GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 590 AIRFOIL (goe590-il) Reynolds number: 200,000 Max Cl/Cd: 70.1 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe590-il-200000-n5.txt Download as CSV file: xf-goe590-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3911 0.09790 0.09455 -0.0134 1.0000 0.0170
-7.750 -0.3887 0.09545 0.09216 -0.0152 1.0000 0.0171
-7.500 -0.3871 0.09293 0.08968 -0.0169 1.0000 0.0172
-7.250 -0.3810 0.08998 0.08677 -0.0197 1.0000 0.0173
-7.000 -0.3725 0.08685 0.08365 -0.0222 1.0000 0.0173
-6.750 -0.3626 0.08357 0.08038 -0.0244 1.0000 0.0174
-6.500 -0.3516 0.08018 0.07699 -0.0265 1.0000 0.0174
-6.250 -0.3398 0.07675 0.07356 -0.0283 1.0000 0.0175
-6.000 -0.3276 0.07339 0.07020 -0.0298 1.0000 0.0175
-5.750 -0.3150 0.06992 0.06668 -0.0310 1.0000 0.0175
-5.500 -0.2931 0.06568 0.06239 -0.0343 0.9904 0.0175
-5.250 -0.2606 0.06107 0.05766 -0.0396 0.9653 0.0176
-4.750 -0.2049 0.05028 0.04663 -0.0482 0.9125 0.0165
-4.500 -0.1776 0.04589 0.04205 -0.0512 0.8848 0.0146
-4.250 -0.1502 0.04202 0.03792 -0.0531 0.8564 0.0135
-4.000 -0.1244 0.03832 0.03394 -0.0539 0.8296 0.0129
-3.750 -0.0996 0.03478 0.03006 -0.0540 0.8053 0.0125
-3.500 -0.0751 0.03134 0.02627 -0.0537 0.7847 0.0124
-3.250 -0.0504 0.02803 0.02253 -0.0529 0.7668 0.0127
-3.000 -0.0254 0.02493 0.01900 -0.0519 0.7510 0.0144
-2.750 -0.0001 0.02098 0.01444 -0.0505 0.7372 0.0156
-2.500 0.0256 0.01739 0.01007 -0.0490 0.7240 0.0168
-2.250 0.0511 0.01591 0.00819 -0.0483 0.7101 0.0196
-2.000 0.0773 0.01505 0.00700 -0.0476 0.6964 0.0245
-1.750 0.1035 0.01415 0.00578 -0.0470 0.6831 0.0304
-1.500 0.1294 0.01364 0.00506 -0.0466 0.6694 0.0363
-1.250 0.1549 0.01304 0.00432 -0.0460 0.6556 0.0420
-1.000 0.1803 0.01262 0.00377 -0.0455 0.6421 0.0455
-0.750 0.2057 0.01231 0.00331 -0.0449 0.6294 0.0481
-0.500 0.2309 0.01204 0.00294 -0.0444 0.6173 0.0524
-0.250 0.2561 0.01182 0.00262 -0.0439 0.6057 0.0543
0.000 0.2816 0.01166 0.00237 -0.0434 0.5945 0.0568
0.250 0.3073 0.01155 0.00215 -0.0429 0.5847 0.0616
0.500 0.3327 0.01144 0.00201 -0.0424 0.5764 0.0783
0.750 0.3578 0.01129 0.00197 -0.0420 0.5683 0.1291
1.000 0.3820 0.01108 0.00195 -0.0414 0.5613 0.2258
1.500 0.4946 0.00959 0.00205 -0.0542 0.5455 1.0000
1.750 0.5194 0.00971 0.00212 -0.0536 0.5397 1.0000
2.000 0.5442 0.00986 0.00219 -0.0530 0.5347 1.0000
2.250 0.5692 0.00998 0.00231 -0.0525 0.5292 1.0000
2.500 0.5940 0.01012 0.00243 -0.0520 0.5239 1.0000
2.750 0.6189 0.01029 0.00260 -0.0515 0.5196 1.0000
3.000 0.6440 0.01043 0.00279 -0.0510 0.5148 1.0000
3.250 0.6690 0.01058 0.00300 -0.0505 0.5102 1.0000
3.500 0.6937 0.01076 0.00320 -0.0500 0.5038 1.0000
3.750 0.7182 0.01090 0.00344 -0.0493 0.4941 1.0000
4.000 0.7427 0.01104 0.00367 -0.0487 0.4838 1.0000
4.250 0.7670 0.01120 0.00391 -0.0480 0.4739 1.0000
4.500 0.7899 0.01131 0.00406 -0.0470 0.4486 1.0000
4.750 0.8097 0.01155 0.00414 -0.0455 0.3665 1.0000
5.000 0.8095 0.01461 0.00554 -0.0421 0.0463 1.0000
5.250 0.8282 0.01555 0.00648 -0.0405 0.0232 1.0000
5.500 0.8465 0.01651 0.00759 -0.0389 0.0176 1.0000
5.750 0.8656 0.01731 0.00856 -0.0375 0.0138 1.0000
6.000 0.8819 0.01841 0.00981 -0.0356 0.0123 1.0000
6.250 0.8959 0.01977 0.01132 -0.0334 0.0112 1.0000
6.500 0.9046 0.02196 0.01359 -0.0305 0.0096 1.0000
6.750 0.9232 0.02302 0.01479 -0.0290 0.0087 1.0000
7.000 0.9408 0.02474 0.01663 -0.0273 0.0083 1.0000
7.250 0.9606 0.02687 0.01894 -0.0257 0.0079 1.0000
7.500 0.9815 0.02924 0.02154 -0.0243 0.0077 1.0000
7.750 1.0016 0.03200 0.02461 -0.0228 0.0076 1.0000
8.000 1.0193 0.03518 0.02815 -0.0211 0.0077 1.0000
8.250 1.0338 0.03846 0.03179 -0.0191 0.0077 1.0000
8.500 1.0449 0.03918 0.03262 -0.0181 0.0062 1.0000
9.000 1.0547 0.04626 0.04041 -0.0135 0.0056 1.0000
9.250 1.0555 0.04975 0.04418 -0.0113 0.0057 1.0000
9.500 1.0527 0.05325 0.04797 -0.0089 0.0057 1.0000
9.750 1.0450 0.05666 0.05163 -0.0061 0.0057 1.0000
10.000 1.0357 0.05954 0.05469 -0.0036 0.0058 1.0000
10.250 1.0266 0.06233 0.05767 -0.0017 0.0059 1.0000
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Polar data table (+)
Polar graphs
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