GOE 676 (= M 12) AIRFOIL (goe676-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 676 (= M 12) AIRFOIL (goe676-il) Reynolds number: 50,000 Max Cl/Cd: 33.61 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe676-il-50000-n5.txt Download as CSV file: xf-goe676-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 676 (= M 12) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5248 0.09906 0.09167 -0.0267 1.0000 0.0797
-9.750 -0.5309 0.09347 0.08613 -0.0303 1.0000 0.0796
-9.500 -0.5396 0.08736 0.08005 -0.0347 1.0000 0.0792
-9.250 -0.5530 0.08156 0.07427 -0.0383 1.0000 0.0786
-9.000 -0.5691 0.07666 0.06937 -0.0395 1.0000 0.0780
-8.750 -0.5828 0.07188 0.06451 -0.0402 1.0000 0.0776
-8.500 -0.5942 0.06733 0.05982 -0.0401 1.0000 0.0772
-8.250 -0.6027 0.06305 0.05536 -0.0393 1.0000 0.0771
-8.000 -0.6082 0.05909 0.05115 -0.0379 1.0000 0.0773
-7.750 -0.6114 0.05547 0.04724 -0.0360 1.0000 0.0783
-7.500 -0.6129 0.05211 0.04350 -0.0337 1.0000 0.0798
-7.250 -0.6119 0.04897 0.03992 -0.0312 1.0000 0.0811
-7.000 -0.6074 0.04609 0.03658 -0.0287 1.0000 0.0819
-6.750 -0.5982 0.04354 0.03379 -0.0266 1.0000 0.0827
-6.500 -0.5866 0.04139 0.03145 -0.0246 1.0000 0.0837
-6.250 -0.5740 0.03948 0.02933 -0.0227 1.0000 0.0848
-6.000 -0.5601 0.03793 0.02761 -0.0209 1.0000 0.0870
-5.750 -0.5458 0.03645 0.02591 -0.0191 1.0000 0.0899
-5.500 -0.5304 0.03487 0.02399 -0.0174 1.0000 0.0928
-5.250 -0.5132 0.03330 0.02204 -0.0158 1.0000 0.0949
-5.000 -0.4948 0.03189 0.02043 -0.0144 1.0000 0.0967
-4.750 -0.4760 0.03078 0.01926 -0.0132 1.0000 0.0991
-4.500 -0.4571 0.02989 0.01828 -0.0121 1.0000 0.1028
-4.250 -0.4375 0.02908 0.01727 -0.0109 1.0000 0.1080
-4.000 -0.4006 0.02812 0.01628 -0.0131 0.9938 0.1142
-3.750 -0.3617 0.02725 0.01524 -0.0153 0.9865 0.1215
-3.500 -0.3236 0.02652 0.01451 -0.0177 0.9787 0.1324
-3.250 -0.2838 0.02579 0.01373 -0.0203 0.9714 0.1458
-3.000 -0.2468 0.02506 0.01298 -0.0225 0.9627 0.1649
-2.750 -0.2120 0.02421 0.01227 -0.0243 0.9537 0.1925
-2.500 -0.1765 0.02303 0.01160 -0.0266 0.9459 0.2617
-2.250 -0.1569 0.02121 0.01140 -0.0254 0.9357 0.5378
-2.000 -0.0967 0.02128 0.01233 -0.0275 0.9340 0.8677
-1.750 0.0538 0.02176 0.01233 -0.0489 0.9484 1.0000
-1.500 0.0921 0.02163 0.01197 -0.0517 0.9348 1.0000
-1.250 0.1281 0.02151 0.01166 -0.0540 0.9207 1.0000
-1.000 0.1622 0.02141 0.01139 -0.0556 0.9062 1.0000
-0.750 0.1942 0.02131 0.01115 -0.0568 0.8916 1.0000
-0.500 0.2243 0.02123 0.01094 -0.0574 0.8769 1.0000
-0.250 0.2526 0.02117 0.01076 -0.0576 0.8621 1.0000
0.000 0.2793 0.02113 0.01062 -0.0574 0.8474 1.0000
0.250 0.3047 0.02111 0.01050 -0.0568 0.8329 1.0000
0.500 0.3292 0.02111 0.01042 -0.0561 0.8186 1.0000
0.750 0.3533 0.02113 0.01035 -0.0552 0.8046 1.0000
1.000 0.3760 0.02118 0.01034 -0.0541 0.7904 1.0000
1.250 0.3974 0.02128 0.01039 -0.0528 0.7757 1.0000
1.500 0.4186 0.02139 0.01046 -0.0514 0.7611 1.0000
1.750 0.4399 0.02151 0.01055 -0.0501 0.7466 1.0000
2.000 0.4617 0.02164 0.01065 -0.0488 0.7324 1.0000
2.250 0.4835 0.02177 0.01077 -0.0476 0.7184 1.0000
2.500 0.5056 0.02190 0.01088 -0.0463 0.7045 1.0000
2.750 0.5279 0.02203 0.01100 -0.0451 0.6910 1.0000
3.000 0.5508 0.02216 0.01112 -0.0439 0.6779 1.0000
3.250 0.5742 0.02228 0.01122 -0.0427 0.6650 1.0000
3.500 0.5963 0.02249 0.01145 -0.0415 0.6513 1.0000
3.750 0.6181 0.02276 0.01175 -0.0402 0.6374 1.0000
4.000 0.6400 0.02304 0.01206 -0.0390 0.6236 1.0000
4.250 0.6620 0.02335 0.01240 -0.0379 0.6103 1.0000
4.500 0.6845 0.02366 0.01276 -0.0367 0.5975 1.0000
4.750 0.7072 0.02394 0.01307 -0.0356 0.5844 1.0000
5.000 0.7296 0.02421 0.01337 -0.0343 0.5704 1.0000
5.250 0.7505 0.02451 0.01374 -0.0329 0.5550 1.0000
5.500 0.7710 0.02479 0.01407 -0.0313 0.5388 1.0000
5.750 0.7905 0.02510 0.01444 -0.0297 0.5218 1.0000
6.000 0.8098 0.02540 0.01481 -0.0281 0.5041 1.0000
6.250 0.8292 0.02568 0.01517 -0.0264 0.4862 1.0000
6.500 0.8487 0.02596 0.01549 -0.0247 0.4681 1.0000
6.750 0.8684 0.02628 0.01587 -0.0232 0.4509 1.0000
7.000 0.8883 0.02667 0.01634 -0.0217 0.4346 1.0000
7.250 0.9079 0.02711 0.01689 -0.0202 0.4182 1.0000
7.500 0.9272 0.02759 0.01745 -0.0187 0.4015 1.0000
7.750 0.9449 0.02813 0.01808 -0.0170 0.3828 1.0000
8.000 0.9605 0.02875 0.01882 -0.0151 0.3615 1.0000
8.250 0.9759 0.02936 0.01949 -0.0131 0.3395 1.0000
8.500 0.9887 0.03015 0.02037 -0.0110 0.3151 1.0000
8.750 0.9991 0.03099 0.02120 -0.0086 0.2887 1.0000
9.000 1.0058 0.03197 0.02211 -0.0059 0.2601 1.0000
9.250 1.0103 0.03311 0.02317 -0.0032 0.2323 1.0000
9.500 1.0137 0.03442 0.02441 -0.0006 0.2072 1.0000
9.750 1.0149 0.03587 0.02574 0.0021 0.1884 1.0000
10.000 1.0167 0.03753 0.02735 0.0044 0.1720 1.0000
10.250 1.0182 0.03939 0.02918 0.0064 0.1572 1.0000
10.500 1.0191 0.04146 0.03119 0.0082 0.1441 1.0000
10.750 1.0199 0.04370 0.03338 0.0098 0.1320 1.0000
11.000 1.0215 0.04606 0.03580 0.0111 0.1198 1.0000
11.250 1.0236 0.04851 0.03832 0.0123 0.1092 1.0000
11.500 1.0263 0.05092 0.04066 0.0134 0.1006 1.0000
11.750 1.0287 0.05352 0.04350 0.0141 0.0920 1.0000
12.000 1.0322 0.05601 0.04606 0.0149 0.0858 1.0000
12.250 1.0344 0.05878 0.04906 0.0153 0.0798 1.0000
12.500 1.0367 0.06129 0.05150 0.0157 0.0755 1.0000
12.750 1.0379 0.06453 0.05509 0.0159 0.0712 1.0000
13.000 1.0388 0.06762 0.05835 0.0160 0.0678 1.0000
13.250 1.0409 0.07034 0.06106 0.0160 0.0650 1.0000
13.500 1.0368 0.07437 0.06535 0.0155 0.0626 1.0000
13.750 1.0285 0.07907 0.07034 0.0144 0.0606 1.0000
14.000 1.0190 0.08402 0.07552 0.0130 0.0590 1.0000
14.250 1.0081 0.08934 0.08104 0.0111 0.0578 1.0000
14.500 0.9944 0.09533 0.08723 0.0087 0.0570 1.0000
14.750 0.9747 0.10279 0.09490 0.0051 0.0567 1.0000
15.000 0.9376 0.11476 0.10714 -0.0017 0.0574 1.0000
15.250 0.8796 0.13417 0.12669 -0.0130 0.0597 1.0000
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Polar data table (+)
Polar graphs
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