GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 673 AIRFOIL (goe673-il) Reynolds number: 200,000 Max Cl/Cd: 73.36 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe673-il-200000-n5.txt Download as CSV file: xf-goe673-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 673 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3273 0.08623 0.08303 -0.0433 1.0000 0.0141
-9.500 -0.3351 0.08174 0.07859 -0.0438 1.0000 0.0136
-9.250 -0.3452 0.07708 0.07399 -0.0441 1.0000 0.0131
-9.000 -0.3582 0.07233 0.06929 -0.0442 1.0000 0.0127
-8.750 -0.3749 0.06738 0.06441 -0.0441 1.0000 0.0123
-8.250 -0.4182 0.04576 0.04273 -0.0589 0.9937 0.0108
-8.000 -0.4960 0.05674 0.05346 -0.0587 0.9945 0.0108
-7.750 -0.4805 0.05117 0.04749 -0.0644 0.9884 0.0105
-7.250 -0.4446 0.04139 0.03697 -0.0717 0.9783 0.0101
-7.000 -0.4260 0.03658 0.03168 -0.0739 0.9725 0.0100
-6.500 -0.3725 0.02927 0.02333 -0.0777 0.9654 0.0101
-6.250 -0.3480 0.02659 0.02019 -0.0781 0.9598 0.0103
-6.000 -0.3211 0.02309 0.01627 -0.0793 0.9564 0.0116
-5.750 -0.2891 0.02150 0.01444 -0.0807 0.9538 0.0127
-5.500 -0.2629 0.01998 0.01270 -0.0805 0.9482 0.0132
-5.250 -0.2330 0.01858 0.01108 -0.0810 0.9440 0.0139
-5.000 -0.2017 0.01733 0.00969 -0.0819 0.9408 0.0149
-4.750 -0.1740 0.01651 0.00876 -0.0820 0.9354 0.0168
-4.500 -0.1450 0.01579 0.00793 -0.0823 0.9303 0.0184
-4.250 -0.1145 0.01466 0.00664 -0.0831 0.9266 0.0208
-4.000 -0.0878 0.01410 0.00594 -0.0830 0.9198 0.0257
-3.750 -0.0578 0.01352 0.00524 -0.0835 0.9148 0.0339
-3.500 -0.0313 0.01234 0.00466 -0.0839 0.9089 0.1643
-3.250 -0.0044 0.01165 0.00438 -0.0842 0.9024 0.2747
-3.000 0.0229 0.01096 0.00421 -0.0846 0.8969 0.4123
-2.750 0.0495 0.01069 0.00405 -0.0844 0.8891 0.4705
-2.500 0.0782 0.01047 0.00384 -0.0845 0.8830 0.5064
-2.250 0.1050 0.01027 0.00368 -0.0843 0.8747 0.5421
-2.000 0.1324 0.01007 0.00356 -0.0841 0.8673 0.5822
-1.750 0.1594 0.00991 0.00345 -0.0838 0.8591 0.6243
-1.500 0.1860 0.00978 0.00337 -0.0834 0.8502 0.6651
-1.250 0.2131 0.00964 0.00326 -0.0830 0.8422 0.7035
-1.000 0.2388 0.00952 0.00321 -0.0823 0.8325 0.7428
-0.750 0.2639 0.00939 0.00315 -0.0815 0.8229 0.7828
-0.500 0.2884 0.00926 0.00309 -0.0804 0.8135 0.8251
-0.250 0.3131 0.00916 0.00306 -0.0792 0.8032 0.8733
0.000 0.3426 0.00910 0.00301 -0.0792 0.7924 0.9242
0.250 0.3776 0.00907 0.00293 -0.0806 0.7815 0.9621
0.500 0.4154 0.00904 0.00284 -0.0829 0.7700 0.9956
0.750 0.4433 0.00908 0.00279 -0.0830 0.7577 1.0000
1.000 0.4700 0.00914 0.00278 -0.0828 0.7447 1.0000
1.250 0.4967 0.00921 0.00278 -0.0827 0.7312 1.0000
1.500 0.5234 0.00930 0.00282 -0.0825 0.7173 1.0000
1.750 0.5502 0.00940 0.00286 -0.0824 0.7030 1.0000
2.000 0.5769 0.00952 0.00292 -0.0822 0.6884 1.0000
2.250 0.6035 0.00965 0.00301 -0.0820 0.6737 1.0000
2.500 0.6301 0.00979 0.00311 -0.0818 0.6584 1.0000
2.750 0.6565 0.00995 0.00324 -0.0816 0.6427 1.0000
3.000 0.6828 0.01013 0.00341 -0.0814 0.6268 1.0000
3.250 0.7090 0.01031 0.00358 -0.0812 0.6113 1.0000
3.500 0.7353 0.01050 0.00377 -0.0810 0.5964 1.0000
3.750 0.7615 0.01071 0.00399 -0.0808 0.5818 1.0000
4.000 0.7876 0.01092 0.00426 -0.0805 0.5673 1.0000
4.250 0.8137 0.01114 0.00453 -0.0803 0.5530 1.0000
4.500 0.8378 0.01142 0.00478 -0.0796 0.5250 1.0000
4.750 0.8569 0.01195 0.00502 -0.0780 0.4614 1.0000
5.000 0.8736 0.01273 0.00543 -0.0761 0.3802 1.0000
5.250 0.8837 0.01420 0.00612 -0.0735 0.2432 1.0000
5.500 0.8846 0.01688 0.00760 -0.0699 0.0403 1.0000
5.750 0.9035 0.01781 0.00848 -0.0686 0.0231 1.0000
6.000 0.9244 0.01851 0.00934 -0.0674 0.0192 1.0000
6.250 0.9433 0.01936 0.01033 -0.0660 0.0166 1.0000
6.500 0.9554 0.02076 0.01190 -0.0635 0.0138 1.0000
6.750 0.9715 0.02173 0.01302 -0.0618 0.0130 1.0000
7.000 0.9853 0.02290 0.01431 -0.0596 0.0123 1.0000
7.250 0.9982 0.02419 0.01570 -0.0573 0.0117 1.0000
7.500 1.0114 0.02556 0.01717 -0.0551 0.0112 1.0000
7.750 1.0258 0.02677 0.01847 -0.0532 0.0103 1.0000
8.000 1.0402 0.02789 0.01966 -0.0514 0.0093 1.0000
8.250 1.0546 0.02940 0.02124 -0.0497 0.0087 1.0000
8.500 1.0736 0.03174 0.02368 -0.0486 0.0083 1.0000
8.750 1.0991 0.03503 0.02717 -0.0486 0.0080 1.0000
9.000 1.1172 0.03720 0.02960 -0.0473 0.0079 1.0000
9.250 1.1325 0.03966 0.03235 -0.0457 0.0078 1.0000
9.500 1.1438 0.04236 0.03544 -0.0436 0.0077 1.0000
9.750 1.1498 0.04516 0.03855 -0.0409 0.0077 1.0000
10.000 1.1508 0.04792 0.04162 -0.0378 0.0076 1.0000
10.250 1.1484 0.05053 0.04452 -0.0345 0.0075 1.0000
10.500 1.1438 0.05321 0.04749 -0.0313 0.0073 1.0000
10.750 1.1369 0.05612 0.05067 -0.0284 0.0071 1.0000
11.000 1.1273 0.05934 0.05415 -0.0260 0.0069 1.0000
11.250 1.1161 0.06279 0.05785 -0.0241 0.0067 1.0000
11.500 1.1026 0.06671 0.06200 -0.0228 0.0067 1.0000
11.750 1.0874 0.07102 0.06653 -0.0222 0.0066 1.0000
12.000 1.0709 0.07579 0.07151 -0.0225 0.0066 1.0000
12.250 1.0533 0.08111 0.07703 -0.0236 0.0066 1.0000
12.500 1.0347 0.08702 0.08313 -0.0257 0.0066 1.0000
12.750 1.0155 0.09358 0.08986 -0.0287 0.0067 1.0000
13.000 0.9962 0.10079 0.09722 -0.0326 0.0068 1.0000
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Polar data table (+)
Polar graphs
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