GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 628 AIRFOIL (goe628-il) Reynolds number: 100,000 Max Cl/Cd: 47.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe628-il-100000-n5.txt Download as CSV file: xf-goe628-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 628 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4763 0.04911 0.04321 -0.1070 0.9450 0.0727
-10.250 -0.4819 0.04307 0.03658 -0.1132 0.9306 0.0732
-10.000 -0.4684 0.03953 0.03259 -0.1161 0.9204 0.0738
-9.750 -0.4465 0.03794 0.03093 -0.1167 0.9104 0.0746
-9.500 -0.4198 0.03629 0.02918 -0.1182 0.9025 0.0757
-9.250 -0.3987 0.03474 0.02744 -0.1186 0.8922 0.0767
-9.000 -0.3733 0.03308 0.02557 -0.1196 0.8838 0.0776
-8.750 -0.3518 0.03165 0.02393 -0.1195 0.8735 0.0784
-8.500 -0.3257 0.03025 0.02230 -0.1201 0.8650 0.0793
-8.250 -0.3027 0.02908 0.02093 -0.1199 0.8552 0.0802
-8.000 -0.2764 0.02796 0.01957 -0.1200 0.8465 0.0814
-7.750 -0.2515 0.02707 0.01861 -0.1198 0.8373 0.0826
-7.500 -0.2253 0.02628 0.01779 -0.1197 0.8285 0.0838
-7.250 -0.1992 0.02554 0.01698 -0.1195 0.8201 0.0851
-7.000 -0.1743 0.02484 0.01619 -0.1191 0.8109 0.0865
-6.750 -0.1466 0.02414 0.01536 -0.1190 0.8035 0.0879
-6.500 -0.1229 0.02357 0.01469 -0.1183 0.7939 0.0895
-6.250 -0.0940 0.02294 0.01394 -0.1184 0.7873 0.0913
-6.000 -0.0717 0.02249 0.01348 -0.1175 0.7777 0.0935
-5.750 -0.0442 0.02198 0.01289 -0.1174 0.7704 0.0966
-5.500 -0.0193 0.02157 0.01237 -0.1168 0.7622 0.0999
-5.250 0.0060 0.02111 0.01188 -0.1163 0.7542 0.1037
-5.000 0.0336 0.02065 0.01133 -0.1161 0.7473 0.1092
-4.750 0.0569 0.02027 0.01095 -0.1153 0.7385 0.1160
-4.500 0.0845 0.01980 0.01045 -0.1152 0.7314 0.1287
-4.250 0.1085 0.01945 0.01017 -0.1145 0.7228 0.1498
-4.000 0.1348 0.01917 0.00994 -0.1141 0.7141 0.1785
-3.750 0.1610 0.01906 0.00982 -0.1135 0.7050 0.2038
-3.500 0.1869 0.01901 0.00972 -0.1129 0.6953 0.2236
-3.250 0.2140 0.01899 0.00961 -0.1124 0.6866 0.2404
-3.000 0.2390 0.01904 0.00962 -0.1116 0.6772 0.2571
-2.750 0.2678 0.01907 0.00951 -0.1114 0.6702 0.2733
-2.500 0.2911 0.01916 0.00958 -0.1104 0.6608 0.2857
-2.250 0.3182 0.01918 0.00954 -0.1099 0.6532 0.2970
-2.000 0.3433 0.01924 0.00950 -0.1092 0.6449 0.3094
-1.750 0.3686 0.01929 0.00955 -0.1084 0.6365 0.3203
-1.500 0.3951 0.01933 0.00951 -0.1079 0.6288 0.3324
-1.250 0.4191 0.01940 0.00955 -0.1069 0.6197 0.3445
-1.000 0.4465 0.01937 0.00946 -0.1065 0.6125 0.3547
-0.750 0.4694 0.01941 0.00948 -0.1054 0.6026 0.3644
-0.500 0.4961 0.01935 0.00935 -0.1049 0.5948 0.3724
-0.250 0.5197 0.01937 0.00937 -0.1040 0.5853 0.3804
0.000 0.5458 0.01933 0.00924 -0.1034 0.5770 0.3887
0.250 0.5695 0.01934 0.00926 -0.1025 0.5673 0.3965
0.500 0.5954 0.01934 0.00915 -0.1019 0.5585 0.4057
0.750 0.6188 0.01935 0.00920 -0.1009 0.5486 0.4134
1.000 0.6444 0.01936 0.00913 -0.1003 0.5398 0.4233
1.250 0.6677 0.01941 0.00921 -0.0993 0.5299 0.4318
1.500 0.6926 0.01944 0.00916 -0.0986 0.5209 0.4424
1.750 0.7153 0.01952 0.00928 -0.0975 0.5104 0.4524
2.000 0.7409 0.01958 0.00925 -0.0969 0.5014 0.4646
2.250 0.7634 0.01970 0.00942 -0.0959 0.4907 0.4767
2.500 0.7882 0.01978 0.00946 -0.0952 0.4823 0.4913
2.750 0.8105 0.01991 0.00966 -0.0942 0.4722 0.5082
3.000 0.8343 0.02000 0.00974 -0.0934 0.4639 0.5298
3.250 0.8555 0.02011 0.00999 -0.0922 0.4542 0.5598
3.500 0.8775 0.02007 0.01010 -0.0910 0.4465 0.6225
4.000 0.9429 0.02014 0.01058 -0.0929 0.4292 1.0000
4.250 0.9634 0.02052 0.01092 -0.0917 0.4214 1.0000
4.500 0.9848 0.02087 0.01117 -0.0906 0.4146 1.0000
4.750 1.0064 0.02125 0.01144 -0.0896 0.4083 1.0000
5.000 1.0261 0.02166 0.01181 -0.0883 0.4014 1.0000
5.250 1.0475 0.02205 0.01209 -0.0872 0.3956 1.0000
5.500 1.0685 0.02248 0.01246 -0.0862 0.3902 1.0000
5.750 1.0881 0.02294 0.01292 -0.0849 0.3847 1.0000
6.000 1.1087 0.02338 0.01330 -0.0838 0.3797 1.0000
6.250 1.1320 0.02381 0.01360 -0.0831 0.3754 1.0000
6.500 1.1482 0.02433 0.01418 -0.0814 0.3702 1.0000
6.750 1.1659 0.02482 0.01467 -0.0799 0.3653 1.0000
7.000 1.1860 0.02530 0.01510 -0.0787 0.3612 1.0000
7.250 1.2109 0.02578 0.01547 -0.0784 0.3577 1.0000
7.500 1.2245 0.02640 0.01619 -0.0764 0.3535 1.0000
7.750 1.2403 0.02699 0.01683 -0.0747 0.3492 1.0000
8.000 1.2584 0.02755 0.01738 -0.0734 0.3453 1.0000
8.250 1.2804 0.02807 0.01784 -0.0727 0.3418 1.0000
8.500 1.2995 0.02870 0.01848 -0.0717 0.3384 1.0000
8.750 1.3114 0.02947 0.01936 -0.0697 0.3348 1.0000
9.000 1.3254 0.03021 0.02016 -0.0680 0.3311 1.0000
9.250 1.3422 0.03087 0.02085 -0.0668 0.3276 1.0000
9.500 1.3633 0.03144 0.02138 -0.0661 0.3244 1.0000
9.750 1.3829 0.03213 0.02208 -0.0653 0.3214 1.0000
10.000 1.3878 0.03320 0.02332 -0.0627 0.3179 1.0000
10.250 1.3963 0.03421 0.02444 -0.0608 0.3144 1.0000
10.500 1.4090 0.03508 0.02536 -0.0593 0.3110 1.0000
10.750 1.4268 0.03577 0.02605 -0.0584 0.3078 1.0000
11.000 1.4535 0.03625 0.02647 -0.0584 0.3049 1.0000
11.250 1.4458 0.03794 0.02839 -0.0552 0.3014 1.0000
11.500 1.4442 0.03954 0.03015 -0.0528 0.2977 1.0000
11.750 1.4499 0.04082 0.03151 -0.0511 0.2939 1.0000
12.000 1.4651 0.04163 0.03234 -0.0502 0.2906 1.0000
12.250 1.4911 0.04195 0.03259 -0.0500 0.2874 1.0000
12.500 1.4686 0.04495 0.03588 -0.0469 0.2837 1.0000
12.750 1.4565 0.04765 0.03877 -0.0449 0.2798 1.0000
13.000 1.4574 0.04957 0.04079 -0.0437 0.2762 1.0000
13.250 1.4727 0.05043 0.04166 -0.0430 0.2730 1.0000
13.500 1.4957 0.05080 0.04200 -0.0426 0.2703 1.0000
13.750 1.4426 0.05744 0.04902 -0.0406 0.2658 1.0000
14.000 1.4050 0.06360 0.05542 -0.0401 0.2611 1.0000
14.250 1.4110 0.06548 0.05735 -0.0397 0.2577 1.0000
14.500 1.4435 0.06451 0.05634 -0.0391 0.2551 1.0000
15.000 1.2795 0.09122 0.08359 -0.0441 0.2395 1.0000
15.250 1.3222 0.08807 0.08043 -0.0425 0.2386 1.0000
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