GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 596 AIRFOIL (goe596-il) Reynolds number: 500,000 Max Cl/Cd: 97.22 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe596-il-500000-n5.txt Download as CSV file: xf-goe596-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 596 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3637 0.08827 0.08592 -0.0359 1.0000 0.0171
-9.000 -0.3642 0.08539 0.08306 -0.0364 1.0000 0.0173
-8.750 -0.3671 0.08257 0.08028 -0.0366 1.0000 0.0176
-8.500 -0.3582 0.07796 0.07568 -0.0415 0.9900 0.0181
-8.250 -0.3513 0.07210 0.06982 -0.0489 0.9762 0.0187
-8.000 -0.3415 0.05790 0.05550 -0.0699 0.9595 0.0201
-7.750 -0.3160 0.05403 0.05155 -0.0761 0.9493 0.0204
-7.500 -0.2919 0.04945 0.04685 -0.0823 0.9368 0.0208
-7.250 -0.2717 0.04432 0.04154 -0.0872 0.9218 0.0213
-7.000 -0.2561 0.03907 0.03602 -0.0902 0.9059 0.0221
-6.750 -0.2668 0.02474 0.02050 -0.0908 0.8872 0.0240
-6.500 -0.2504 0.02181 0.01712 -0.0900 0.8753 0.0247
-6.250 -0.2275 0.02086 0.01600 -0.0896 0.8642 0.0250
-6.000 -0.2042 0.01997 0.01494 -0.0891 0.8536 0.0253
-5.750 -0.1813 0.01884 0.01360 -0.0884 0.8430 0.0256
-5.500 -0.1578 0.01775 0.01230 -0.0878 0.8329 0.0259
-5.250 -0.1337 0.01685 0.01118 -0.0872 0.8220 0.0263
-5.000 -0.1094 0.01594 0.01008 -0.0866 0.8101 0.0267
-4.750 -0.0847 0.01513 0.00907 -0.0860 0.7980 0.0270
-4.500 -0.0595 0.01450 0.00827 -0.0854 0.7852 0.0276
-4.250 -0.0342 0.01391 0.00750 -0.0848 0.7717 0.0282
-4.000 -0.0089 0.01331 0.00674 -0.0842 0.7562 0.0286
-3.750 0.0165 0.01281 0.00608 -0.0836 0.7377 0.0289
-3.500 0.0417 0.01241 0.00552 -0.0829 0.7160 0.0292
-3.250 0.0668 0.01210 0.00506 -0.0823 0.6938 0.0295
-3.000 0.0919 0.01183 0.00464 -0.0816 0.6726 0.0297
-2.750 0.1164 0.01142 0.00409 -0.0809 0.6525 0.0300
-2.500 0.1409 0.01108 0.00363 -0.0801 0.6336 0.0306
-2.250 0.1661 0.01086 0.00332 -0.0795 0.6168 0.0311
-2.000 0.1917 0.01072 0.00311 -0.0790 0.6030 0.0317
-1.750 0.2180 0.01057 0.00292 -0.0786 0.5929 0.0326
-1.500 0.2441 0.01043 0.00274 -0.0782 0.5846 0.0333
-1.250 0.2706 0.01027 0.00254 -0.0779 0.5770 0.0340
-1.000 0.2969 0.01015 0.00238 -0.0774 0.5697 0.0347
-0.750 0.3236 0.01003 0.00224 -0.0771 0.5626 0.0355
-0.500 0.3502 0.00996 0.00212 -0.0768 0.5559 0.0362
-0.250 0.3770 0.00987 0.00201 -0.0765 0.5502 0.0369
0.000 0.4037 0.00976 0.00189 -0.0761 0.5439 0.0387
0.250 0.4302 0.00973 0.00183 -0.0758 0.5378 0.0409
0.500 0.4573 0.00968 0.00179 -0.0756 0.5316 0.0440
0.750 0.4840 0.00965 0.00176 -0.0752 0.5255 0.0493
1.000 0.5106 0.00960 0.00175 -0.0749 0.5203 0.0652
1.250 0.5356 0.00919 0.00179 -0.0745 0.5146 0.2315
1.500 0.5572 0.00851 0.00188 -0.0737 0.5087 0.5178
2.000 0.6527 0.00763 0.00209 -0.0822 0.4909 1.0000
2.250 0.6779 0.00771 0.00213 -0.0816 0.4839 1.0000
2.500 0.7025 0.00782 0.00219 -0.0808 0.4756 1.0000
2.750 0.7273 0.00792 0.00226 -0.0801 0.4654 1.0000
3.000 0.7519 0.00804 0.00233 -0.0794 0.4563 1.0000
3.250 0.7766 0.00816 0.00241 -0.0787 0.4460 1.0000
3.500 0.8008 0.00831 0.00251 -0.0780 0.4315 1.0000
3.750 0.8244 0.00851 0.00261 -0.0771 0.4117 1.0000
4.000 0.8478 0.00872 0.00273 -0.0762 0.3908 1.0000
4.250 0.8711 0.00896 0.00288 -0.0753 0.3714 1.0000
4.500 0.8940 0.00924 0.00306 -0.0744 0.3516 1.0000
4.750 0.9175 0.00949 0.00324 -0.0736 0.3372 1.0000
5.000 0.9411 0.00974 0.00344 -0.0728 0.3235 1.0000
5.500 0.9874 0.01031 0.00388 -0.0711 0.2908 1.0000
5.750 1.0106 0.01060 0.00412 -0.0703 0.2742 1.0000
6.000 1.0333 0.01092 0.00438 -0.0694 0.2544 1.0000
6.250 1.0540 0.01140 0.00470 -0.0683 0.2216 1.0000
6.500 1.0720 0.01209 0.00515 -0.0667 0.1795 1.0000
6.750 1.0913 0.01267 0.00560 -0.0654 0.1539 1.0000
7.000 1.1100 0.01328 0.00608 -0.0640 0.1252 1.0000
7.250 1.1191 0.01460 0.00697 -0.0612 0.0581 1.0000
7.500 1.1382 0.01513 0.00747 -0.0598 0.0491 1.0000
7.750 1.1587 0.01553 0.00790 -0.0587 0.0456 1.0000
8.000 1.1782 0.01600 0.00838 -0.0573 0.0425 1.0000
8.250 1.1963 0.01652 0.00891 -0.0558 0.0395 1.0000
8.500 1.2159 0.01692 0.00937 -0.0546 0.0382 1.0000
8.750 1.2344 0.01737 0.00986 -0.0531 0.0366 1.0000
9.000 1.2513 0.01785 0.01038 -0.0515 0.0351 1.0000
9.250 1.2653 0.01840 0.01095 -0.0493 0.0336 1.0000
9.500 1.2768 0.01905 0.01164 -0.0468 0.0320 1.0000
9.750 1.2909 0.01957 0.01222 -0.0447 0.0311 1.0000
10.000 1.3051 0.02011 0.01283 -0.0428 0.0301 1.0000
10.250 1.3186 0.02070 0.01347 -0.0409 0.0289 1.0000
10.500 1.3310 0.02138 0.01420 -0.0389 0.0279 1.0000
10.750 1.3417 0.02217 0.01503 -0.0368 0.0267 1.0000
11.000 1.3494 0.02318 0.01607 -0.0345 0.0255 1.0000
11.250 1.3620 0.02393 0.01691 -0.0329 0.0247 1.0000
11.500 1.3731 0.02481 0.01787 -0.0313 0.0238 1.0000
11.750 1.3833 0.02579 0.01892 -0.0297 0.0228 1.0000
12.000 1.3934 0.02681 0.01999 -0.0282 0.0217 1.0000
12.250 1.4012 0.02807 0.02128 -0.0268 0.0207 1.0000
12.500 1.4086 0.02941 0.02270 -0.0254 0.0199 1.0000
12.750 1.4161 0.03082 0.02421 -0.0242 0.0191 1.0000
13.000 1.4235 0.03228 0.02575 -0.0231 0.0181 1.0000
13.250 1.4300 0.03390 0.02742 -0.0222 0.0173 1.0000
13.500 1.4349 0.03574 0.02932 -0.0214 0.0166 1.0000
13.750 1.4377 0.03787 0.03152 -0.0207 0.0160 1.0000
14.000 1.4417 0.03998 0.03373 -0.0202 0.0153 1.0000
14.250 1.4444 0.04231 0.03616 -0.0198 0.0148 1.0000
14.500 1.4455 0.04490 0.03885 -0.0196 0.0143 1.0000
14.750 1.4468 0.04753 0.04156 -0.0196 0.0138 1.0000
15.000 1.4472 0.05034 0.04444 -0.0197 0.0132 1.0000
15.250 1.4442 0.05365 0.04784 -0.0200 0.0129 1.0000
15.500 1.4414 0.05700 0.05128 -0.0204 0.0125 1.0000
15.750 1.4402 0.06024 0.05464 -0.0209 0.0121 1.0000
16.000 1.4369 0.06382 0.05833 -0.0216 0.0118 1.0000
16.250 1.4330 0.06754 0.06216 -0.0223 0.0116 1.0000
16.500 1.4290 0.07138 0.06610 -0.0233 0.0112 1.0000
16.750 1.4240 0.07546 0.07029 -0.0244 0.0110 1.0000
17.000 1.4188 0.07964 0.07457 -0.0256 0.0108 1.0000
17.250 1.4126 0.08409 0.07913 -0.0270 0.0106 1.0000
17.500 1.4067 0.08861 0.08374 -0.0286 0.0104 1.0000
17.750 1.3980 0.09366 0.08889 -0.0305 0.0102 1.0000
18.000 1.3898 0.09873 0.09406 -0.0324 0.0100 1.0000
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