.4886 1.0000
6.250 1.0516 0.02862 0.01889 -0.0688 0.4857 1.0000
6.500 1.0503 0.02946 0.01982 -0.0646 0.4808 1.0000
6.750 1.0434 0.03041 0.02087 -0.0596 0.4754 1.0000
7.000 1.0625 0.03061 0.02107 -0.0585 0.4715 1.0000
7.250 1.0951 0.03046 0.02088 -0.0594 0.4687 1.0000
7.500 1.0807 0.03184 0.02237 -0.0537 0.4634 1.0000
7.750 1.0663 0.03351 0.02415 -0.0488 0.4573 1.0000
8.000 1.0896 0.03364 0.02429 -0.0484 0.4539 1.0000
8.250 1.1252 0.03326 0.02388 -0.0494 0.4515 1.0000
8.500 1.0546 0.03843 0.02930 -0.0401 0.4404 1.0000
8.750 1.0818 0.03827 0.02915 -0.0401 0.4373 1.0000
9.000 1.1204 0.03741 0.02828 -0.0410 0.4351 1.0000
9.500 1.0832 0.04350 0.03456 -0.0349 0.4193 1.0000
10.000 1.0496 0.05096 0.04217 -0.0315 0.4012 1.0000
10.500 1.0498 0.05575 0.04706 -0.0300 0.3862 1.0000
11.500 1.0455 0.06651 0.05805 -0.0278 0.3540 1.0000
12.000 1.0666 0.06932 0.06094 -0.0272 0.3424 1.0000
13.000 1.0792 0.07884 0.07068 -0.0262 0.3146 1.0000
13.500 1.0937 0.08259 0.07452 -0.0259 0.3017 1.0000
13.750 1.1201 0.08192 0.07388 -0.0256 0.2983 1.0000
14.000 1.1542 0.08026 0.07223 -0.0253 0.2960 1.0000
14.500 1.1504 0.08657 0.07868 -0.0254 0.2822 1.0000
14.750 1.1821 0.08522 0.07735 -0.0250 0.2802 1.0000
15.250 1.1660 0.09337 0.08567 -0.0255 0.2666 1.0000
15.500 1.1982 0.09187 0.08420 -0.0251 0.2647 1.0000
15.750 1.1477 0.10212 0.09459 -0.0265 0.2533 1.0000
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Polar data table (+)
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