GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 500,000 Max Cl/Cd: 110.42 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe426-il-500000-n5.txt Download as CSV file: xf-goe426-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 426 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2975 0.11460 0.11216 -0.0432 1.0000 0.0200
-11.500 -0.2982 0.11042 0.10799 -0.0447 1.0000 0.0205
-11.250 -0.3074 0.10239 0.09996 -0.0494 0.9856 0.0215
-11.000 -0.2845 0.09959 0.09714 -0.0538 0.9733 0.0217
-10.750 -0.2601 0.09619 0.09371 -0.0592 0.9618 0.0221
-10.500 -0.2384 0.09142 0.08891 -0.0660 0.9496 0.0224
-10.250 -0.2183 0.08616 0.08359 -0.0733 0.9340 0.0226
-10.000 -0.2029 0.08126 0.07859 -0.0794 0.9125 0.0231
-9.750 -0.1996 0.07652 0.07377 -0.0832 0.8850 0.0232
-9.500 -0.2031 0.07206 0.06920 -0.0856 0.8554 0.0235
-9.250 -0.2127 0.06719 0.06422 -0.0878 0.8262 0.0237
-9.000 -0.2369 0.05997 0.05691 -0.0916 0.7989 0.0242
-8.750 -0.3353 0.04014 0.03660 -0.1046 0.7741 0.0242
-8.500 -0.3654 0.03041 0.02604 -0.1052 0.7601 0.0247
-8.250 -0.3611 0.02609 0.02109 -0.1046 0.7483 0.0252
-8.000 -0.3447 0.02402 0.01862 -0.1040 0.7373 0.0255
-7.750 -0.3251 0.02249 0.01687 -0.1037 0.7275 0.0258
-7.500 -0.3033 0.02136 0.01555 -0.1033 0.7174 0.0260
-7.250 -0.2799 0.02048 0.01451 -0.1030 0.7079 0.0262
-7.000 -0.2563 0.01966 0.01352 -0.1027 0.6985 0.0265
-6.750 -0.2318 0.01886 0.01257 -0.1024 0.6893 0.0267
-6.500 -0.2072 0.01811 0.01167 -0.1021 0.6808 0.0269
-6.250 -0.1819 0.01740 0.01081 -0.1019 0.6719 0.0272
-6.000 -0.1566 0.01674 0.01000 -0.1016 0.6631 0.0275
-5.750 -0.1309 0.01612 0.00925 -0.1014 0.6531 0.0278
-5.500 -0.1050 0.01553 0.00853 -0.1011 0.6433 0.0280
-5.000 -0.0528 0.01451 0.00727 -0.1006 0.6231 0.0287
-4.750 -0.0265 0.01411 0.00676 -0.1004 0.6137 0.0292
-4.500 0.0000 0.01375 0.00630 -0.1002 0.6036 0.0296
-4.250 0.0266 0.01343 0.00588 -0.0999 0.5941 0.0300
-3.750 0.0795 0.01270 0.00500 -0.0995 0.5774 0.0306
-3.500 0.1057 0.01233 0.00457 -0.0992 0.5699 0.0310
-3.250 0.1325 0.01206 0.00426 -0.0991 0.5632 0.0315
-3.000 0.1594 0.01185 0.00402 -0.0989 0.5565 0.0320
-2.750 0.1863 0.01167 0.00379 -0.0987 0.5509 0.0325
-2.500 0.2136 0.01148 0.00358 -0.0986 0.5454 0.0331
-2.250 0.2408 0.01133 0.00338 -0.0985 0.5399 0.0337
-2.000 0.2680 0.01121 0.00320 -0.0984 0.5351 0.0344
-1.750 0.2957 0.01108 0.00305 -0.0983 0.5304 0.0353
-1.500 0.3232 0.01099 0.00293 -0.0982 0.5255 0.0362
-1.250 0.3503 0.01085 0.00276 -0.0981 0.5209 0.0375
-1.000 0.3780 0.01075 0.00265 -0.0981 0.5169 0.0388
-0.750 0.4058 0.01068 0.00256 -0.0980 0.5129 0.0403
-0.500 0.4335 0.01063 0.00249 -0.0980 0.5087 0.0420
-0.250 0.4609 0.01059 0.00242 -0.0979 0.5048 0.0445
0.000 0.4886 0.01054 0.00237 -0.0978 0.5014 0.0486
0.250 0.5164 0.01047 0.00232 -0.0978 0.4979 0.0573
0.500 0.5436 0.01024 0.00231 -0.0978 0.4942 0.1285
0.750 0.5687 0.00956 0.00233 -0.0978 0.4905 0.3822
1.000 0.5948 0.00936 0.00239 -0.0977 0.4869 0.4793
1.250 0.6216 0.00922 0.00247 -0.0975 0.4839 0.5604
1.500 0.6483 0.00913 0.00255 -0.0973 0.4803 0.6216
1.750 0.6740 0.00902 0.00265 -0.0968 0.4763 0.6905
2.000 0.6985 0.00892 0.00276 -0.0960 0.4727 0.7652
2.250 0.7233 0.00887 0.00284 -0.0952 0.4695 0.8151
2.500 0.7478 0.00876 0.00290 -0.0943 0.4661 0.8712
2.750 0.7929 0.00871 0.00296 -0.0979 0.4616 1.0000
3.000 0.8198 0.00883 0.00303 -0.0978 0.4574 1.0000
3.250 0.8465 0.00896 0.00312 -0.0976 0.4536 1.0000
3.500 0.8739 0.00904 0.00321 -0.0976 0.4500 1.0000
3.750 0.9010 0.00915 0.00330 -0.0974 0.4458 1.0000
4.000 0.9277 0.00928 0.00341 -0.0973 0.4414 1.0000
4.250 0.9541 0.00942 0.00352 -0.0971 0.4371 1.0000
4.500 0.9812 0.00952 0.00363 -0.0969 0.4324 1.0000
4.750 1.0077 0.00965 0.00376 -0.0968 0.4278 1.0000
5.000 1.0337 0.00981 0.00390 -0.0965 0.4233 1.0000
5.250 1.0602 0.00993 0.00404 -0.0963 0.4186 1.0000
5.500 1.0864 0.01008 0.00419 -0.0961 0.4129 1.0000
5.750 1.1116 0.01026 0.00435 -0.0957 0.4068 1.0000
6.000 1.1376 0.01040 0.00451 -0.0954 0.4002 1.0000
6.250 1.1626 0.01059 0.00470 -0.0950 0.3939 1.0000
6.500 1.1879 0.01077 0.00489 -0.0947 0.3884 1.0000
6.750 1.2124 0.01098 0.00509 -0.0942 0.3802 1.0000
7.000 1.2361 0.01122 0.00532 -0.0936 0.3698 1.0000
7.250 1.2588 0.01150 0.00556 -0.0928 0.3591 1.0000
7.500 1.2818 0.01176 0.00582 -0.0921 0.3492 1.0000
7.750 1.3036 0.01208 0.00611 -0.0912 0.3366 1.0000
8.000 1.3244 0.01244 0.00643 -0.0902 0.3233 1.0000
8.250 1.3442 0.01283 0.00678 -0.0890 0.3096 1.0000
8.500 1.3624 0.01328 0.00717 -0.0876 0.2931 1.0000
8.750 1.3780 0.01383 0.00763 -0.0858 0.2729 1.0000
9.000 1.3899 0.01445 0.00815 -0.0833 0.2502 1.0000
9.250 1.3950 0.01529 0.00883 -0.0798 0.2195 1.0000
9.500 1.3931 0.01650 0.00981 -0.0755 0.1806 1.0000
9.750 1.3868 0.01801 0.01110 -0.0709 0.1415 1.0000
10.000 1.3862 0.01937 0.01233 -0.0675 0.1180 1.0000
10.250 1.3886 0.02065 0.01356 -0.0646 0.1023 1.0000
10.500 1.3910 0.02203 0.01489 -0.0621 0.0864 1.0000
10.750 1.3894 0.02378 0.01655 -0.0595 0.0672 1.0000
11.000 1.3869 0.02574 0.01845 -0.0571 0.0517 1.0000
11.250 1.3859 0.02776 0.02045 -0.0552 0.0404 1.0000
11.500 1.3853 0.02989 0.02257 -0.0536 0.0310 1.0000
11.750 1.3856 0.03209 0.02477 -0.0523 0.0247 1.0000
12.000 1.3873 0.03426 0.02697 -0.0513 0.0216 1.0000
12.250 1.3892 0.03649 0.02926 -0.0504 0.0196 1.0000
12.500 1.3916 0.03874 0.03158 -0.0497 0.0184 1.0000
12.750 1.3944 0.04101 0.03392 -0.0491 0.0174 1.0000
13.000 1.3963 0.04346 0.03643 -0.0486 0.0167 1.0000
13.250 1.3963 0.04617 0.03922 -0.0482 0.0158 1.0000
13.500 1.3958 0.04903 0.04214 -0.0479 0.0152 1.0000
13.750 1.3969 0.05178 0.04497 -0.0478 0.0147 1.0000
14.000 1.3981 0.05459 0.04788 -0.0477 0.0143 1.0000
14.250 1.3985 0.05755 0.05093 -0.0477 0.0139 1.0000
14.500 1.3987 0.06060 0.05405 -0.0479 0.0134 1.0000
14.750 1.3983 0.06378 0.05732 -0.0481 0.0132 1.0000
15.000 1.3971 0.06712 0.06074 -0.0485 0.0129 1.0000
15.250 1.3952 0.07061 0.06430 -0.0489 0.0125 1.0000
15.500 1.3923 0.07430 0.06807 -0.0495 0.0123 1.0000
15.750 1.3880 0.07827 0.07212 -0.0502 0.0120 1.0000
16.000 1.3858 0.08201 0.07595 -0.0509 0.0118 1.0000
16.250 1.3853 0.08554 0.07957 -0.0516 0.0115 1.0000
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