GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 614 AIRFOIL (goe614-il) Reynolds number: 100,000 Max Cl/Cd: 33.6 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe614-il-100000.txt Download as CSV file: xf-goe614-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 614 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0212 0.10251 0.09788 -0.0917 0.9156 0.1573
-8.500 -0.2074 0.07198 0.06731 -0.1107 0.8953 0.0899
-8.250 -0.1989 0.06555 0.06080 -0.1171 0.8902 0.0884
-8.000 -0.2476 0.05766 0.05261 -0.1190 0.8739 0.0858
-7.750 -0.2921 0.05062 0.04494 -0.1178 0.8583 0.0836
-7.500 -0.3016 0.04651 0.04027 -0.1162 0.8464 0.0829
-7.250 -0.2759 0.04355 0.03696 -0.1178 0.8404 0.0840
-7.000 -0.2394 0.04035 0.03332 -0.1207 0.8374 0.0853
-6.750 -0.2371 0.03919 0.03192 -0.1173 0.8239 0.0859
-6.500 -0.1969 0.03650 0.02881 -0.1197 0.8208 0.0871
-6.250 -0.1869 0.03554 0.02761 -0.1170 0.8088 0.0881
-6.000 -0.1459 0.03354 0.02523 -0.1190 0.8048 0.0899
-5.750 -0.0973 0.03167 0.02342 -0.1223 0.8023 0.0934
-5.500 -0.0868 0.03126 0.02295 -0.1193 0.7903 0.0958
-5.250 -0.0413 0.02972 0.02125 -0.1219 0.7863 0.1020
-5.000 0.0086 0.02819 0.01965 -0.1253 0.7835 0.1128
-4.750 0.0156 0.02785 0.01947 -0.1218 0.7713 0.1211
-4.500 0.0554 0.02637 0.01819 -0.1236 0.7669 0.1555
-4.250 0.1065 0.02584 0.01760 -0.1270 0.7637 0.2036
-4.000 0.1110 0.02632 0.01805 -0.1229 0.7505 0.2174
-3.750 0.1593 0.02592 0.01757 -0.1260 0.7466 0.2423
-3.500 0.1683 0.02629 0.01790 -0.1227 0.7350 0.2543
-3.250 0.2097 0.02584 0.01738 -0.1246 0.7299 0.2727
-3.000 0.2383 0.02568 0.01721 -0.1245 0.7227 0.2878
-2.750 0.2596 0.02565 0.01716 -0.1232 0.7137 0.3028
-2.500 0.3057 0.02510 0.01653 -0.1259 0.7093 0.3255
-2.250 0.3109 0.02555 0.01698 -0.1220 0.6985 0.3387
-2.000 0.3488 0.02523 0.01664 -0.1233 0.6931 0.3607
-1.750 0.3746 0.02524 0.01659 -0.1228 0.6864 0.3783
-1.500 0.3912 0.02543 0.01676 -0.1208 0.6779 0.3930
-1.250 0.4339 0.02492 0.01617 -0.1229 0.6733 0.4115
-1.000 0.4416 0.02535 0.01666 -0.1195 0.6644 0.4223
-0.750 0.4715 0.02519 0.01645 -0.1197 0.6582 0.4394
-0.500 0.5138 0.02480 0.01599 -0.1219 0.6541 0.4613
-0.250 0.5122 0.02560 0.01685 -0.1171 0.6452 0.4756
0.000 0.5424 0.02545 0.01675 -0.1172 0.6397 0.4987
0.250 0.5856 0.02500 0.01627 -0.1195 0.6357 0.5306
0.500 0.5795 0.02589 0.01734 -0.1140 0.6270 0.5483
0.750 0.6068 0.02580 0.01734 -0.1137 0.6218 0.5829
1.000 0.6484 0.02534 0.01692 -0.1156 0.6181 0.6317
1.250 0.6458 0.02619 0.01803 -0.1108 0.6106 0.6670
1.500 0.6665 0.02618 0.01830 -0.1093 0.6048 0.7404
1.750 0.7888 0.02522 0.01745 -0.1267 0.6003 1.0000
2.000 0.7916 0.02622 0.01837 -0.1230 0.5941 1.0000
2.250 0.7990 0.02704 0.01911 -0.1199 0.5877 1.0000
2.500 0.8373 0.02702 0.01888 -0.1215 0.5833 1.0000
2.750 0.8713 0.02724 0.01892 -0.1226 0.5790 1.0000
3.000 0.8476 0.02893 0.02071 -0.1147 0.5710 1.0000
3.250 0.8857 0.02877 0.02039 -0.1161 0.5660 1.0000
3.500 0.9459 0.02816 0.01949 -0.1211 0.5621 1.0000
3.750 0.9015 0.03042 0.02196 -0.1100 0.5534 1.0000
4.000 0.9379 0.03028 0.02168 -0.1112 0.5483 1.0000
4.250 0.9970 0.02967 0.02084 -0.1160 0.5445 1.0000
4.500 0.9438 0.03234 0.02373 -0.1039 0.5364 1.0000
4.750 0.9658 0.03272 0.02405 -0.1030 0.5313 1.0000
5.000 1.0288 0.03191 0.02305 -0.1082 0.5276 1.0000
5.250 0.9731 0.03486 0.02617 -0.0962 0.5201 1.0000
5.500 0.9669 0.03635 0.02768 -0.0917 0.5136 1.0000
5.750 1.0473 0.03446 0.02559 -0.0986 0.5104 1.0000
6.000 1.0750 0.03466 0.02572 -0.0985 0.5051 1.0000
6.250 0.9591 0.04124 0.03259 -0.0813 0.4940 1.0000
6.500 1.0745 0.03672 0.02782 -0.0907 0.4925 1.0000
6.750 1.1508 0.03512 0.02603 -0.0971 0.4882 1.0000
7.000 0.9109 0.05060 0.04203 -0.0708 0.4691 1.0000
7.250 0.9863 0.04639 0.03771 -0.0732 0.4686 1.0000
7.500 1.1016 0.04066 0.03177 -0.0804 0.4685 1.0000
7.750 1.0164 0.04767 0.03896 -0.0706 0.4563 1.0000
8.000 1.1098 0.04309 0.03423 -0.0754 0.4561 1.0000
8.250 1.2039 0.03986 0.03083 -0.0822 0.4545 1.0000
8.500 1.0261 0.05313 0.04445 -0.0654 0.4371 1.0000
8.750 1.1001 0.04917 0.04041 -0.0677 0.4371 1.0000
9.000 1.1821 0.04556 0.03670 -0.0716 0.4366 1.0000
9.250 0.7821 0.09037 0.08205 -0.0603 0.3861 1.0000
9.500 0.7203 0.10191 0.09369 -0.0614 0.3774 1.0000
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Polar data table (+)
Polar graphs
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