GOE 426 AIRFOIL (goe426-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 426 AIRFOIL (goe426-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.28 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe426-il-1000000-n5.txt Download as CSV file: xf-goe426-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5083 0.03878 0.03635 -0.1114 0.8791 0.0202
-11.000 -0.6143 0.02731 0.02389 -0.1088 0.8348 0.0207
-10.750 -0.6083 0.02511 0.02134 -0.1076 0.8117 0.0209
-10.500 -0.5953 0.02355 0.01949 -0.1066 0.7890 0.0211
-10.250 -0.5785 0.02237 0.01807 -0.1059 0.7696 0.0211
-10.000 -0.5591 0.02142 0.01691 -0.1052 0.7541 0.0212
-9.750 -0.5419 0.01990 0.01514 -0.1046 0.7421 0.0214
-9.500 -0.5218 0.01878 0.01384 -0.1041 0.7314 0.0217
-9.250 -0.4984 0.01816 0.01312 -0.1037 0.7219 0.0219
-9.000 -0.4741 0.01769 0.01255 -0.1034 0.7134 0.0220
-8.750 -0.4494 0.01720 0.01198 -0.1032 0.7048 0.0222
-8.500 -0.4246 0.01672 0.01139 -0.1029 0.6966 0.0223
-8.250 -0.3996 0.01620 0.01077 -0.1027 0.6877 0.0225
-8.000 -0.3744 0.01570 0.01017 -0.1024 0.6793 0.0227
-7.750 -0.3490 0.01520 0.00957 -0.1022 0.6704 0.0228
-7.500 -0.3234 0.01471 0.00897 -0.1019 0.6624 0.0230
-7.250 -0.2975 0.01427 0.00844 -0.1017 0.6533 0.0232
-7.000 -0.2715 0.01382 0.00790 -0.1015 0.6444 0.0234
-6.750 -0.2455 0.01341 0.00738 -0.1013 0.6337 0.0236
-6.500 -0.2192 0.01301 0.00689 -0.1011 0.6224 0.0238
-6.250 -0.1929 0.01265 0.00643 -0.1009 0.6109 0.0240
-6.000 -0.1666 0.01232 0.00600 -0.1007 0.5995 0.0242
-5.750 -0.1399 0.01201 0.00561 -0.1005 0.5888 0.0244
-5.500 -0.1132 0.01172 0.00524 -0.1003 0.5791 0.0246
-5.000 -0.0593 0.01124 0.00461 -0.1000 0.5608 0.0251
-4.750 -0.0323 0.01104 0.00434 -0.0999 0.5531 0.0252
-4.500 -0.0047 0.01087 0.00412 -0.0998 0.5471 0.0254
-4.250 0.0221 0.01055 0.00374 -0.0996 0.5407 0.0259
-4.000 0.0491 0.01031 0.00346 -0.0995 0.5350 0.0263
-3.750 0.0768 0.01012 0.00324 -0.0995 0.5303 0.0266
-3.500 0.1044 0.00997 0.00307 -0.0994 0.5255 0.0270
-3.000 0.1599 0.00972 0.00276 -0.0993 0.5165 0.0277
-2.750 0.1879 0.00960 0.00261 -0.0993 0.5124 0.0281
-2.500 0.2157 0.00950 0.00248 -0.0993 0.5079 0.0285
-2.000 0.2716 0.00932 0.00225 -0.0992 0.5001 0.0294
-1.750 0.2998 0.00923 0.00215 -0.0992 0.4966 0.0299
-1.500 0.3278 0.00917 0.00206 -0.0992 0.4929 0.0303
-1.250 0.3557 0.00909 0.00195 -0.0992 0.4893 0.0312
-1.000 0.3836 0.00903 0.00189 -0.0992 0.4858 0.0324
-0.750 0.4119 0.00897 0.00184 -0.0992 0.4831 0.0337
-0.500 0.4402 0.00893 0.00180 -0.0993 0.4798 0.0348
-0.250 0.4683 0.00890 0.00176 -0.0993 0.4763 0.0359
0.000 0.4962 0.00887 0.00173 -0.0992 0.4728 0.0386
0.250 0.5242 0.00886 0.00172 -0.0992 0.4697 0.0417
0.500 0.5524 0.00882 0.00170 -0.0993 0.4669 0.0474
0.750 0.5805 0.00877 0.00169 -0.0993 0.4635 0.0593
1.250 0.6337 0.00803 0.00172 -0.0994 0.4566 0.3620
1.500 0.6610 0.00793 0.00177 -0.0993 0.4534 0.4222
1.750 0.6885 0.00779 0.00182 -0.0993 0.4503 0.4918
2.000 0.7157 0.00769 0.00190 -0.0993 0.4463 0.5649
2.250 0.7426 0.00762 0.00197 -0.0991 0.4422 0.6257
2.500 0.7688 0.00756 0.00207 -0.0988 0.4386 0.6893
2.750 0.7960 0.00753 0.00215 -0.0987 0.4354 0.7283
3.000 0.8232 0.00754 0.00222 -0.0985 0.4312 0.7554
3.250 0.8496 0.00754 0.00231 -0.0982 0.4265 0.7920
3.500 0.8744 0.00751 0.00240 -0.0976 0.4219 0.8405
3.750 0.9058 0.00734 0.00249 -0.0982 0.4179 0.9567
4.000 0.9408 0.00743 0.00257 -0.0998 0.4128 1.0000
4.250 0.9675 0.00757 0.00267 -0.0996 0.4075 1.0000
4.500 0.9947 0.00767 0.00276 -0.0996 0.4025 1.0000
4.750 1.0212 0.00780 0.00287 -0.0994 0.3951 1.0000
5.000 1.0477 0.00795 0.00298 -0.0992 0.3882 1.0000
5.250 1.0741 0.00809 0.00311 -0.0990 0.3814 1.0000
5.500 1.1002 0.00825 0.00325 -0.0987 0.3757 1.0000
5.750 1.1266 0.00839 0.00338 -0.0985 0.3691 1.0000
6.000 1.1518 0.00860 0.00355 -0.0982 0.3601 1.0000
6.250 1.1764 0.00884 0.00374 -0.0977 0.3475 1.0000
6.500 1.2014 0.00906 0.00392 -0.0973 0.3371 1.0000
6.750 1.2260 0.00928 0.00412 -0.0969 0.3291 1.0000
7.000 1.2493 0.00959 0.00436 -0.0962 0.3151 1.0000
7.500 1.2954 0.01021 0.00487 -0.0948 0.2878 1.0000
7.750 1.3164 0.01062 0.00519 -0.0938 0.2702 1.0000
8.000 1.3365 0.01106 0.00554 -0.0927 0.2497 1.0000
8.250 1.3511 0.01179 0.00607 -0.0907 0.2150 1.0000
8.500 1.3580 0.01286 0.00685 -0.0875 0.1681 1.0000
8.750 1.3583 0.01401 0.00774 -0.0832 0.1246 1.0000
9.000 1.3651 0.01474 0.00838 -0.0798 0.1057 1.0000
9.250 1.3715 0.01552 0.00907 -0.0765 0.0884 1.0000
9.500 1.3739 0.01653 0.00995 -0.0729 0.0654 1.0000
9.750 1.3785 0.01751 0.01085 -0.0698 0.0498 1.0000
10.000 1.3844 0.01849 0.01179 -0.0671 0.0390 1.0000
10.250 1.3883 0.01964 0.01289 -0.0644 0.0274 1.0000
10.500 1.3942 0.02078 0.01402 -0.0621 0.0205 1.0000
10.750 1.4027 0.02183 0.01509 -0.0603 0.0178 1.0000
11.000 1.4111 0.02296 0.01624 -0.0586 0.0161 1.0000
11.250 1.4196 0.02415 0.01747 -0.0571 0.0149 1.0000
11.500 1.4287 0.02536 0.01872 -0.0558 0.0141 1.0000
11.750 1.4370 0.02670 0.02011 -0.0545 0.0134 1.0000
12.000 1.4441 0.02820 0.02165 -0.0534 0.0128 1.0000
12.250 1.4497 0.02990 0.02340 -0.0523 0.0122 1.0000
12.500 1.4559 0.03161 0.02516 -0.0513 0.0118 1.0000
12.750 1.4626 0.03333 0.02694 -0.0505 0.0115 1.0000
13.000 1.4681 0.03520 0.02887 -0.0498 0.0112 1.0000
13.250 1.4729 0.03719 0.03092 -0.0491 0.0108 1.0000
13.500 1.4770 0.03930 0.03309 -0.0485 0.0106 1.0000
13.750 1.4799 0.04159 0.03544 -0.0480 0.0102 1.0000
14.000 1.4822 0.04401 0.03792 -0.0475 0.0099 1.0000
14.250 1.4826 0.04670 0.04066 -0.0472 0.0095 1.0000
14.500 1.4827 0.04949 0.04353 -0.0470 0.0093 1.0000
14.750 1.4839 0.05225 0.04635 -0.0469 0.0091 1.0000
15.000 1.4863 0.05490 0.04907 -0.0469 0.0090 1.0000
15.250 1.4874 0.05775 0.05199 -0.0469 0.0088 1.0000
15.500 1.4882 0.06070 0.05502 -0.0471 0.0086 1.0000
15.750 1.4888 0.06372 0.05810 -0.0473 0.0085 1.0000
16.000 1.4886 0.06690 0.06135 -0.0476 0.0083 1.0000
16.250 1.4887 0.07006 0.06458 -0.0480 0.0081 1.0000
16.500 1.4881 0.07336 0.06795 -0.0485 0.0080 1.0000
16.750 1.4867 0.07686 0.07153 -0.0491 0.0078 1.0000
17.000 1.4863 0.08025 0.07498 -0.0497 0.0077 1.0000
17.250 1.4848 0.08383 0.07863 -0.0505 0.0075 1.0000
17.500 1.4821 0.08765 0.08252 -0.0514 0.0074 1.0000
17.750 1.4794 0.09154 0.08648 -0.0524 0.0072 1.0000
18.000 1.4758 0.09564 0.09065 -0.0535 0.0071 1.0000
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