GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 50,000 Max Cl/Cd: 24.34 at α=12° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe593-il-50000.txt Download as CSV file: xf-goe593-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3450 0.12268 0.11556 -0.0332 1.0000 0.2076
-9.750 -0.3242 0.11726 0.11013 -0.0316 1.0000 0.2142
-9.500 -0.3343 0.11606 0.10903 -0.0313 1.0000 0.2227
-9.250 -0.3289 0.11246 0.10550 -0.0302 1.0000 0.2286
-9.000 -0.3335 0.11072 0.10384 -0.0291 1.0000 0.2384
-8.750 -0.3368 0.10797 0.10119 -0.0281 1.0000 0.2440
-8.500 -0.3353 0.10561 0.09889 -0.0264 1.0000 0.2537
-8.250 -0.3773 0.10690 0.10043 -0.0247 1.0000 0.2572
-8.000 -0.3436 0.10114 0.09461 -0.0228 1.0000 0.2695
-7.750 -0.3887 0.10237 0.09608 -0.0200 1.0000 0.2736
-7.500 -0.3638 0.09765 0.09135 -0.0180 1.0000 0.2874
-7.250 -0.3643 0.09504 0.08882 -0.0154 1.0000 0.2975
-7.000 -0.3971 0.09508 0.08904 -0.0115 1.0000 0.3052
-6.750 -0.3906 0.09211 0.08611 -0.0088 1.0000 0.3186
-6.500 -0.4379 0.09266 0.08687 -0.0049 1.0000 0.3228
-6.250 -0.4354 0.09005 0.08432 -0.0015 1.0000 0.3384
-6.000 -0.4381 0.08777 0.08211 0.0018 1.0000 0.3541
-5.750 -0.4449 0.08573 0.08015 0.0052 1.0000 0.3704
-5.500 -0.4562 0.08398 0.07849 0.0085 1.0000 0.3876
-5.250 -0.4701 0.08221 0.07682 0.0119 1.0000 0.4070
-5.000 -0.4547 0.07941 0.07403 0.0163 1.0000 0.4307
-4.000 -0.4240 0.05181 0.04455 -0.0244 1.0000 0.1890
-3.750 -0.4020 0.04741 0.03942 -0.0259 1.0000 0.1741
-3.500 -0.3841 0.04466 0.03642 -0.0255 1.0000 0.1702
-3.250 -0.3647 0.04218 0.03351 -0.0253 1.0000 0.1689
-3.000 -0.3452 0.04024 0.03114 -0.0248 1.0000 0.1707
-2.750 -0.3249 0.03848 0.02892 -0.0242 1.0000 0.1724
-2.500 -0.3042 0.03696 0.02692 -0.0234 1.0000 0.1743
-2.250 -0.2851 0.03571 0.02554 -0.0226 1.0000 0.1799
-2.000 -0.2656 0.03485 0.02447 -0.0218 1.0000 0.1881
-1.750 -0.2452 0.03391 0.02332 -0.0210 1.0000 0.1962
-1.500 -0.2244 0.03329 0.02251 -0.0204 1.0000 0.2095
-1.250 -0.2040 0.03271 0.02191 -0.0197 1.0000 0.2267
-1.000 -0.1837 0.03226 0.02151 -0.0190 1.0000 0.2530
-0.750 -0.1547 0.03184 0.02122 -0.0198 0.9986 0.3015
-0.500 -0.0645 0.02948 0.02157 -0.0301 0.9858 1.0000
-0.250 -0.0133 0.03090 0.02222 -0.0353 0.9708 1.0000
0.000 0.0285 0.03196 0.02286 -0.0390 0.9554 1.0000
0.250 0.0692 0.03297 0.02355 -0.0424 0.9397 1.0000
0.500 0.1091 0.03393 0.02423 -0.0455 0.9236 1.0000
0.750 0.1484 0.03482 0.02491 -0.0483 0.9072 1.0000
1.000 0.1868 0.03567 0.02556 -0.0509 0.8907 1.0000
1.250 0.2246 0.03646 0.02619 -0.0532 0.8741 1.0000
1.500 0.2622 0.03717 0.02677 -0.0553 0.8573 1.0000
1.750 0.3006 0.03780 0.02729 -0.0574 0.8402 1.0000
2.000 0.3386 0.03836 0.02776 -0.0592 0.8234 1.0000
2.250 0.3778 0.03880 0.02812 -0.0610 0.8066 1.0000
2.500 0.4167 0.03915 0.02841 -0.0626 0.7900 1.0000
2.750 0.4562 0.03936 0.02859 -0.0641 0.7735 1.0000
3.000 0.4769 0.03994 0.02914 -0.0631 0.7542 1.0000
3.250 0.5072 0.04028 0.02947 -0.0632 0.7365 1.0000
3.500 0.5402 0.04048 0.02967 -0.0634 0.7195 1.0000
3.750 0.5733 0.04062 0.02982 -0.0636 0.7031 1.0000
4.000 0.6066 0.04070 0.02991 -0.0637 0.6872 1.0000
4.250 0.6419 0.04060 0.02984 -0.0638 0.6722 1.0000
4.500 0.7131 0.03867 0.02799 -0.0676 0.6627 1.0000
4.750 0.7440 0.03873 0.02810 -0.0672 0.6473 1.0000
5.000 0.7703 0.03904 0.02845 -0.0664 0.6321 1.0000
5.250 0.7934 0.03955 0.02900 -0.0653 0.6171 1.0000
5.500 0.8128 0.04030 0.02981 -0.0638 0.6024 1.0000
5.750 0.8258 0.04150 0.03104 -0.0619 0.5885 1.0000
6.000 0.8445 0.04248 0.03207 -0.0606 0.5759 1.0000
6.250 0.9181 0.04035 0.03007 -0.0644 0.5672 1.0000
6.500 0.9039 0.04323 0.03299 -0.0601 0.5535 1.0000
6.750 0.8732 0.04737 0.03712 -0.0548 0.5408 1.0000
7.000 0.8856 0.04906 0.03887 -0.0534 0.5313 1.0000
7.250 0.9042 0.05028 0.04017 -0.0524 0.5216 1.0000
7.500 0.8248 0.06025 0.05003 -0.0486 0.5088 1.0000
7.750 0.9112 0.05544 0.04544 -0.0492 0.5041 1.0000
8.000 0.7958 0.06971 0.05952 -0.0472 0.4939 1.0000
8.250 0.8348 0.06958 0.05951 -0.0468 0.4870 1.0000
8.500 0.7832 0.07792 0.06779 -0.0467 0.4827 1.0000
8.750 0.7713 0.08263 0.07253 -0.0468 0.4790 1.0000
9.000 0.8049 0.08341 0.07345 -0.0464 0.4714 1.0000
9.250 0.7816 0.08931 0.07935 -0.0469 0.4701 1.0000
9.500 0.7693 0.09430 0.08438 -0.0475 0.4696 1.0000
9.750 0.7623 0.09893 0.08907 -0.0482 0.4697 1.0000
10.000 0.7644 0.10330 0.09352 -0.0491 0.4712 1.0000
10.750 1.2072 0.05767 0.04933 -0.0334 0.3618 1.0000
11.000 1.2708 0.05390 0.04569 -0.0336 0.3320 1.0000
11.250 1.2010 0.06080 0.05268 -0.0268 0.3324 1.0000
11.500 1.1300 0.07043 0.06230 -0.0243 0.3307 1.0000
11.750 1.1283 0.07228 0.06424 -0.0221 0.3142 1.0000
12.000 1.3220 0.05431 0.04587 -0.0214 0.2367 1.0000
12.250 1.2851 0.05836 0.05020 -0.0163 0.2321 1.0000
12.500 0.8819 0.12113 0.11251 -0.0387 0.3013 1.0000
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Polar data table (+)
Polar graphs
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