GOE 414 AIRFOIL (goe414-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 414 AIRFOIL (goe414-il) Reynolds number: 100,000 Max Cl/Cd: 54.64 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe414-il-100000-n5.txt Download as CSV file: xf-goe414-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 414 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2849 0.09268 0.08810 -0.0671 0.9780 0.0347
-9.250 -0.2829 0.08651 0.08195 -0.0724 0.9727 0.0348
-9.000 -0.2857 0.07989 0.07536 -0.0780 0.9652 0.0348
-8.750 -0.2962 0.07258 0.06809 -0.0842 0.9551 0.0348
-8.500 -0.3166 0.05869 0.05409 -0.0980 0.9421 0.0346
-8.250 -0.3373 0.04568 0.04036 -0.1081 0.9299 0.0347
-8.000 -0.3257 0.04177 0.03614 -0.1100 0.9225 0.0362
-7.750 -0.2987 0.03974 0.03393 -0.1124 0.9191 0.0384
-7.500 -0.2905 0.03668 0.03043 -0.1116 0.9094 0.0400
-7.250 -0.2676 0.03297 0.02605 -0.1132 0.9051 0.0423
-7.000 -0.2508 0.03071 0.02330 -0.1124 0.8971 0.0449
-6.750 -0.2220 0.02968 0.02221 -0.1133 0.8923 0.0476
-6.500 -0.1935 0.02823 0.02044 -0.1139 0.8874 0.0506
-6.250 -0.1701 0.02684 0.01863 -0.1134 0.8796 0.0544
-6.000 -0.1369 0.02587 0.01762 -0.1147 0.8755 0.0577
-5.750 -0.1143 0.02503 0.01659 -0.1138 0.8664 0.0612
-5.500 -0.0814 0.02398 0.01529 -0.1147 0.8616 0.0668
-5.250 -0.0576 0.02335 0.01458 -0.1140 0.8526 0.0716
-5.000 -0.0257 0.02233 0.01333 -0.1146 0.8474 0.0789
-4.750 -0.0015 0.02175 0.01272 -0.1139 0.8383 0.0871
-4.500 0.0304 0.02109 0.01195 -0.1146 0.8324 0.1000
-4.250 0.0549 0.02066 0.01140 -0.1139 0.8226 0.1113
-4.000 0.0873 0.02012 0.01068 -0.1146 0.8168 0.1225
-3.750 0.1108 0.01983 0.01035 -0.1138 0.8069 0.1319
-3.500 0.1417 0.01941 0.00986 -0.1143 0.8012 0.1450
-3.250 0.1658 0.01918 0.00960 -0.1137 0.7916 0.1582
-3.000 0.1950 0.01879 0.00915 -0.1139 0.7847 0.1705
-2.750 0.2209 0.01848 0.00879 -0.1134 0.7756 0.1814
-2.500 0.2481 0.01814 0.00846 -0.1133 0.7675 0.1942
-2.250 0.2756 0.01784 0.00817 -0.1131 0.7593 0.2138
-2.000 0.3017 0.01759 0.00798 -0.1128 0.7505 0.2409
-1.750 0.3305 0.01730 0.00773 -0.1129 0.7428 0.2775
-1.500 0.3560 0.01714 0.00762 -0.1124 0.7330 0.3151
-1.250 0.3847 0.01691 0.00739 -0.1125 0.7248 0.3547
-1.000 0.4111 0.01672 0.00725 -0.1122 0.7150 0.3966
-0.750 0.4372 0.01647 0.00713 -0.1119 0.7054 0.4508
-0.500 0.4633 0.01594 0.00697 -0.1114 0.6972 0.5630
-0.250 0.5253 0.01514 0.00698 -0.1174 0.6870 1.0000
0.000 0.5511 0.01522 0.00686 -0.1170 0.6777 1.0000
0.250 0.5774 0.01529 0.00674 -0.1166 0.6686 1.0000
0.500 0.6018 0.01543 0.00673 -0.1160 0.6584 1.0000
0.750 0.6279 0.01554 0.00667 -0.1156 0.6491 1.0000
1.000 0.6532 0.01568 0.00666 -0.1151 0.6392 1.0000
1.250 0.6777 0.01586 0.00672 -0.1145 0.6290 1.0000
1.500 0.7038 0.01602 0.00673 -0.1142 0.6200 1.0000
1.750 0.7281 0.01622 0.00685 -0.1136 0.6100 1.0000
2.000 0.7529 0.01643 0.00697 -0.1131 0.6009 1.0000
2.250 0.7784 0.01664 0.00707 -0.1127 0.5924 1.0000
2.500 0.8022 0.01689 0.00728 -0.1121 0.5832 1.0000
2.750 0.8283 0.01711 0.00739 -0.1118 0.5758 1.0000
3.000 0.8513 0.01738 0.00765 -0.1111 0.5665 1.0000
3.250 0.8768 0.01762 0.00782 -0.1107 0.5594 1.0000
3.500 0.9001 0.01791 0.00811 -0.1101 0.5511 1.0000
3.750 0.9261 0.01816 0.00829 -0.1099 0.5452 1.0000
4.000 0.9492 0.01849 0.00866 -0.1092 0.5380 1.0000
4.250 0.9744 0.01876 0.00890 -0.1089 0.5321 1.0000
4.500 0.9978 0.01909 0.00924 -0.1083 0.5253 1.0000
4.750 1.0217 0.01938 0.00954 -0.1077 0.5186 1.0000
5.000 1.0452 0.01969 0.00985 -0.1071 0.5121 1.0000
5.250 1.0682 0.02001 0.01020 -0.1064 0.5053 1.0000
5.500 1.0922 0.02031 0.01051 -0.1059 0.4991 1.0000
5.750 1.1137 0.02066 0.01092 -0.1050 0.4918 1.0000
6.000 1.1384 0.02095 0.01118 -0.1046 0.4860 1.0000
6.250 1.1591 0.02137 0.01171 -0.1036 0.4795 1.0000
6.500 1.1828 0.02174 0.01215 -0.1031 0.4746 1.0000
6.750 1.2081 0.02211 0.01256 -0.1028 0.4706 1.0000
7.000 1.2289 0.02260 0.01319 -0.1019 0.4656 1.0000
7.250 1.2518 0.02303 0.01373 -0.1013 0.4609 1.0000
7.500 1.2764 0.02340 0.01415 -0.1010 0.4555 1.0000
7.750 1.2910 0.02381 0.01465 -0.0988 0.4443 1.0000
8.000 1.3038 0.02420 0.01508 -0.0964 0.4309 1.0000
8.250 1.3167 0.02463 0.01556 -0.0940 0.4188 1.0000
8.500 1.3294 0.02508 0.01604 -0.0916 0.4072 1.0000
8.750 1.3350 0.02559 0.01660 -0.0881 0.3931 1.0000
9.000 1.3407 0.02621 0.01734 -0.0847 0.3796 1.0000
9.250 1.3455 0.02696 0.01823 -0.0815 0.3655 1.0000
9.500 1.3456 0.02793 0.01932 -0.0779 0.3452 1.0000
9.750 1.3452 0.02910 0.02054 -0.0746 0.3174 1.0000
10.000 1.3415 0.03063 0.02193 -0.0711 0.2798 1.0000
10.250 1.3280 0.03304 0.02402 -0.0671 0.2404 1.0000
10.500 1.3157 0.03581 0.02659 -0.0638 0.2087 1.0000
10.750 1.3010 0.03909 0.02968 -0.0609 0.1562 1.0000
11.000 1.2739 0.04374 0.03397 -0.0579 0.1117 1.0000
11.250 1.2523 0.04830 0.03834 -0.0558 0.0729 1.0000
11.500 1.2300 0.05325 0.04311 -0.0543 0.0437 1.0000
11.750 1.2181 0.05740 0.04726 -0.0534 0.0363 1.0000
12.000 1.2103 0.06126 0.05121 -0.0528 0.0327 1.0000
12.250 1.2044 0.06504 0.05512 -0.0525 0.0304 1.0000
12.500 1.1978 0.06900 0.05922 -0.0523 0.0288 1.0000
12.750 1.1905 0.07315 0.06354 -0.0522 0.0278 1.0000
13.250 1.1779 0.08153 0.07221 -0.0526 0.0263 1.0000
13.500 1.1729 0.08564 0.07649 -0.0529 0.0256 1.0000
13.750 1.1678 0.08983 0.08084 -0.0534 0.0249 1.0000
14.000 1.1628 0.09404 0.08520 -0.0539 0.0241 1.0000
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Polar data table (+)
Polar graphs
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