GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 500,000 Max Cl/Cd: 94.65 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe590-il-500000.txt Download as CSV file: xf-goe590-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 590 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3390 0.08421 0.08219 -0.0121 1.0000 0.0116
-8.000 -0.3363 0.08078 0.07878 -0.0130 1.0000 0.0118
-7.750 -0.3343 0.07738 0.07539 -0.0139 1.0000 0.0120
-7.500 -0.3329 0.07403 0.07207 -0.0148 1.0000 0.0123
-7.250 -0.3328 0.07079 0.06885 -0.0157 1.0000 0.0125
-7.000 -0.3349 0.06769 0.06579 -0.0165 1.0000 0.0127
-6.750 -0.3360 0.06444 0.06256 -0.0177 1.0000 0.0129
-6.500 -0.3322 0.06077 0.05890 -0.0197 1.0000 0.0133
-6.250 -0.3265 0.05703 0.05517 -0.0216 1.0000 0.0138
-6.000 -0.3188 0.05331 0.05144 -0.0234 1.0000 0.0143
-5.750 -0.3022 0.04956 0.04765 -0.0271 0.9965 0.0154
-5.500 -0.3339 0.06081 0.05868 -0.0268 1.0000 0.0147
-5.250 -0.3048 0.05794 0.05571 -0.0302 0.9981 0.0158
-5.000 -0.2657 0.05370 0.05133 -0.0358 0.9832 0.0160
-4.750 -0.2255 0.04885 0.04632 -0.0414 0.9621 0.0161
-4.250 -0.1632 0.03748 0.03450 -0.0496 0.8967 0.0178
-4.000 -0.1429 0.03573 0.03254 -0.0493 0.8578 0.0196
-3.750 -0.1128 0.03485 0.03136 -0.0486 0.8235 0.0248
-3.500 -0.0891 0.03265 0.02887 -0.0477 0.7950 0.0251
-3.250 -0.0667 0.02994 0.02584 -0.0467 0.7725 0.0252
-3.000 -0.0444 0.02711 0.02270 -0.0457 0.7540 0.0253
-2.750 -0.0277 0.02182 0.01696 -0.0444 0.7392 0.0230
-2.500 -0.0051 0.01709 0.01159 -0.0422 0.7259 0.0206
-2.250 0.0199 0.01520 0.00929 -0.0410 0.7108 0.0226
-2.000 0.0461 0.01445 0.00825 -0.0403 0.6951 0.0248
-1.750 0.0709 0.01212 0.00546 -0.0393 0.6805 0.0278
-1.500 0.0968 0.01148 0.00469 -0.0388 0.6641 0.0308
-1.250 0.1230 0.01119 0.00428 -0.0384 0.6470 0.0355
-1.000 0.1492 0.01083 0.00374 -0.0379 0.6301 0.0374
-0.750 0.1740 0.01006 0.00282 -0.0372 0.6147 0.0395
-0.500 0.1988 0.00963 0.00232 -0.0366 0.6007 0.0436
-0.250 0.2242 0.00941 0.00202 -0.0360 0.5888 0.0464
0.000 0.2499 0.00926 0.00179 -0.0356 0.5785 0.0484
0.250 0.2757 0.00916 0.00160 -0.0351 0.5695 0.0499
0.500 0.3016 0.00905 0.00144 -0.0347 0.5610 0.0531
0.750 0.3277 0.00897 0.00135 -0.0344 0.5537 0.0609
1.000 0.3527 0.00873 0.00135 -0.0338 0.5471 0.1540
1.250 0.4156 0.00687 0.00158 -0.0420 0.5399 0.9844
1.500 0.4827 0.00700 0.00159 -0.0510 0.5323 1.0000
1.750 0.5074 0.00708 0.00163 -0.0504 0.5271 1.0000
2.000 0.5323 0.00716 0.00168 -0.0498 0.5220 1.0000
2.250 0.5568 0.00728 0.00176 -0.0492 0.5168 1.0000
2.500 0.5815 0.00733 0.00181 -0.0486 0.5076 1.0000
2.750 0.6061 0.00745 0.00189 -0.0480 0.5010 1.0000
3.000 0.6311 0.00752 0.00199 -0.0475 0.4952 1.0000
3.250 0.6556 0.00765 0.00209 -0.0468 0.4890 1.0000
3.500 0.6803 0.00768 0.00220 -0.0462 0.4779 1.0000
3.750 0.7045 0.00775 0.00225 -0.0455 0.4623 1.0000
4.000 0.7289 0.00780 0.00231 -0.0448 0.4408 1.0000
4.250 0.7525 0.00795 0.00239 -0.0440 0.4057 1.0000
4.500 0.7571 0.01059 0.00346 -0.0410 0.0647 1.0000
4.750 0.7774 0.01133 0.00412 -0.0396 0.0319 1.0000
5.000 0.7965 0.01224 0.00518 -0.0380 0.0242 1.0000
5.250 0.8184 0.01271 0.00571 -0.0369 0.0212 1.0000
5.500 0.8393 0.01328 0.00632 -0.0357 0.0180 1.0000
5.750 0.8561 0.01432 0.00745 -0.0338 0.0162 1.0000
6.000 0.8642 0.01652 0.00980 -0.0304 0.0149 1.0000
6.250 0.8841 0.01731 0.01067 -0.0289 0.0142 1.0000
6.500 0.9017 0.01879 0.01221 -0.0270 0.0140 1.0000
6.750 0.9219 0.01998 0.01352 -0.0255 0.0133 1.0000
7.000 0.9427 0.02092 0.01456 -0.0243 0.0119 1.0000
7.250 0.9635 0.02308 0.01687 -0.0228 0.0118 1.0000
7.500 0.9844 0.02588 0.01991 -0.0212 0.0117 1.0000
8.500 1.0244 0.04686 0.04217 -0.0124 0.0149 1.0000
8.750 1.0302 0.05008 0.04565 -0.0102 0.0149 1.0000
9.000 1.0333 0.05331 0.04914 -0.0080 0.0148 1.0000
9.250 1.0337 0.05650 0.05256 -0.0057 0.0148 1.0000
9.500 1.0309 0.05953 0.05582 -0.0034 0.0148 1.0000
9.750 1.0253 0.06250 0.05899 -0.0011 0.0147 1.0000
10.000 1.0158 0.06526 0.06196 0.0013 0.0147 1.0000
10.250 1.0003 0.06765 0.06448 0.0043 0.0147 1.0000
10.500 0.9840 0.07046 0.06743 0.0057 0.0146 1.0000
10.750 0.9675 0.07384 0.07094 0.0056 0.0146 1.0000
11.000 0.9503 0.07819 0.07540 0.0042 0.0146 1.0000
11.250 0.9329 0.08324 0.08052 0.0019 0.0146 1.0000
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Polar data table (+)
Polar graphs
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