GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.88 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe371-il-1000000-n5.txt Download as CSV file: xf-goe371-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3403 0.10309 0.10145 -0.0268 1.0000 0.0039
-9.250 -0.3359 0.10049 0.09887 -0.0273 1.0000 0.0041
-9.000 -0.3352 0.09709 0.09550 -0.0278 1.0000 0.0040
-8.750 -0.3274 0.09350 0.09192 -0.0302 0.9992 0.0040
-8.500 -0.3170 0.08997 0.08840 -0.0329 0.9917 0.0043
-8.250 -0.3057 0.08583 0.08426 -0.0368 0.9839 0.0045
-8.000 -0.2905 0.08106 0.07948 -0.0424 0.9742 0.0047
-7.750 -0.2680 0.07434 0.07274 -0.0524 0.9632 0.0050
-7.500 -0.2382 0.06482 0.06317 -0.0684 0.9442 0.0054
-7.250 -0.2101 0.06156 0.05981 -0.0749 0.9211 0.0057
-7.000 -0.1957 0.05717 0.05528 -0.0800 0.8891 0.0059
-6.750 -0.1826 0.05305 0.05101 -0.0839 0.8600 0.0062
-6.500 -0.1687 0.04664 0.04442 -0.0899 0.8368 0.0068
-6.250 -0.1760 0.01430 0.01012 -0.1039 0.8185 0.0095
-6.000 -0.1554 0.01154 0.00681 -0.1032 0.8062 0.0109
-5.500 -0.1000 0.01236 0.00770 -0.1028 0.7846 0.0128
-5.250 -0.0755 0.01109 0.00612 -0.1023 0.7763 0.0146
-5.000 -0.0485 0.01097 0.00593 -0.1021 0.7683 0.0152
-4.750 -0.0208 0.01128 0.00624 -0.1019 0.7605 0.0157
-4.500 0.0068 0.01157 0.00653 -0.1018 0.7528 0.0163
-4.250 0.0341 0.01154 0.00644 -0.1016 0.7469 0.0173
-4.000 0.0608 0.01116 0.00593 -0.1013 0.7405 0.0185
-3.750 0.0878 0.01092 0.00557 -0.1011 0.7344 0.0195
-3.500 0.1151 0.01080 0.00538 -0.1009 0.7281 0.0201
-3.000 0.1681 0.00985 0.00421 -0.1003 0.7145 0.0215
-2.750 0.1949 0.00953 0.00385 -0.1001 0.7081 0.0220
-2.500 0.2220 0.00933 0.00361 -0.0999 0.7026 0.0227
-2.250 0.2492 0.00915 0.00339 -0.0997 0.6963 0.0234
-2.000 0.2761 0.00890 0.00308 -0.0994 0.6902 0.0240
-1.750 0.3032 0.00865 0.00279 -0.0992 0.6830 0.0245
-1.500 0.3301 0.00844 0.00252 -0.0989 0.6748 0.0249
-1.250 0.3569 0.00823 0.00226 -0.0986 0.6643 0.0252
-1.000 0.3836 0.00806 0.00203 -0.0983 0.6513 0.0254
-0.750 0.4098 0.00793 0.00181 -0.0979 0.6313 0.0256
-0.500 0.4347 0.00795 0.00166 -0.0972 0.5874 0.0260
-0.250 0.4588 0.00809 0.00157 -0.0965 0.5371 0.0262
0.000 0.4839 0.00815 0.00147 -0.0959 0.5066 0.0263
0.250 0.5098 0.00817 0.00139 -0.0955 0.4872 0.0264
0.500 0.5362 0.00817 0.00132 -0.0951 0.4725 0.0266
0.750 0.5627 0.00818 0.00127 -0.0948 0.4595 0.0270
1.000 0.5894 0.00820 0.00125 -0.0945 0.4481 0.0275
1.250 0.6160 0.00824 0.00125 -0.0943 0.4377 0.0281
1.500 0.6426 0.00829 0.00127 -0.0940 0.4279 0.0287
1.750 0.6694 0.00830 0.00124 -0.0937 0.4190 0.0307
2.000 0.6960 0.00836 0.00127 -0.0935 0.4104 0.0320
2.250 0.7228 0.00840 0.00131 -0.0932 0.4027 0.0335
2.500 0.7495 0.00847 0.00136 -0.0930 0.3948 0.0349
2.750 0.7761 0.00853 0.00142 -0.0927 0.3864 0.0372
3.000 0.8004 0.00801 0.00164 -0.0923 0.3798 0.4142
3.500 0.8644 0.00717 0.00196 -0.0947 0.3481 1.0000
3.750 0.8897 0.00736 0.00208 -0.0942 0.3292 1.0000
4.000 0.9134 0.00771 0.00225 -0.0935 0.2918 1.0000
4.250 0.9353 0.00823 0.00252 -0.0925 0.2424 1.0000
4.500 0.9587 0.00862 0.00277 -0.0918 0.2133 1.0000
4.750 0.9829 0.00893 0.00299 -0.0912 0.1951 1.0000
5.000 1.0072 0.00923 0.00322 -0.0906 0.1774 1.0000
5.250 1.0315 0.00952 0.00344 -0.0900 0.1627 1.0000
5.500 1.0558 0.00981 0.00367 -0.0894 0.1486 1.0000
5.750 1.0799 0.01012 0.00391 -0.0888 0.1338 1.0000
6.000 1.1029 0.01052 0.00420 -0.0880 0.1122 1.0000
6.250 1.1230 0.01120 0.00465 -0.0869 0.0729 1.0000
6.500 1.1449 0.01171 0.00506 -0.0859 0.0535 1.0000
6.750 1.1670 0.01217 0.00546 -0.0851 0.0398 1.0000
7.000 1.1865 0.01289 0.00603 -0.0838 0.0148 1.0000
7.250 1.2089 0.01331 0.00646 -0.0829 0.0113 1.0000
7.500 1.2315 0.01370 0.00688 -0.0820 0.0093 1.0000
7.750 1.2541 0.01406 0.00729 -0.0812 0.0083 1.0000
8.000 1.2759 0.01449 0.00774 -0.0803 0.0074 1.0000
8.250 1.2966 0.01502 0.00830 -0.0792 0.0063 1.0000
8.500 1.3182 0.01542 0.00875 -0.0783 0.0060 1.0000
8.750 1.3393 0.01585 0.00922 -0.0773 0.0054 1.0000
9.000 1.3596 0.01634 0.00974 -0.0762 0.0049 1.0000
9.250 1.3785 0.01692 0.01037 -0.0748 0.0045 1.0000
9.500 1.3961 0.01759 0.01111 -0.0733 0.0042 1.0000
9.750 1.4146 0.01814 0.01172 -0.0719 0.0041 1.0000
10.000 1.4323 0.01871 0.01235 -0.0704 0.0038 1.0000
10.250 1.4485 0.01935 0.01306 -0.0688 0.0036 1.0000
10.500 1.4625 0.02000 0.01378 -0.0667 0.0035 1.0000
10.750 1.4754 0.02062 0.01445 -0.0644 0.0033 1.0000
11.000 1.4871 0.02131 0.01522 -0.0620 0.0031 1.0000
11.250 1.4983 0.02204 0.01600 -0.0597 0.0030 1.0000
11.500 1.5059 0.02303 0.01708 -0.0570 0.0028 1.0000
11.750 1.5101 0.02428 0.01843 -0.0540 0.0026 1.0000
12.000 1.5195 0.02521 0.01944 -0.0519 0.0026 1.0000
12.250 1.5266 0.02634 0.02066 -0.0497 0.0025 1.0000
12.500 1.5312 0.02772 0.02215 -0.0474 0.0025 1.0000
12.750 1.5395 0.02887 0.02339 -0.0457 0.0024 1.0000
13.000 1.5418 0.03056 0.02519 -0.0437 0.0024 1.0000
13.250 1.5452 0.03226 0.02699 -0.0420 0.0023 1.0000
13.500 1.5478 0.03413 0.02898 -0.0405 0.0022 1.0000
13.750 1.5465 0.03648 0.03146 -0.0391 0.0022 1.0000
14.000 1.5470 0.03878 0.03387 -0.0380 0.0021 1.0000
14.250 1.5452 0.04143 0.03663 -0.0372 0.0021 1.0000
14.500 1.5449 0.04404 0.03935 -0.0366 0.0020 1.0000
14.750 1.5400 0.04729 0.04273 -0.0363 0.0020 1.0000
15.000 1.5331 0.05098 0.04654 -0.0363 0.0020 1.0000
15.250 1.5343 0.05381 0.04946 -0.0365 0.0019 1.0000
15.500 1.5209 0.05882 0.05463 -0.0374 0.0019 1.0000
15.750 1.5127 0.06342 0.05936 -0.0387 0.0019 1.0000
16.000 1.5062 0.06801 0.06407 -0.0402 0.0019 1.0000
16.250 1.4963 0.07332 0.06950 -0.0421 0.0018 1.0000
16.500 1.4820 0.07954 0.07587 -0.0445 0.0018 1.0000
16.750 1.4742 0.08483 0.08126 -0.0468 0.0018 1.0000
17.000 1.4551 0.09223 0.08882 -0.0500 0.0018 1.0000
17.250 1.4451 0.09817 0.09486 -0.0527 0.0018 1.0000
17.500 1.4250 0.10622 0.10306 -0.0565 0.0018 1.0000
17.750 1.4072 0.11407 0.11105 -0.0604 0.0018 1.0000
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Polar data table (+)
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