GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 723 AIRFOIL (goe723-il) Reynolds number: 100,000 Max Cl/Cd: 58.52 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe723-il-100000-n5.txt Download as CSV file: xf-goe723-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 723 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2293 0.10595 0.10104 -0.0416 1.0000 0.0840
-9.750 -0.2518 0.10377 0.09896 -0.0439 1.0000 0.0865
-9.500 -0.2684 0.10138 0.09667 -0.0448 1.0000 0.0869
-9.250 -0.2606 0.09796 0.09332 -0.0423 1.0000 0.0879
-9.000 -0.2406 0.09505 0.09042 -0.0411 0.9978 0.0898
-8.750 -0.2247 0.09100 0.08636 -0.0439 0.9915 0.0916
-8.500 -0.2133 0.08655 0.08190 -0.0474 0.9843 0.0923
-8.000 -0.3474 0.08009 0.07520 -0.0526 0.9869 0.0541
-7.750 -0.3282 0.07660 0.07169 -0.0559 0.9763 0.0533
-7.500 -0.3113 0.07151 0.06658 -0.0621 0.9630 0.0522
-7.250 -0.2965 0.06457 0.05959 -0.0712 0.9489 0.0508
-7.000 -0.2894 0.04794 0.04240 -0.0928 0.9323 0.0486
-6.750 -0.2701 0.04224 0.03622 -0.0988 0.9201 0.0490
-6.500 -0.2468 0.03792 0.03139 -0.1026 0.9101 0.0492
-6.250 -0.2201 0.03417 0.02708 -0.1056 0.9015 0.0489
-6.000 -0.1948 0.03153 0.02397 -0.1068 0.8913 0.0488
-5.500 -0.1382 0.02761 0.01926 -0.1088 0.8735 0.0490
-5.250 -0.1065 0.02604 0.01737 -0.1099 0.8663 0.0494
-5.000 -0.0807 0.02486 0.01596 -0.1097 0.8557 0.0499
-4.750 -0.0492 0.02377 0.01461 -0.1105 0.8485 0.0512
-4.500 -0.0236 0.02293 0.01358 -0.1101 0.8380 0.0524
-4.250 0.0066 0.02205 0.01249 -0.1105 0.8305 0.0533
-4.000 0.0325 0.02131 0.01163 -0.1100 0.8208 0.0538
-3.750 0.0617 0.02061 0.01080 -0.1101 0.8133 0.0543
-3.500 0.0867 0.01994 0.01013 -0.1095 0.8040 0.0551
-3.250 0.1145 0.01932 0.00947 -0.1094 0.7969 0.0561
-3.000 0.1391 0.01889 0.00902 -0.1087 0.7878 0.0573
-2.750 0.1675 0.01846 0.00849 -0.1086 0.7813 0.0590
-2.500 0.1917 0.01817 0.00814 -0.1079 0.7722 0.0617
-2.250 0.2196 0.01782 0.00769 -0.1077 0.7656 0.0652
-2.000 0.2445 0.01753 0.00737 -0.1071 0.7575 0.0691
-1.750 0.2718 0.01727 0.00700 -0.1067 0.7506 0.0743
-1.500 0.2978 0.01694 0.00672 -0.1063 0.7434 0.0863
-1.250 0.3230 0.01626 0.00658 -0.1060 0.7362 0.2038
-1.000 0.3505 0.01594 0.00661 -0.1059 0.7303 0.3210
-0.750 0.3750 0.01591 0.00673 -0.1052 0.7223 0.3818
-0.500 0.4033 0.01587 0.00672 -0.1050 0.7161 0.4258
-0.250 0.4293 0.01587 0.00680 -0.1045 0.7090 0.4676
0.000 0.4555 0.01582 0.00688 -0.1039 0.7019 0.5202
0.250 0.4834 0.01575 0.00687 -0.1037 0.6958 0.5670
0.500 0.5091 0.01571 0.00692 -0.1031 0.6876 0.6031
0.750 0.5379 0.01555 0.00684 -0.1029 0.6812 0.6501
1.000 0.5655 0.01525 0.00688 -0.1026 0.6726 0.7405
1.250 0.6274 0.01496 0.00672 -0.1095 0.6647 1.0000
1.500 0.6522 0.01516 0.00683 -0.1088 0.6565 1.0000
1.750 0.6788 0.01531 0.00687 -0.1084 0.6494 1.0000
2.000 0.7043 0.01551 0.00699 -0.1078 0.6421 1.0000
2.250 0.7298 0.01570 0.00711 -0.1073 0.6347 1.0000
2.500 0.7563 0.01587 0.00720 -0.1068 0.6281 1.0000
2.750 0.7804 0.01609 0.00741 -0.1060 0.6200 1.0000
3.000 0.8076 0.01625 0.00749 -0.1057 0.6138 1.0000
3.250 0.8308 0.01651 0.00778 -0.1048 0.6054 1.0000
3.500 0.8571 0.01668 0.00791 -0.1043 0.5986 1.0000
3.750 0.8808 0.01693 0.00819 -0.1034 0.5906 1.0000
4.000 0.9062 0.01713 0.00837 -0.1028 0.5832 1.0000
4.250 0.9303 0.01738 0.00866 -0.1020 0.5753 1.0000
4.500 0.9549 0.01759 0.00887 -0.1012 0.5669 1.0000
4.750 0.9777 0.01780 0.00910 -0.1001 0.5562 1.0000
5.000 1.0010 0.01793 0.00922 -0.0990 0.5440 1.0000
5.250 1.0236 0.01806 0.00932 -0.0977 0.5303 1.0000
5.500 1.0450 0.01825 0.00952 -0.0963 0.5163 1.0000
5.750 1.0660 0.01849 0.00982 -0.0949 0.5028 1.0000
6.000 1.0867 0.01872 0.01007 -0.0934 0.4877 1.0000
6.250 1.1062 0.01895 0.01029 -0.0917 0.4700 1.0000
6.500 1.1253 0.01923 0.01057 -0.0900 0.4528 1.0000
6.750 1.1442 0.01956 0.01092 -0.0883 0.4360 1.0000
7.000 1.1619 0.01992 0.01129 -0.0864 0.4173 1.0000
7.250 1.1780 0.02035 0.01170 -0.0843 0.3953 1.0000
7.500 1.1922 0.02085 0.01213 -0.0819 0.3718 1.0000
7.750 1.2045 0.02146 0.01269 -0.0793 0.3451 1.0000
8.000 1.2130 0.02223 0.01333 -0.0761 0.3134 1.0000
8.250 1.2169 0.02317 0.01411 -0.0723 0.2765 1.0000
8.500 1.2126 0.02450 0.01513 -0.0676 0.2175 1.0000
8.750 1.1971 0.02668 0.01675 -0.0622 0.1484 1.0000
9.000 1.1920 0.02859 0.01842 -0.0585 0.1254 1.0000
9.250 1.1907 0.03038 0.02014 -0.0555 0.1136 1.0000
9.500 1.1936 0.03198 0.02181 -0.0531 0.1052 1.0000
9.750 1.1936 0.03388 0.02371 -0.0509 0.0997 1.0000
10.000 1.1976 0.03555 0.02548 -0.0490 0.0952 1.0000
10.250 1.2014 0.03733 0.02735 -0.0474 0.0914 1.0000
10.500 1.2036 0.03930 0.02939 -0.0458 0.0883 1.0000
10.750 1.2041 0.04149 0.03158 -0.0443 0.0857 1.0000
11.000 1.2102 0.04325 0.03347 -0.0431 0.0829 1.0000
11.250 1.2156 0.04511 0.03544 -0.0419 0.0803 1.0000
11.500 1.2208 0.04701 0.03740 -0.0409 0.0779 1.0000
11.750 1.2258 0.04895 0.03937 -0.0398 0.0759 1.0000
12.000 1.2316 0.05083 0.04123 -0.0386 0.0740 1.0000
12.250 1.2409 0.05244 0.04296 -0.0376 0.0718 1.0000
12.500 1.2499 0.05410 0.04473 -0.0367 0.0694 1.0000
12.750 1.2585 0.05580 0.04648 -0.0358 0.0672 1.0000
13.000 1.2672 0.05752 0.04820 -0.0349 0.0652 1.0000
13.250 1.2788 0.05903 0.04969 -0.0338 0.0629 1.0000
13.500 1.2878 0.06086 0.05170 -0.0330 0.0608 1.0000
13.750 1.2960 0.06277 0.05376 -0.0323 0.0586 1.0000
14.000 1.3034 0.06476 0.05581 -0.0317 0.0565 1.0000
14.250 1.3140 0.06648 0.05750 -0.0310 0.0546 1.0000
14.500 1.3235 0.06848 0.05960 -0.0302 0.0527 1.0000
14.750 1.3261 0.07115 0.06253 -0.0299 0.0510 1.0000
15.250 1.3322 0.07649 0.06821 -0.0294 0.0476 1.0000
15.500 1.3363 0.07899 0.07077 -0.0292 0.0462 1.0000
15.750 1.3448 0.08116 0.07289 -0.0288 0.0446 1.0000
16.000 1.3365 0.08535 0.07743 -0.0294 0.0435 1.0000
16.250 1.3292 0.08959 0.08196 -0.0302 0.0424 1.0000
16.500 1.3223 0.09390 0.08651 -0.0311 0.0414 1.0000
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