GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 500,000 Max Cl/Cd: 103.21 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe693-il-500000.txt Download as CSV file: xf-goe693-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.7510 0.04693 0.04417 -0.0831 1.0000 0.0276
-11.750 -0.7983 0.04261 0.03971 -0.0803 1.0000 0.0273
-11.500 -0.8276 0.03952 0.03640 -0.0759 1.0000 0.0274
-11.250 -0.8444 0.03693 0.03357 -0.0719 1.0000 0.0277
-11.000 -0.8491 0.03479 0.03116 -0.0690 0.9998 0.0282
-10.750 -0.8321 0.03088 0.02678 -0.0715 0.9967 0.0290
-10.500 -0.8040 0.02919 0.02504 -0.0734 0.9946 0.0298
-10.250 -0.7737 0.02817 0.02394 -0.0752 0.9925 0.0306
-10.000 -0.7451 0.02695 0.02258 -0.0766 0.9894 0.0315
-9.750 -0.7148 0.02564 0.02107 -0.0783 0.9868 0.0325
-9.500 -0.6825 0.02447 0.01965 -0.0802 0.9847 0.0335
-9.250 -0.6508 0.02276 0.01765 -0.0822 0.9831 0.0344
-9.000 -0.6242 0.02101 0.01578 -0.0830 0.9793 0.0354
-8.750 -0.5917 0.02026 0.01499 -0.0845 0.9763 0.0364
-8.500 -0.5570 0.01954 0.01417 -0.0864 0.9742 0.0376
-8.250 -0.5225 0.01868 0.01319 -0.0882 0.9720 0.0387
-8.000 -0.4880 0.01785 0.01221 -0.0899 0.9699 0.0397
-7.750 -0.4611 0.01738 0.01161 -0.0897 0.9633 0.0404
-7.500 -0.4334 0.01590 0.01002 -0.0902 0.9586 0.0419
-7.250 -0.4052 0.01525 0.00933 -0.0904 0.9535 0.0430
-7.000 -0.3798 0.01473 0.00876 -0.0898 0.9455 0.0441
-6.750 -0.3529 0.01422 0.00818 -0.0896 0.9393 0.0453
-6.500 -0.3281 0.01379 0.00768 -0.0888 0.9298 0.0466
-6.250 -0.3019 0.01343 0.00722 -0.0883 0.9219 0.0477
-6.000 -0.2778 0.01267 0.00640 -0.0875 0.9121 0.0494
-5.750 -0.2523 0.01220 0.00592 -0.0870 0.9018 0.0513
-5.500 -0.2261 0.01186 0.00550 -0.0865 0.8921 0.0534
-5.250 -0.1996 0.01156 0.00513 -0.0860 0.8809 0.0557
-5.000 -0.1734 0.01114 0.00467 -0.0856 0.8698 0.0592
-4.750 -0.1464 0.01088 0.00438 -0.0854 0.8595 0.0635
-4.500 -0.1195 0.01061 0.00405 -0.0850 0.8487 0.0691
-4.250 -0.0919 0.01045 0.00387 -0.0849 0.8380 0.0765
-4.000 -0.0643 0.01029 0.00371 -0.0847 0.8286 0.0860
-3.750 -0.0366 0.01018 0.00357 -0.0847 0.8190 0.0950
-3.500 -0.0083 0.01017 0.00350 -0.0846 0.8095 0.1025
-3.250 0.0190 0.01001 0.00331 -0.0845 0.8002 0.1103
-3.000 0.0472 0.00995 0.00321 -0.0845 0.7906 0.1164
-2.750 0.0748 0.00982 0.00304 -0.0844 0.7824 0.1229
-2.500 0.1029 0.00973 0.00294 -0.0844 0.7740 0.1296
-2.250 0.1310 0.00967 0.00281 -0.0843 0.7668 0.1357
-2.000 0.1590 0.00953 0.00271 -0.0844 0.7588 0.1436
-1.750 0.1870 0.00948 0.00260 -0.0843 0.7517 0.1520
-1.500 0.2150 0.00936 0.00252 -0.0844 0.7435 0.1629
-1.250 0.2427 0.00926 0.00242 -0.0843 0.7350 0.1780
-1.000 0.2703 0.00908 0.00235 -0.0842 0.7254 0.2058
-0.750 0.2977 0.00886 0.00229 -0.0842 0.7177 0.2639
-0.500 0.3246 0.00849 0.00226 -0.0842 0.7108 0.3650
-0.250 0.3498 0.00796 0.00226 -0.0839 0.7049 0.5388
0.000 0.3722 0.00733 0.00232 -0.0828 0.6985 0.7432
0.250 0.3949 0.00696 0.00242 -0.0808 0.6923 0.9134
0.500 0.4414 0.00703 0.00247 -0.0846 0.6864 0.9767
0.750 0.4899 0.00709 0.00250 -0.0890 0.6795 0.9949
1.000 0.5288 0.00718 0.00249 -0.0914 0.6726 1.0000
1.250 0.5547 0.00720 0.00249 -0.0910 0.6650 1.0000
1.500 0.5804 0.00727 0.00249 -0.0905 0.6579 1.0000
1.750 0.6063 0.00731 0.00251 -0.0901 0.6503 1.0000
2.000 0.6320 0.00738 0.00252 -0.0896 0.6421 1.0000
2.250 0.6579 0.00743 0.00255 -0.0892 0.6331 1.0000
2.500 0.6834 0.00752 0.00258 -0.0886 0.6245 1.0000
2.750 0.7093 0.00758 0.00262 -0.0882 0.6138 1.0000
3.000 0.7348 0.00766 0.00267 -0.0877 0.6023 1.0000
3.250 0.7603 0.00776 0.00272 -0.0871 0.5902 1.0000
3.500 0.7858 0.00788 0.00278 -0.0866 0.5770 1.0000
3.750 0.8111 0.00800 0.00286 -0.0861 0.5606 1.0000
4.000 0.8363 0.00814 0.00295 -0.0855 0.5416 1.0000
4.250 0.8608 0.00834 0.00306 -0.0849 0.5177 1.0000
4.500 0.8847 0.00859 0.00320 -0.0841 0.4899 1.0000
4.750 0.9081 0.00889 0.00338 -0.0833 0.4614 1.0000
5.000 0.9311 0.00924 0.00359 -0.0825 0.4333 1.0000
5.250 0.9541 0.00960 0.00383 -0.0816 0.4084 1.0000
5.500 0.9774 0.00995 0.00408 -0.0809 0.3872 1.0000
5.750 1.0011 0.01027 0.00433 -0.0802 0.3703 1.0000
6.000 1.0250 0.01057 0.00459 -0.0795 0.3566 1.0000
6.250 1.0486 0.01089 0.00486 -0.0789 0.3437 1.0000
6.500 1.0725 0.01119 0.00513 -0.0782 0.3305 1.0000
6.750 1.0958 0.01151 0.00541 -0.0775 0.3156 1.0000
7.000 1.1183 0.01188 0.00572 -0.0767 0.2978 1.0000
7.250 1.1407 0.01225 0.00602 -0.0758 0.2738 1.0000
7.500 1.1606 0.01277 0.00638 -0.0746 0.2392 1.0000
7.750 1.1779 0.01345 0.00684 -0.0730 0.2025 1.0000
8.000 1.1965 0.01403 0.00733 -0.0716 0.1859 1.0000
8.250 1.2156 0.01455 0.00780 -0.0703 0.1753 1.0000
8.500 1.2339 0.01510 0.00831 -0.0688 0.1662 1.0000
8.750 1.2542 0.01549 0.00873 -0.0677 0.1596 1.0000
9.000 1.2716 0.01602 0.00926 -0.0661 0.1513 1.0000
9.250 1.2905 0.01639 0.00965 -0.0647 0.1427 1.0000
9.500 1.3070 0.01687 0.01013 -0.0629 0.1326 1.0000
9.750 1.3237 0.01737 0.01059 -0.0612 0.1165 1.0000
10.000 1.3349 0.01821 0.01126 -0.0589 0.0930 1.0000
10.250 1.3449 0.01915 0.01212 -0.0564 0.0788 1.0000
10.500 1.3528 0.02026 0.01315 -0.0537 0.0600 1.0000
10.750 1.3540 0.02185 0.01452 -0.0504 0.0363 1.0000
11.000 1.3605 0.02317 0.01583 -0.0479 0.0305 1.0000
11.250 1.3698 0.02433 0.01704 -0.0459 0.0278 1.0000
11.500 1.3748 0.02585 0.01861 -0.0436 0.0257 1.0000
11.750 1.3853 0.02701 0.01986 -0.0420 0.0246 1.0000
12.000 1.3938 0.02836 0.02129 -0.0403 0.0234 1.0000
12.250 1.3999 0.02995 0.02294 -0.0386 0.0224 1.0000
12.500 1.4010 0.03203 0.02508 -0.0368 0.0215 1.0000
12.750 1.4045 0.03397 0.02712 -0.0352 0.0208 1.0000
13.000 1.4114 0.03568 0.02893 -0.0341 0.0202 1.0000
13.250 1.4163 0.03762 0.03096 -0.0330 0.0195 1.0000
13.500 1.4199 0.03972 0.03314 -0.0320 0.0190 1.0000
13.750 1.4216 0.04207 0.03556 -0.0310 0.0185 1.0000
14.000 1.4208 0.04473 0.03830 -0.0301 0.0181 1.0000
14.250 1.4159 0.04789 0.04154 -0.0292 0.0177 1.0000
14.500 1.4069 0.05157 0.04532 -0.0284 0.0173 1.0000
14.750 1.4080 0.05431 0.04816 -0.0280 0.0171 1.0000
15.000 1.4089 0.05711 0.05107 -0.0278 0.0168 1.0000
15.250 1.4084 0.06014 0.05421 -0.0276 0.0165 1.0000
15.500 1.4072 0.06334 0.05751 -0.0276 0.0163 1.0000
15.750 1.4055 0.06666 0.06093 -0.0277 0.0160 1.0000
16.000 1.4035 0.07007 0.06444 -0.0279 0.0157 1.0000
16.250 1.4011 0.07361 0.06807 -0.0283 0.0154 1.0000
16.500 1.3986 0.07725 0.07179 -0.0288 0.0152 1.0000
16.750 1.3956 0.08101 0.07563 -0.0294 0.0149 1.0000
17.000 1.3919 0.08487 0.07955 -0.0301 0.0146 1.0000
17.250 1.3877 0.08876 0.08351 -0.0308 0.0144 1.0000
17.500 1.3827 0.09256 0.08737 -0.0311 0.0141 1.0000
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Polar data table (+)
Polar graphs
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