GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: GOE 379 AIRFOIL (goe379-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.49 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe379-il-1000000-n5.txt Download as CSV file: xf-goe379-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 379 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2243 0.11672 0.11521 -0.0279 1.0000 0.0036
-10.750 -0.2209 0.11356 0.11206 -0.0283 1.0000 0.0035
-10.500 -0.3163 0.12376 0.12212 -0.0211 1.0000 0.0035
-10.250 -0.3103 0.12087 0.11923 -0.0220 1.0000 0.0035
-10.000 -0.3090 0.11683 0.11521 -0.0224 1.0000 0.0030
-9.750 -0.3046 0.11391 0.11231 -0.0231 1.0000 0.0023
-9.250 -0.2945 0.10782 0.10625 -0.0246 1.0000 0.0028
-9.000 -0.2875 0.10508 0.10353 -0.0254 1.0000 0.0034
-8.750 -0.2809 0.10307 0.10153 -0.0262 1.0000 0.0036
-8.500 -0.2719 0.10021 0.09869 -0.0278 0.9926 0.0037
-8.250 -0.2557 0.09755 0.09603 -0.0319 0.9817 0.0039
-8.000 -0.2357 0.09348 0.09194 -0.0372 0.9702 0.0039
-7.750 -0.2082 0.08828 0.08672 -0.0447 0.9599 0.0038
-7.500 -0.1734 0.08351 0.08190 -0.0546 0.9466 0.0039
-7.250 -0.1426 0.07851 0.07680 -0.0637 0.9199 0.0039
-7.000 -0.1280 0.07544 0.07361 -0.0670 0.8898 0.0039
-6.750 -0.1191 0.07265 0.07072 -0.0686 0.8645 0.0039
-6.500 -0.1100 0.06980 0.06778 -0.0700 0.8445 0.0039
-6.250 -0.1056 0.06525 0.06317 -0.0713 0.8282 0.0036
-6.000 -0.0957 0.06177 0.05960 -0.0733 0.8106 0.0034
-5.750 -0.0822 0.05871 0.05646 -0.0754 0.7938 0.0033
-5.500 -0.0667 0.05528 0.05294 -0.0778 0.7787 0.0032
-5.250 -0.0490 0.05183 0.04939 -0.0803 0.7634 0.0031
-5.000 -0.0295 0.04839 0.04584 -0.0826 0.7458 0.0030
-4.750 -0.0080 0.04498 0.04229 -0.0848 0.7323 0.0030
-4.500 0.0155 0.04057 0.03773 -0.0873 0.7200 0.0029
-4.250 0.0402 0.03594 0.03292 -0.0893 0.7091 0.0029
-4.000 0.0638 0.02372 0.02015 -0.0908 0.7026 0.0040
-3.750 0.0886 0.02315 0.01948 -0.0907 0.6903 0.0041
-3.500 0.1139 0.02342 0.01968 -0.0907 0.6764 0.0044
-3.250 0.1386 0.02276 0.01891 -0.0906 0.6631 0.0049
-3.000 0.1630 0.02065 0.01658 -0.0900 0.6509 0.0060
-2.750 0.1873 0.01860 0.01429 -0.0892 0.6374 0.0083
-2.500 0.2016 0.00439 0.00019 -0.0837 0.6019 0.0104
-2.000 0.2645 0.01788 0.01322 -0.0883 0.5893 0.0183
0.000 0.4637 0.00894 0.00242 -0.0821 0.4989 0.0175
0.250 0.4888 0.00857 0.00188 -0.0813 0.4864 0.0159
0.750 0.5404 0.00834 0.00142 -0.0802 0.4620 0.0131
1.000 0.5664 0.00832 0.00134 -0.0798 0.4496 0.0124
1.250 0.5923 0.00832 0.00128 -0.0794 0.4363 0.0119
1.500 0.6180 0.00833 0.00123 -0.0790 0.4227 0.0116
1.750 0.6438 0.00836 0.00119 -0.0785 0.4087 0.0115
2.000 0.6695 0.00842 0.00115 -0.0781 0.3954 0.0119
2.250 0.6953 0.00848 0.00116 -0.0777 0.3831 0.0166
2.500 0.7207 0.00854 0.00124 -0.0773 0.3702 0.0470
2.750 0.7462 0.00862 0.00135 -0.0770 0.3585 0.0645
3.250 0.7857 0.00763 0.00171 -0.0742 0.3434 0.7370
3.500 0.8861 0.00741 0.00195 -0.0912 0.3274 1.0000
3.750 0.9108 0.00755 0.00206 -0.0907 0.3206 1.0000
4.000 0.9355 0.00770 0.00221 -0.0901 0.3120 1.0000
4.250 0.9563 0.00817 0.00243 -0.0890 0.2667 1.0000
4.500 0.9724 0.00907 0.00285 -0.0871 0.1809 1.0000
4.750 0.9887 0.00995 0.00336 -0.0852 0.1125 1.0000
5.000 1.0011 0.01125 0.00419 -0.0826 0.0054 1.0000
5.250 1.0243 0.01150 0.00446 -0.0818 0.0039 1.0000
5.500 1.0473 0.01178 0.00477 -0.0809 0.0027 1.0000
5.750 1.0695 0.01211 0.00517 -0.0799 0.0022 1.0000
6.000 1.0919 0.01242 0.00555 -0.0790 0.0017 1.0000
6.250 1.1129 0.01286 0.00606 -0.0778 0.0015 1.0000
6.500 1.1332 0.01335 0.00661 -0.0764 0.0014 1.0000
6.750 1.1524 0.01393 0.00728 -0.0749 0.0014 1.0000
7.000 1.1709 0.01456 0.00799 -0.0733 0.0014 1.0000
7.250 1.1874 0.01532 0.00885 -0.0713 0.0014 1.0000
7.500 1.2021 0.01620 0.00982 -0.0690 0.0014 1.0000
7.750 1.2151 0.01714 0.01086 -0.0665 0.0014 1.0000
8.000 1.2255 0.01822 0.01204 -0.0636 0.0014 1.0000
8.250 1.2361 0.01921 0.01311 -0.0609 0.0014 1.0000
8.500 1.2432 0.02042 0.01440 -0.0575 0.0014 1.0000
8.750 1.2473 0.02156 0.01562 -0.0536 0.0015 1.0000
9.000 1.2488 0.02302 0.01717 -0.0494 0.0015 1.0000
9.250 1.2551 0.02435 0.01859 -0.0464 0.0015 1.0000
9.500 1.2624 0.02583 0.02016 -0.0436 0.0016 1.0000
9.750 1.2709 0.02757 0.02201 -0.0411 0.0016 1.0000
10.000 1.2808 0.02941 0.02406 -0.0389 0.0017 1.0000
10.250 1.2917 0.03183 0.02665 -0.0369 0.0017 1.0000
10.500 1.3006 0.03416 0.02914 -0.0348 0.0018 1.0000
10.750 1.3060 0.03692 0.03209 -0.0324 0.0019 1.0000
11.000 1.3051 0.04365 0.03918 -0.0299 0.0022 1.0000
11.250 1.2997 0.04622 0.04193 -0.0271 0.0022 1.0000
11.500 1.2912 0.04908 0.04496 -0.0244 0.0022 1.0000
11.750 1.2821 0.05181 0.04786 -0.0223 0.0022 1.0000
12.000 1.2704 0.05527 0.05149 -0.0206 0.0022 1.0000
12.250 1.2579 0.05871 0.05509 -0.0195 0.0022 1.0000
12.500 1.2444 0.06258 0.05913 -0.0189 0.0022 1.0000
12.750 1.2308 0.06668 0.06338 -0.0190 0.0022 1.0000
13.000 1.2152 0.07130 0.06816 -0.0196 0.0022 1.0000
13.250 1.2011 0.07583 0.07283 -0.0209 0.0022 1.0000
13.500 1.1855 0.08113 0.07827 -0.0226 0.0022 1.0000
13.750 1.1693 0.08683 0.08410 -0.0248 0.0022 1.0000
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Polar data table (+)
Polar graphs
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