GOE 439 AIRFOIL (goe439-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 439 AIRFOIL (goe439-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.26 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe439-il-1000000.txt Download as CSV file: xf-goe439-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 439 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3072 0.10354 0.10194 -0.0274 1.0000 0.0083
-9.000 -0.3038 0.10076 0.09917 -0.0279 1.0000 0.0086
-8.750 -0.3013 0.09793 0.09637 -0.0282 1.0000 0.0090
-8.000 -0.1989 0.07019 0.06878 -0.0423 0.9902 0.0104
-7.750 -0.1865 0.06637 0.06497 -0.0452 0.9854 0.0106
-7.500 -0.1743 0.06272 0.06131 -0.0482 0.9785 0.0109
-7.250 -0.1582 0.05834 0.05693 -0.0530 0.9721 0.0113
-7.000 -0.1403 0.05385 0.05242 -0.0586 0.9612 0.0120
-6.750 -0.1222 0.04888 0.04741 -0.0654 0.9437 0.0127
-6.500 -0.1075 0.04413 0.04257 -0.0723 0.9160 0.0138
-6.250 -0.0977 0.04012 0.03844 -0.0757 0.8879 0.0139
-6.000 -0.0864 0.03620 0.03441 -0.0788 0.8642 0.0139
-5.750 -0.0731 0.03181 0.02988 -0.0822 0.8444 0.0139
-5.500 -0.0718 0.01646 0.01304 -0.1061 0.8789 0.0098
-5.250 -0.0527 0.01249 0.00826 -0.1053 0.8600 0.0104
-4.750 -0.0028 0.01097 0.00629 -0.1043 0.8268 0.0114
-4.500 0.0230 0.01043 0.00557 -0.1037 0.8118 0.0120
-4.250 0.0490 0.00995 0.00491 -0.1032 0.7981 0.0127
-4.000 0.0754 0.00970 0.00454 -0.1028 0.7853 0.0136
-3.750 0.1010 0.00891 0.00355 -0.1023 0.7734 0.0150
-3.500 0.1276 0.00861 0.00318 -0.1019 0.7620 0.0162
-3.250 0.1545 0.00843 0.00291 -0.1016 0.7513 0.0177
-3.000 0.1814 0.00829 0.00269 -0.1013 0.7409 0.0191
-2.750 0.2079 0.00791 0.00224 -0.1009 0.7307 0.0225
-2.500 0.2351 0.00786 0.00215 -0.1006 0.7206 0.0255
-2.250 0.2618 0.00762 0.00183 -0.1003 0.7106 0.0297
-1.750 0.3162 0.00753 0.00167 -0.0998 0.6892 0.0367
-1.500 0.3430 0.00731 0.00139 -0.0995 0.6782 0.0434
-1.250 0.3700 0.00727 0.00128 -0.0992 0.6663 0.0476
-1.000 0.3969 0.00717 0.00115 -0.0989 0.6536 0.0561
-0.750 0.4235 0.00707 0.00110 -0.0986 0.6397 0.0867
-0.500 0.4504 0.00707 0.00109 -0.0984 0.6242 0.1082
-0.250 0.4773 0.00711 0.00107 -0.0981 0.6075 0.1183
0.000 0.5039 0.00714 0.00106 -0.0978 0.5897 0.1268
0.250 0.5304 0.00721 0.00104 -0.0975 0.5724 0.1336
0.500 0.5569 0.00726 0.00105 -0.0972 0.5558 0.1424
0.750 0.5835 0.00729 0.00106 -0.0969 0.5406 0.1565
1.000 0.6097 0.00722 0.00111 -0.0967 0.5263 0.2256
1.250 0.6326 0.00659 0.00126 -0.0961 0.5131 0.5708
1.500 0.6718 0.00580 0.00135 -0.0987 0.4966 1.0000
1.750 0.6977 0.00594 0.00140 -0.0983 0.4819 1.0000
2.000 0.7238 0.00608 0.00146 -0.0979 0.4694 1.0000
2.250 0.7499 0.00621 0.00153 -0.0975 0.4579 1.0000
2.500 0.7762 0.00632 0.00159 -0.0972 0.4470 1.0000
2.750 0.8024 0.00646 0.00167 -0.0968 0.4354 1.0000
3.000 0.8284 0.00660 0.00175 -0.0965 0.4230 1.0000
3.250 0.8544 0.00675 0.00186 -0.0961 0.4118 1.0000
3.500 0.8803 0.00691 0.00196 -0.0958 0.4006 1.0000
3.750 0.9060 0.00709 0.00208 -0.0954 0.3856 1.0000
4.000 0.9319 0.00725 0.00219 -0.0950 0.3734 1.0000
4.250 0.9578 0.00741 0.00233 -0.0947 0.3616 1.0000
4.750 1.0081 0.00786 0.00264 -0.0938 0.3276 1.0000
5.000 1.0330 0.00811 0.00281 -0.0933 0.3087 1.0000
5.250 1.0577 0.00837 0.00301 -0.0928 0.2904 1.0000
5.500 1.0817 0.00869 0.00323 -0.0923 0.2671 1.0000
5.750 1.1041 0.00917 0.00353 -0.0914 0.2327 1.0000
6.000 1.1233 0.00995 0.00399 -0.0902 0.1757 1.0000
6.250 1.1343 0.01154 0.00500 -0.0877 0.0706 1.0000
6.500 1.1516 0.01255 0.00578 -0.0859 0.0228 1.0000
6.750 1.1750 0.01289 0.00616 -0.0853 0.0200 1.0000
7.000 1.1963 0.01345 0.00676 -0.0842 0.0160 1.0000
7.250 1.2184 0.01390 0.00727 -0.0832 0.0146 1.0000
7.500 1.2407 0.01430 0.00771 -0.0824 0.0132 1.0000
7.750 1.2622 0.01476 0.00819 -0.0814 0.0119 1.0000
8.000 1.2770 0.01582 0.00937 -0.0793 0.0103 1.0000
8.250 1.2980 0.01625 0.00985 -0.0783 0.0100 1.0000
8.500 1.3172 0.01681 0.01046 -0.0770 0.0094 1.0000
8.750 1.3352 0.01743 0.01115 -0.0755 0.0089 1.0000
9.000 1.3516 0.01812 0.01190 -0.0738 0.0084 1.0000
9.250 1.3672 0.01880 0.01263 -0.0720 0.0080 1.0000
9.500 1.3789 0.01962 0.01350 -0.0696 0.0074 1.0000
9.750 1.3707 0.02128 0.01530 -0.0639 0.0070 1.0000
10.000 1.3767 0.02227 0.01638 -0.0608 0.0067 1.0000
10.250 1.3866 0.02308 0.01726 -0.0584 0.0066 1.0000
10.500 1.3912 0.02427 0.01853 -0.0555 0.0064 1.0000
10.750 1.3963 0.02551 0.01987 -0.0530 0.0062 1.0000
11.000 1.3985 0.02706 0.02151 -0.0504 0.0060 1.0000
11.250 1.4009 0.02872 0.02326 -0.0481 0.0059 1.0000
11.500 1.4068 0.03018 0.02480 -0.0465 0.0056 1.0000
11.750 1.4091 0.03207 0.02678 -0.0447 0.0056 1.0000
12.000 1.4096 0.03428 0.02910 -0.0431 0.0055 1.0000
12.250 1.4139 0.03618 0.03108 -0.0420 0.0053 1.0000
12.500 1.4183 0.03813 0.03310 -0.0411 0.0051 1.0000
12.750 1.4185 0.04067 0.03574 -0.0401 0.0051 1.0000
13.000 1.4205 0.04305 0.03821 -0.0395 0.0050 1.0000
13.250 1.4203 0.04578 0.04102 -0.0390 0.0048 1.0000
13.500 1.4169 0.04899 0.04433 -0.0385 0.0047 1.0000
13.750 1.4107 0.05275 0.04824 -0.0377 0.0046 1.0000
14.000 1.3962 0.05818 0.05394 -0.0365 0.0044 1.0000
14.250 1.3953 0.06125 0.05714 -0.0372 0.0043 1.0000
14.500 1.3923 0.06488 0.06091 -0.0379 0.0043 1.0000
14.750 1.3871 0.06900 0.06518 -0.0387 0.0042 1.0000
15.000 1.3805 0.07354 0.06989 -0.0400 0.0041 1.0000
15.250 1.3747 0.07809 0.07458 -0.0415 0.0040 1.0000
15.500 1.3626 0.08390 0.08056 -0.0434 0.0040 1.0000
15.750 1.3508 0.08987 0.08671 -0.0457 0.0040 1.0000
16.000 1.3411 0.09568 0.09266 -0.0483 0.0039 1.0000
16.250 1.3202 0.10387 0.10107 -0.0519 0.0039 1.0000
16.500 1.3086 0.11047 0.10781 -0.0553 0.0039 1.0000
16.750 1.2908 0.11868 0.11620 -0.0597 0.0039 1.0000
17.000 1.2710 0.12765 0.12533 -0.0647 0.0039 1.0000
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