GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 392 AIRFOIL (goe392-il) Reynolds number: 100,000 Max Cl/Cd: 59.27 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe392-il-100000.txt Download as CSV file: xf-goe392-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 392 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3569 0.09626 0.09232 -0.0298 1.0000 0.0664
-7.000 -0.3769 0.09567 0.09185 -0.0263 1.0000 0.0667
-6.750 -0.3955 0.09481 0.09109 -0.0238 1.0000 0.0673
-6.500 -0.4098 0.09341 0.08977 -0.0234 1.0000 0.0681
-6.250 -0.4105 0.09042 0.08682 -0.0330 0.9973 0.0697
-6.000 -0.3923 0.08506 0.08147 -0.0341 0.9922 0.0723
-5.750 -0.3662 0.08096 0.07728 -0.0384 0.9854 0.0790
-5.500 -0.3349 0.07429 0.07051 -0.0519 0.9755 0.0855
-5.250 -0.2968 0.06832 0.06425 -0.0659 0.9663 0.0977
-5.000 -0.2646 0.06396 0.05967 -0.0729 0.9588 0.1113
-4.750 -0.2485 0.06059 0.05647 -0.0715 0.9516 0.1267
-4.500 -0.2163 0.05708 0.05284 -0.0763 0.9452 0.1537
-4.250 -0.1974 0.05497 0.05080 -0.0749 0.9366 0.1731
-4.000 -0.1636 0.05186 0.04763 -0.0784 0.9313 0.2118
-3.750 -0.1416 0.04968 0.04539 -0.0791 0.9216 0.2507
-3.250 -0.0163 0.03356 0.02614 -0.0980 0.9102 0.0835
-3.000 0.0272 0.02974 0.02174 -0.1001 0.9061 0.0689
-2.750 0.0606 0.02833 0.01981 -0.1006 0.8977 0.0702
-2.500 0.1030 0.02587 0.01709 -0.1027 0.8931 0.0691
-2.250 0.1368 0.02443 0.01546 -0.1032 0.8855 0.0696
-2.000 0.1768 0.02275 0.01388 -0.1051 0.8802 0.0766
-1.750 0.2103 0.02180 0.01284 -0.1058 0.8726 0.0878
-1.500 0.2518 0.02064 0.01167 -0.1080 0.8670 0.1172
-1.250 0.2903 0.01805 0.01134 -0.1093 0.8643 0.6828
-1.000 0.3464 0.01734 0.01078 -0.1143 0.8567 1.0000
-0.750 0.3934 0.01700 0.01004 -0.1176 0.8515 1.0000
-0.500 0.4239 0.01702 0.00981 -0.1181 0.8412 1.0000
-0.250 0.4610 0.01688 0.00944 -0.1196 0.8329 1.0000
0.000 0.4997 0.01666 0.00901 -0.1214 0.8249 1.0000
0.250 0.5288 0.01670 0.00889 -0.1215 0.8139 1.0000
0.500 0.5601 0.01670 0.00875 -0.1219 0.8039 1.0000
0.750 0.5980 0.01653 0.00843 -0.1234 0.7961 1.0000
1.000 0.6230 0.01672 0.00854 -0.1228 0.7845 1.0000
1.250 0.6489 0.01690 0.00865 -0.1224 0.7735 1.0000
1.500 0.6769 0.01704 0.00872 -0.1223 0.7635 1.0000
1.750 0.7097 0.01704 0.00863 -0.1229 0.7550 1.0000
2.000 0.7328 0.01730 0.00888 -0.1220 0.7435 1.0000
2.250 0.7572 0.01755 0.00916 -0.1214 0.7327 1.0000
2.500 0.7839 0.01774 0.00933 -0.1211 0.7228 1.0000
2.750 0.8146 0.01781 0.00937 -0.1213 0.7141 1.0000
3.000 0.8371 0.01811 0.00973 -0.1204 0.7028 1.0000
3.250 0.8611 0.01839 0.01012 -0.1196 0.6920 1.0000
3.500 0.8875 0.01861 0.01039 -0.1192 0.6822 1.0000
3.750 0.9145 0.01811 0.00987 -0.1180 0.6625 1.0000
4.000 0.9381 0.01742 0.00909 -0.1157 0.6354 1.0000
4.250 0.9591 0.01688 0.00843 -0.1131 0.6048 1.0000
4.500 0.9746 0.01671 0.00830 -0.1099 0.5718 1.0000
4.750 0.9898 0.01670 0.00819 -0.1068 0.5342 1.0000
5.000 0.9986 0.01694 0.00821 -0.1026 0.4760 1.0000
5.250 1.0068 0.01755 0.00846 -0.0985 0.4020 1.0000
5.500 1.0097 0.01881 0.00906 -0.0941 0.3018 1.0000
5.750 0.9928 0.02202 0.01083 -0.0876 0.0689 1.0000
6.000 1.0049 0.02316 0.01195 -0.0848 0.0542 1.0000
6.250 1.0167 0.02421 0.01316 -0.0820 0.0497 1.0000
6.500 1.0248 0.02537 0.01450 -0.0787 0.0464 1.0000
6.750 1.0322 0.02652 0.01591 -0.0755 0.0437 1.0000
7.000 1.0365 0.02783 0.01743 -0.0719 0.0426 1.0000
7.250 1.0384 0.02929 0.01907 -0.0682 0.0423 1.0000
7.500 1.0391 0.03087 0.02080 -0.0647 0.0424 1.0000
7.750 1.0403 0.03255 0.02260 -0.0614 0.0426 1.0000
8.000 1.0454 0.03428 0.02438 -0.0585 0.0431 1.0000
8.250 1.0671 0.03590 0.02593 -0.0568 0.0443 1.0000
8.500 1.1778 0.03961 0.02941 -0.0658 0.0488 1.0000
8.750 1.2719 0.04622 0.03633 -0.0737 0.0587 1.0000
9.250 1.3841 0.05182 0.04396 -0.0713 0.1324 1.0000
9.500 1.3954 0.05467 0.04863 -0.0650 0.1872 1.0000
9.750 1.3676 0.05966 0.05452 -0.0592 0.2049 1.0000
10.000 1.3389 0.06618 0.06157 -0.0552 0.2215 1.0000
10.250 1.3034 0.06952 0.06514 -0.0501 0.2199 1.0000
10.500 1.2696 0.07377 0.06953 -0.0461 0.2208 1.0000
10.750 1.2370 0.07898 0.07485 -0.0440 0.2220 1.0000
11.000 1.2056 0.08505 0.08099 -0.0436 0.2229 1.0000
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Polar data table (+)
Polar graphs
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