GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 500,000 Max Cl/Cd: 97.45 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe393-il-500000-n5.txt Download as CSV file: xf-goe393-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5166 0.11165 0.10946 0.0217 1.0000 0.0099
-9.250 -0.5161 0.10663 0.10445 0.0194 1.0000 0.0102
-9.000 -0.5164 0.10155 0.09939 0.0169 1.0000 0.0106
-8.750 -0.5082 0.09898 0.09684 0.0155 1.0000 0.0108
-8.500 -0.4996 0.09650 0.09437 0.0141 1.0000 0.0111
-8.250 -0.4914 0.09385 0.09173 0.0125 1.0000 0.0115
-8.000 -0.4848 0.09065 0.08856 0.0104 1.0000 0.0120
-7.750 -0.4786 0.08652 0.08445 0.0068 1.0000 0.0126
-7.500 -0.4707 0.08029 0.07821 0.0002 1.0000 0.0134
-7.250 -0.4593 0.07297 0.07088 -0.0081 1.0000 0.0142
-7.000 -0.4404 0.07058 0.06848 -0.0111 1.0000 0.0146
-6.500 -0.3915 0.06372 0.06149 -0.0207 0.9211 0.0163
-6.250 -0.3698 0.05139 0.04869 -0.0330 0.8265 0.0188
-6.000 -0.3485 0.05018 0.04718 -0.0338 0.7672 0.0192
-5.750 -0.3246 0.04874 0.04555 -0.0352 0.7347 0.0198
-5.500 -0.2990 0.04627 0.04290 -0.0375 0.7122 0.0206
-5.250 -0.2702 0.04157 0.03795 -0.0415 0.6955 0.0219
-5.000 -0.2371 0.01812 0.01281 -0.0528 0.6926 0.0261
-4.750 -0.2106 0.01719 0.01165 -0.0527 0.6748 0.0268
-4.500 -0.1839 0.01608 0.01025 -0.0527 0.6569 0.0274
-4.250 -0.1569 0.01508 0.00895 -0.0526 0.6404 0.0278
-4.000 -0.1297 0.01423 0.00785 -0.0525 0.6275 0.0282
-3.750 -0.1023 0.01350 0.00691 -0.0524 0.6173 0.0286
-3.500 -0.0747 0.01289 0.00612 -0.0522 0.6074 0.0291
-3.250 -0.0470 0.01242 0.00549 -0.0520 0.5982 0.0298
-3.000 -0.0193 0.01196 0.00487 -0.0519 0.5890 0.0304
-2.750 0.0084 0.01151 0.00430 -0.0517 0.5809 0.0308
-2.500 0.0362 0.01115 0.00382 -0.0515 0.5729 0.0313
-2.250 0.0640 0.01084 0.00342 -0.0513 0.5649 0.0318
-1.750 0.1197 0.01036 0.00278 -0.0509 0.5489 0.0327
-1.250 0.1755 0.01001 0.00231 -0.0505 0.5347 0.0333
-1.000 0.2034 0.00985 0.00209 -0.0504 0.5275 0.0338
-0.750 0.2314 0.00969 0.00189 -0.0502 0.5202 0.0346
-0.500 0.2593 0.00958 0.00173 -0.0500 0.5124 0.0360
-0.250 0.2872 0.00948 0.00160 -0.0498 0.5048 0.0381
0.000 0.3151 0.00940 0.00150 -0.0497 0.4973 0.0406
0.250 0.3431 0.00932 0.00143 -0.0495 0.4901 0.0449
0.500 0.3709 0.00925 0.00145 -0.0494 0.4824 0.0687
0.750 0.3990 0.00927 0.00147 -0.0493 0.4749 0.0792
1.000 0.4269 0.00930 0.00150 -0.0491 0.4668 0.0850
1.250 0.4549 0.00932 0.00151 -0.0490 0.4583 0.0892
1.500 0.4827 0.00937 0.00153 -0.0489 0.4495 0.0919
1.750 0.5106 0.00938 0.00155 -0.0488 0.4386 0.0968
2.000 0.5384 0.00942 0.00158 -0.0486 0.4264 0.1000
2.250 0.5661 0.00947 0.00161 -0.0485 0.4152 0.1039
2.500 0.5939 0.00953 0.00166 -0.0484 0.4060 0.1090
2.750 0.6216 0.00957 0.00173 -0.0483 0.3955 0.1148
3.000 0.6492 0.00966 0.00179 -0.0482 0.3823 0.1185
3.250 0.6766 0.00976 0.00186 -0.0481 0.3668 0.1233
3.500 0.7041 0.00986 0.00197 -0.0479 0.3549 0.1311
3.750 0.7316 0.00995 0.00208 -0.0478 0.3444 0.1463
4.000 0.7567 0.00908 0.00232 -0.0478 0.3351 0.6830
4.500 0.8133 0.00872 0.00258 -0.0477 0.3195 1.0000
4.750 0.8406 0.00888 0.00273 -0.0475 0.3115 1.0000
5.000 0.8677 0.00908 0.00291 -0.0474 0.3013 1.0000
5.250 0.8949 0.00926 0.00309 -0.0472 0.2905 1.0000
5.500 0.9219 0.00946 0.00328 -0.0471 0.2780 1.0000
5.750 0.9484 0.00976 0.00351 -0.0469 0.2544 1.0000
6.000 0.9732 0.01043 0.00388 -0.0467 0.1910 1.0000
6.250 0.9971 0.01126 0.00444 -0.0464 0.1425 1.0000
6.500 1.0220 0.01187 0.00491 -0.0462 0.1148 1.0000
6.750 1.0474 0.01234 0.00533 -0.0459 0.0987 1.0000
7.000 1.0729 0.01277 0.00572 -0.0457 0.0883 1.0000
7.250 1.0983 0.01319 0.00613 -0.0454 0.0798 1.0000
7.500 1.1239 0.01356 0.00652 -0.0452 0.0717 1.0000
7.750 1.1489 0.01402 0.00697 -0.0449 0.0604 1.0000
8.000 1.1721 0.01476 0.00756 -0.0445 0.0384 1.0000
8.250 1.1951 0.01552 0.00826 -0.0441 0.0264 1.0000
8.500 1.2186 0.01617 0.00891 -0.0436 0.0201 1.0000
8.750 1.2420 0.01678 0.00956 -0.0432 0.0169 1.0000
9.000 1.2647 0.01748 0.01031 -0.0427 0.0144 1.0000
9.250 1.2873 0.01816 0.01106 -0.0421 0.0129 1.0000
9.500 1.3098 0.01882 0.01179 -0.0416 0.0117 1.0000
9.750 1.3313 0.01957 0.01261 -0.0410 0.0108 1.0000
10.000 1.3513 0.02050 0.01361 -0.0403 0.0099 1.0000
10.250 1.3704 0.02149 0.01469 -0.0395 0.0094 1.0000
10.500 1.3899 0.02234 0.01567 -0.0387 0.0089 1.0000
10.750 1.4084 0.02326 0.01669 -0.0379 0.0084 1.0000
11.000 1.4260 0.02422 0.01774 -0.0370 0.0079 1.0000
11.250 1.4423 0.02524 0.01884 -0.0361 0.0075 1.0000
11.500 1.4559 0.02647 0.02015 -0.0350 0.0071 1.0000
11.750 1.4641 0.02811 0.02190 -0.0335 0.0068 1.0000
12.000 1.4694 0.02967 0.02358 -0.0316 0.0067 1.0000
12.250 1.4737 0.03135 0.02541 -0.0302 0.0065 1.0000
12.500 1.4763 0.03349 0.02769 -0.0296 0.0064 1.0000
12.750 1.4783 0.03612 0.03046 -0.0299 0.0062 1.0000
13.000 1.4793 0.03918 0.03366 -0.0307 0.0061 1.0000
13.250 1.4790 0.04252 0.03714 -0.0318 0.0060 1.0000
13.500 1.4773 0.04609 0.04084 -0.0329 0.0059 1.0000
13.750 1.4738 0.04989 0.04477 -0.0340 0.0058 1.0000
14.000 1.4686 0.05393 0.04894 -0.0352 0.0057 1.0000
14.250 1.4621 0.05816 0.05329 -0.0364 0.0056 1.0000
14.500 1.4543 0.06260 0.05786 -0.0377 0.0055 1.0000
14.750 1.4453 0.06726 0.06264 -0.0392 0.0055 1.0000
15.000 1.4357 0.07209 0.06759 -0.0407 0.0054 1.0000
15.250 1.4249 0.07714 0.07276 -0.0424 0.0054 1.0000
15.500 1.4143 0.08240 0.07814 -0.0443 0.0053 1.0000
15.750 1.4037 0.08786 0.08371 -0.0464 0.0053 1.0000
16.000 1.3929 0.09352 0.08949 -0.0487 0.0052 1.0000
16.250 1.3817 0.09939 0.09548 -0.0511 0.0052 1.0000
16.500 1.3703 0.10535 0.10155 -0.0536 0.0051 1.0000
16.750 1.3583 0.11158 0.10790 -0.0563 0.0051 1.0000
17.000 1.3463 0.11795 0.11437 -0.0592 0.0051 1.0000
17.250 1.3339 0.12448 0.12102 -0.0622 0.0050 1.0000
17.500 1.3216 0.13116 0.12781 -0.0654 0.0050 1.0000
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