GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 423 AIRFOIL (goe423-il) Reynolds number: 100,000 Max Cl/Cd: 40.21 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe423-il-100000-n5.txt Download as CSV file: xf-goe423-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 423 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2348 0.07618 0.07049 -0.1060 0.9277 0.0698
-9.750 -0.2716 0.06467 0.05887 -0.1159 0.9116 0.0696
-9.500 -0.3202 0.05670 0.05057 -0.1179 0.8931 0.0696
-9.250 -0.3505 0.05077 0.04417 -0.1170 0.8774 0.0699
-9.000 -0.3456 0.04807 0.04129 -0.1162 0.8653 0.0704
-8.750 -0.3314 0.04573 0.03878 -0.1162 0.8556 0.0709
-8.500 -0.3247 0.04332 0.03613 -0.1148 0.8417 0.0713
-8.250 -0.3140 0.04101 0.03354 -0.1138 0.8292 0.0718
-8.000 -0.2985 0.03876 0.03098 -0.1132 0.8185 0.0724
-7.750 -0.2839 0.03703 0.02899 -0.1121 0.8050 0.0733
-7.500 -0.2679 0.03529 0.02696 -0.1110 0.7921 0.0745
-7.250 -0.2497 0.03347 0.02475 -0.1102 0.7807 0.0757
-7.000 -0.2319 0.03180 0.02270 -0.1091 0.7677 0.0767
-6.750 -0.2124 0.03030 0.02083 -0.1081 0.7552 0.0775
-6.500 -0.1899 0.02894 0.01906 -0.1074 0.7442 0.0783
-6.250 -0.1667 0.02790 0.01786 -0.1069 0.7327 0.0792
-6.000 -0.1422 0.02715 0.01701 -0.1066 0.7225 0.0805
-5.750 -0.1169 0.02643 0.01614 -0.1063 0.7134 0.0821
-5.500 -0.0921 0.02572 0.01527 -0.1059 0.7050 0.0837
-5.250 -0.0664 0.02497 0.01432 -0.1056 0.6976 0.0853
-5.000 -0.0400 0.02426 0.01340 -0.1054 0.6912 0.0867
-4.750 -0.0144 0.02366 0.01263 -0.1050 0.6845 0.0882
-4.500 0.0119 0.02311 0.01207 -0.1049 0.6789 0.0900
-4.250 0.0381 0.02270 0.01161 -0.1048 0.6737 0.0925
-4.000 0.0634 0.02233 0.01117 -0.1044 0.6680 0.0952
-3.750 0.0897 0.02193 0.01066 -0.1041 0.6630 0.0980
-3.500 0.1166 0.02153 0.01020 -0.1040 0.6589 0.1005
-3.250 0.1414 0.02126 0.00994 -0.1036 0.6543 0.1038
-3.000 0.1666 0.02103 0.00968 -0.1032 0.6500 0.1085
-2.750 0.1920 0.02079 0.00944 -0.1029 0.6462 0.1139
-2.500 0.2184 0.02059 0.00920 -0.1027 0.6429 0.1211
-2.250 0.2454 0.02036 0.00895 -0.1026 0.6401 0.1298
-2.000 0.2695 0.02019 0.00884 -0.1020 0.6367 0.1426
-1.750 0.2936 0.02002 0.00874 -0.1015 0.6332 0.1609
-1.500 0.3183 0.01984 0.00865 -0.1011 0.6298 0.1855
-1.250 0.3437 0.01964 0.00860 -0.1009 0.6267 0.2220
-1.000 0.3697 0.01940 0.00855 -0.1008 0.6238 0.2831
-0.750 0.3955 0.01898 0.00853 -0.1007 0.6214 0.3873
-0.500 0.4154 0.01849 0.00878 -0.0992 0.6188 0.5881
-0.250 0.4525 0.01818 0.00931 -0.0999 0.6160 0.8197
0.250 0.5636 0.01878 0.00983 -0.1103 0.6106 0.9635
0.500 0.6207 0.01901 0.00992 -0.1165 0.6081 0.9886
0.750 0.6673 0.01917 0.00995 -0.1207 0.6057 1.0000
1.000 0.6900 0.01937 0.01003 -0.1200 0.6035 1.0000
1.250 0.7127 0.01961 0.01017 -0.1193 0.6014 1.0000
1.500 0.7292 0.01995 0.01052 -0.1176 0.5988 1.0000
1.750 0.7466 0.02030 0.01087 -0.1160 0.5963 1.0000
2.000 0.7648 0.02066 0.01122 -0.1146 0.5939 1.0000
2.250 0.7838 0.02101 0.01156 -0.1132 0.5915 1.0000
2.500 0.8039 0.02134 0.01185 -0.1120 0.5891 1.0000
2.750 0.8258 0.02164 0.01212 -0.1111 0.5868 1.0000
3.000 0.8492 0.02195 0.01237 -0.1105 0.5848 1.0000
3.250 0.8736 0.02228 0.01265 -0.1101 0.5832 1.0000
3.500 0.8907 0.02277 0.01318 -0.1084 0.5810 1.0000
3.750 0.9012 0.02339 0.01387 -0.1057 0.5779 1.0000
4.000 0.9146 0.02395 0.01449 -0.1034 0.5748 1.0000
4.250 0.9310 0.02448 0.01506 -0.1017 0.5721 1.0000
4.500 0.9504 0.02493 0.01552 -0.1004 0.5695 1.0000
4.750 0.9731 0.02529 0.01588 -0.0997 0.5671 1.0000
5.000 0.9996 0.02557 0.01614 -0.0996 0.5649 1.0000
5.250 1.0196 0.02602 0.01661 -0.0984 0.5619 1.0000
5.500 1.0174 0.02701 0.01774 -0.0938 0.5564 1.0000
5.750 1.0320 0.02753 0.01831 -0.0917 0.5521 1.0000
6.000 1.0560 0.02778 0.01858 -0.0912 0.5488 1.0000
6.250 1.0861 0.02787 0.01867 -0.0916 0.5461 1.0000
6.500 1.1042 0.02837 0.01921 -0.0902 0.5427 1.0000
6.750 1.0895 0.02987 0.02089 -0.0840 0.5364 1.0000
7.000 1.1049 0.03036 0.02144 -0.0822 0.5321 1.0000
7.250 1.1426 0.02991 0.02097 -0.0835 0.5283 1.0000
7.500 1.1498 0.03048 0.02161 -0.0804 0.5225 1.0000
7.750 1.1329 0.03193 0.02318 -0.0740 0.5154 1.0000
8.000 1.1976 0.02978 0.02092 -0.0784 0.5088 1.0000
8.250 1.1603 0.03223 0.02355 -0.0696 0.5014 1.0000
8.500 1.1826 0.03189 0.02324 -0.0685 0.4941 1.0000
8.750 1.1944 0.03225 0.02366 -0.0663 0.4875 1.0000
9.000 1.1734 0.03461 0.02615 -0.0611 0.4789 1.0000
9.250 1.2205 0.03286 0.02437 -0.0624 0.4734 1.0000
9.500 1.1604 0.03839 0.03012 -0.0549 0.4618 1.0000
9.750 1.1368 0.04220 0.03403 -0.0516 0.4508 1.0000
10.000 1.1549 0.04236 0.03424 -0.0506 0.4431 1.0000
11.000 1.1306 0.05381 0.04602 -0.0447 0.3947 1.0000
11.250 1.1306 0.05619 0.04846 -0.0437 0.3803 1.0000
11.500 1.1382 0.05768 0.04999 -0.0428 0.3661 1.0000
11.750 1.1539 0.05814 0.05044 -0.0419 0.3507 1.0000
12.000 1.1764 0.05766 0.04985 -0.0409 0.3312 1.0000
12.250 1.1887 0.05850 0.05061 -0.0398 0.3122 1.0000
12.500 1.1956 0.05988 0.05183 -0.0386 0.2879 1.0000
12.750 1.1946 0.06229 0.05409 -0.0374 0.2623 1.0000
13.000 1.1892 0.06530 0.05695 -0.0364 0.2350 1.0000
13.250 1.1812 0.06876 0.06025 -0.0355 0.2043 1.0000
13.500 1.1683 0.07287 0.06410 -0.0347 0.1611 1.0000
13.750 1.1478 0.07796 0.06881 -0.0341 0.1222 1.0000
14.000 1.1369 0.08215 0.07283 -0.0337 0.1009 1.0000
14.250 1.1310 0.08586 0.07646 -0.0334 0.0855 1.0000
14.500 1.1275 0.08935 0.07992 -0.0333 0.0764 1.0000
14.750 1.1254 0.09272 0.08330 -0.0333 0.0714 1.0000
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Polar data table (+)
Polar graphs
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