GOE 11K AIRFOIL (goe11k-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 11K AIRFOIL (goe11k-il) Reynolds number: 100,000 Max Cl/Cd: 41.91 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe11k-il-100000.txt Download as CSV file: xf-goe11k-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 11K 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4018 0.10693 0.10218 -0.0302 1.0000 0.0857
-9.250 -0.4183 0.10483 0.10016 -0.0314 1.0000 0.0862
-9.000 -0.4340 0.10250 0.09790 -0.0322 1.0000 0.0864
-8.750 -0.3988 0.09622 0.09156 -0.0268 1.0000 0.0918
-8.500 -0.4026 0.09329 0.08867 -0.0260 1.0000 0.0947
-8.250 -0.4118 0.09048 0.08592 -0.0257 1.0000 0.0972
-8.000 -0.4299 0.08809 0.08360 -0.0259 1.0000 0.0991
-7.750 -0.5125 0.09339 0.08863 -0.0235 1.0000 0.0919
-7.500 -0.5236 0.09116 0.08647 -0.0218 1.0000 0.0935
-7.250 -0.5324 0.08841 0.08377 -0.0216 1.0000 0.0960
-7.000 -0.5462 0.08527 0.08064 -0.0248 1.0000 0.0993
-6.750 -0.5626 0.08267 0.07777 -0.0305 1.0000 0.1007
-6.500 -0.5515 0.07757 0.07294 -0.0246 1.0000 0.1030
-6.250 -0.5467 0.07491 0.07030 -0.0220 1.0000 0.1065
-6.000 -0.5507 0.07235 0.06723 -0.0284 1.0000 0.1150
-5.750 -0.5427 0.06723 0.06240 -0.0247 1.0000 0.1171
-5.500 -0.5351 0.06458 0.05978 -0.0222 1.0000 0.1216
-5.250 -0.5280 0.06066 0.05560 -0.0241 1.0000 0.1314
-5.000 -0.5180 0.05830 0.05296 -0.0244 1.0000 0.1448
-4.750 -0.5087 0.05515 0.05002 -0.0213 1.0000 0.1503
-4.500 -0.4972 0.05212 0.04683 -0.0209 1.0000 0.1633
-4.250 -0.4844 0.04933 0.04389 -0.0202 1.0000 0.1774
-4.000 -0.4710 0.04676 0.04122 -0.0191 1.0000 0.1931
-3.750 -0.4576 0.04469 0.03897 -0.0181 1.0000 0.2198
-3.500 -0.4110 0.03342 0.02563 -0.0200 1.0000 0.1029
-3.250 -0.3894 0.03077 0.02241 -0.0183 1.0000 0.0987
-3.000 -0.3694 0.02869 0.01991 -0.0168 1.0000 0.1028
-2.750 -0.3488 0.02715 0.01819 -0.0154 1.0000 0.1062
-2.500 -0.3272 0.02585 0.01653 -0.0140 1.0000 0.1103
-2.250 -0.3053 0.02478 0.01506 -0.0126 1.0000 0.1162
-2.000 -0.2836 0.02372 0.01394 -0.0115 1.0000 0.1207
-1.750 -0.2619 0.02320 0.01320 -0.0103 1.0000 0.1281
-1.500 -0.2395 0.02233 0.01227 -0.0093 1.0000 0.1328
-1.250 -0.2175 0.02180 0.01170 -0.0082 1.0000 0.1388
-1.000 -0.1956 0.02133 0.01119 -0.0071 1.0000 0.1468
-0.750 -0.1741 0.02091 0.01082 -0.0061 1.0000 0.1537
-0.500 -0.1528 0.02054 0.01048 -0.0049 1.0000 0.1615
-0.250 -0.1314 0.02028 0.01025 -0.0038 1.0000 0.1736
0.000 -0.0290 0.01804 0.01069 -0.0191 1.0000 1.0000
0.250 -0.0082 0.01833 0.01073 -0.0180 1.0000 1.0000
0.500 0.0126 0.01863 0.01086 -0.0171 1.0000 1.0000
0.750 0.0333 0.01895 0.01105 -0.0161 1.0000 1.0000
1.000 0.0540 0.01928 0.01129 -0.0153 1.0000 1.0000
1.250 0.0746 0.01964 0.01157 -0.0144 1.0000 1.0000
1.500 0.0952 0.02002 0.01187 -0.0136 1.0000 1.0000
1.750 0.1157 0.02041 0.01222 -0.0128 1.0000 1.0000
2.000 0.1360 0.02084 0.01262 -0.0120 1.0000 1.0000
2.250 0.1563 0.02128 0.01305 -0.0113 1.0000 1.0000
2.500 0.1764 0.02175 0.01352 -0.0106 1.0000 1.0000
2.750 0.2187 0.02266 0.01447 -0.0145 0.9919 1.0000
3.000 0.2643 0.02355 0.01543 -0.0189 0.9809 1.0000
3.250 0.3076 0.02427 0.01625 -0.0227 0.9695 1.0000
3.500 0.3565 0.02477 0.01687 -0.0274 0.9533 1.0000
3.750 0.4805 0.02331 0.01575 -0.0432 0.9039 1.0000
4.000 0.5641 0.02116 0.01394 -0.0508 0.8701 1.0000
4.250 0.6260 0.01912 0.01223 -0.0543 0.8414 1.0000
4.500 0.7208 0.01720 0.00765 -0.0595 0.2361 1.0000
4.750 0.7334 0.01876 0.00861 -0.0566 0.1757 1.0000
5.000 0.7505 0.01991 0.00957 -0.0545 0.1548 1.0000
5.250 0.7712 0.02100 0.01057 -0.0530 0.1375 1.0000
5.500 0.7966 0.02231 0.01180 -0.0526 0.1233 1.0000
5.750 0.8260 0.02382 0.01328 -0.0529 0.1095 1.0000
6.000 0.8584 0.02566 0.01509 -0.0537 0.0974 1.0000
6.250 0.8963 0.02838 0.01774 -0.0558 0.0874 1.0000
6.500 0.9187 0.02972 0.01949 -0.0541 0.0804 1.0000
6.750 0.9470 0.03232 0.02217 -0.0543 0.0749 1.0000
7.000 0.9690 0.03548 0.02578 -0.0528 0.0727 1.0000
7.250 0.9834 0.03749 0.02835 -0.0496 0.0697 1.0000
7.500 0.9968 0.04024 0.03156 -0.0465 0.0679 1.0000
7.750 1.0070 0.04380 0.03560 -0.0430 0.0688 1.0000
8.000 1.0147 0.04780 0.04000 -0.0395 0.0707 1.0000
8.250 1.0229 0.05269 0.04510 -0.0369 0.0729 1.0000
9.500 0.9932 0.08547 0.08005 -0.0183 0.1430 1.0000
9.750 0.9505 0.08688 0.08170 -0.0127 0.1424 1.0000
10.000 0.9160 0.08966 0.08457 -0.0089 0.1421 1.0000
10.250 0.8828 0.09374 0.08871 -0.0080 0.1419 1.0000
10.500 0.8532 0.09923 0.09422 -0.0102 0.1417 1.0000
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Polar data table (+)
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