GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 500,000 Max Cl/Cd: 107.98 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe591-il-500000.txt Download as CSV file: xf-goe591-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2410 0.08423 0.08209 -0.0619 0.9862 0.0279
-8.500 -0.2259 0.07858 0.07644 -0.0693 0.9810 0.0280
-8.250 -0.2156 0.07414 0.07201 -0.0720 0.9754 0.0288
-8.000 -0.1926 0.07148 0.06933 -0.0755 0.9717 0.0295
-7.750 -0.1750 0.06780 0.06565 -0.0808 0.9628 0.0305
-7.500 -0.1478 0.06188 0.05969 -0.0918 0.9567 0.0320
-7.250 -0.1392 0.04528 0.04275 -0.1128 0.9338 0.0350
-7.000 -0.1190 0.04395 0.04138 -0.1137 0.9232 0.0357
-6.750 -0.0977 0.04291 0.04028 -0.1142 0.9116 0.0367
-6.500 -0.0803 0.04072 0.03797 -0.1150 0.8979 0.0385
-6.250 -0.0793 0.03174 0.02833 -0.1169 0.8817 0.0437
-6.000 -0.0589 0.03081 0.02737 -0.1164 0.8704 0.0446
-5.750 -0.0385 0.02958 0.02602 -0.1160 0.8602 0.0461
-5.500 -0.0404 0.01829 0.01299 -0.1121 0.8492 0.0345
-5.250 -0.0209 0.01571 0.01002 -0.1110 0.8399 0.0351
-5.000 0.0028 0.01441 0.00854 -0.1103 0.8317 0.0361
-4.750 0.0282 0.01384 0.00787 -0.1098 0.8231 0.0373
-4.500 0.0536 0.01321 0.00711 -0.1093 0.8149 0.0381
-4.250 0.0794 0.01263 0.00641 -0.1087 0.8069 0.0389
-4.000 0.1051 0.01211 0.00579 -0.1082 0.7987 0.0397
-3.750 0.1312 0.01173 0.00530 -0.1076 0.7907 0.0409
-3.500 0.1570 0.01137 0.00487 -0.1071 0.7824 0.0418
-3.250 0.1832 0.01104 0.00443 -0.1066 0.7746 0.0423
-3.000 0.2078 0.01047 0.00381 -0.1058 0.7658 0.0435
-2.750 0.2334 0.01013 0.00341 -0.1053 0.7578 0.0451
-2.500 0.2591 0.00990 0.00316 -0.1047 0.7485 0.0471
-2.250 0.2854 0.00975 0.00296 -0.1042 0.7402 0.0497
-2.000 0.3114 0.00958 0.00274 -0.1037 0.7307 0.0522
-1.750 0.3373 0.00938 0.00255 -0.1031 0.7213 0.0582
-1.250 0.3889 0.00905 0.00228 -0.1021 0.7017 0.1011
-1.000 0.4146 0.00893 0.00220 -0.1016 0.6916 0.1278
-0.750 0.4400 0.00881 0.00217 -0.1011 0.6812 0.1714
-0.500 0.4654 0.00868 0.00214 -0.1006 0.6699 0.2185
-0.250 0.4905 0.00854 0.00211 -0.1000 0.6589 0.2708
0.000 0.5133 0.00817 0.00213 -0.0992 0.6478 0.4241
0.250 0.5242 0.00712 0.00223 -0.0956 0.6369 0.8089
0.500 0.6117 0.00708 0.00233 -0.1080 0.6220 0.9925
0.750 0.6525 0.00718 0.00231 -0.1109 0.6076 1.0000
1.000 0.6748 0.00730 0.00232 -0.1097 0.5939 1.0000
1.250 0.6971 0.00742 0.00235 -0.1085 0.5805 1.0000
1.500 0.7196 0.00755 0.00239 -0.1073 0.5686 1.0000
1.750 0.7420 0.00769 0.00244 -0.1062 0.5576 1.0000
2.000 0.7647 0.00782 0.00250 -0.1051 0.5464 1.0000
2.250 0.7877 0.00795 0.00257 -0.1041 0.5360 1.0000
2.500 0.8105 0.00811 0.00266 -0.1031 0.5266 1.0000
2.750 0.8335 0.00825 0.00275 -0.1021 0.5168 1.0000
3.000 0.8565 0.00840 0.00285 -0.1011 0.5065 1.0000
3.250 0.8790 0.00858 0.00295 -0.1000 0.4964 1.0000
3.500 0.9018 0.00873 0.00307 -0.0989 0.4862 1.0000
3.750 0.9251 0.00888 0.00319 -0.0980 0.4773 1.0000
4.000 0.9479 0.00907 0.00332 -0.0970 0.4691 1.0000
4.250 0.9716 0.00921 0.00345 -0.0962 0.4612 1.0000
4.750 1.0180 0.00955 0.00375 -0.0944 0.4443 1.0000
5.000 1.0407 0.00976 0.00392 -0.0935 0.4364 1.0000
5.250 1.0642 0.00991 0.00409 -0.0927 0.4279 1.0000
5.500 1.0869 0.01012 0.00427 -0.0917 0.4198 1.0000
5.750 1.1100 0.01029 0.00445 -0.0909 0.4110 1.0000
6.000 1.1327 0.01049 0.00464 -0.0900 0.4028 1.0000
6.250 1.1542 0.01073 0.00485 -0.0888 0.3924 1.0000
6.500 1.1764 0.01092 0.00505 -0.0878 0.3805 1.0000
6.750 1.1977 0.01115 0.00526 -0.0867 0.3677 1.0000
7.000 1.2184 0.01141 0.00550 -0.0855 0.3544 1.0000
7.250 1.2376 0.01171 0.00575 -0.0840 0.3369 1.0000
7.500 1.2565 0.01204 0.00603 -0.0825 0.3206 1.0000
7.750 1.2747 0.01239 0.00634 -0.0808 0.3050 1.0000
8.000 1.2910 0.01279 0.00668 -0.0789 0.2885 1.0000
8.250 1.3055 0.01322 0.00705 -0.0766 0.2709 1.0000
8.500 1.3194 0.01368 0.00745 -0.0742 0.2536 1.0000
8.750 1.3321 0.01423 0.00792 -0.0718 0.2349 1.0000
9.000 1.3433 0.01485 0.00845 -0.0691 0.2160 1.0000
9.250 1.3554 0.01546 0.00900 -0.0668 0.1969 1.0000
9.500 1.3641 0.01627 0.00967 -0.0639 0.1714 1.0000
9.750 1.3687 0.01731 0.01052 -0.0607 0.1401 1.0000
10.000 1.3707 0.01854 0.01157 -0.0572 0.1132 1.0000
10.250 1.3689 0.02004 0.01286 -0.0535 0.0767 1.0000
10.500 1.3581 0.02217 0.01473 -0.0490 0.0405 1.0000
10.750 1.3560 0.02392 0.01638 -0.0459 0.0239 1.0000
11.000 1.3615 0.02527 0.01779 -0.0438 0.0205 1.0000
11.250 1.3673 0.02665 0.01924 -0.0418 0.0192 1.0000
11.500 1.3714 0.02824 0.02091 -0.0399 0.0180 1.0000
11.750 1.3753 0.02990 0.02267 -0.0382 0.0171 1.0000
12.000 1.3804 0.03153 0.02440 -0.0367 0.0168 1.0000
12.250 1.3834 0.03342 0.02638 -0.0353 0.0160 1.0000
12.500 1.3848 0.03551 0.02859 -0.0340 0.0156 1.0000
12.750 1.3844 0.03787 0.03104 -0.0328 0.0152 1.0000
13.000 1.3824 0.04049 0.03376 -0.0317 0.0148 1.0000
13.250 1.3784 0.04342 0.03679 -0.0309 0.0145 1.0000
13.500 1.3701 0.04698 0.04046 -0.0303 0.0142 1.0000
13.750 1.3582 0.05111 0.04472 -0.0299 0.0138 1.0000
14.000 1.3490 0.05510 0.04882 -0.0298 0.0137 1.0000
14.250 1.3476 0.05830 0.05212 -0.0299 0.0135 1.0000
14.500 1.3446 0.06177 0.05569 -0.0301 0.0134 1.0000
14.750 1.3422 0.06525 0.05927 -0.0304 0.0132 1.0000
15.000 1.3384 0.06898 0.06309 -0.0309 0.0130 1.0000
15.250 1.3360 0.07259 0.06680 -0.0314 0.0129 1.0000
15.500 1.3325 0.07640 0.07070 -0.0321 0.0125 1.0000
15.750 1.3297 0.08016 0.07455 -0.0328 0.0123 1.0000
16.000 1.3268 0.08399 0.07846 -0.0336 0.0120 1.0000
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Polar data table (+)
Polar graphs
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