GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.5 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe492-il-1000000-n5.txt Download as CSV file: xf-goe492-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 492 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4078 0.09653 0.09492 -0.0290 1.0000 0.0025
-8.750 -0.4073 0.09283 0.09125 -0.0297 1.0000 0.0033
-8.500 -0.4081 0.09004 0.08848 -0.0299 1.0000 0.0031
-8.000 -0.3933 0.08159 0.08006 -0.0367 0.9964 0.0030
-7.750 -0.3826 0.07719 0.07566 -0.0415 0.9902 0.0030
-7.500 -0.3691 0.07159 0.07007 -0.0486 0.9826 0.0029
-7.000 -0.3287 0.01863 0.01564 -0.1031 0.9526 0.0022
-6.750 -0.3057 0.01548 0.01195 -0.1036 0.9447 0.0022
-6.500 -0.2804 0.01367 0.00978 -0.1038 0.9385 0.0022
-6.250 -0.2549 0.01253 0.00840 -0.1037 0.9316 0.0024
-6.000 -0.2288 0.01156 0.00717 -0.1036 0.9251 0.0026
-5.750 -0.2030 0.01071 0.00612 -0.1034 0.9181 0.0028
-5.500 -0.1766 0.01004 0.00526 -0.1032 0.9125 0.0031
-5.250 -0.1502 0.00954 0.00462 -0.1030 0.9068 0.0034
-5.000 -0.1238 0.00893 0.00385 -0.1028 0.9016 0.0037
-4.750 -0.0973 0.00849 0.00333 -0.1026 0.8965 0.0043
-4.500 -0.0704 0.00821 0.00297 -0.1025 0.8909 0.0052
-4.250 -0.0434 0.00794 0.00261 -0.1024 0.8860 0.0058
-4.000 -0.0165 0.00755 0.00213 -0.1022 0.8807 0.0076
-3.750 0.0105 0.00733 0.00183 -0.1020 0.8750 0.0097
-3.500 0.0375 0.00710 0.00161 -0.1019 0.8695 0.0202
-3.250 0.0648 0.00700 0.00149 -0.1018 0.8633 0.0287
-3.000 0.0920 0.00690 0.00137 -0.1017 0.8574 0.0325
-2.750 0.1191 0.00681 0.00127 -0.1016 0.8498 0.0362
-2.500 0.1460 0.00678 0.00117 -0.1014 0.8386 0.0383
-2.250 0.1725 0.00667 0.00098 -0.1011 0.8246 0.0413
-2.000 0.1992 0.00659 0.00086 -0.1008 0.8107 0.0448
-1.750 0.2260 0.00654 0.00075 -0.1006 0.7985 0.0478
-1.500 0.2527 0.00651 0.00066 -0.1004 0.7852 0.0504
-1.250 0.2793 0.00647 0.00059 -0.1001 0.7703 0.0588
-1.000 0.3055 0.00638 0.00053 -0.0998 0.7529 0.0885
-0.750 0.3310 0.00617 0.00047 -0.0995 0.7332 0.1726
-0.500 0.3567 0.00613 0.00048 -0.0991 0.7095 0.2219
-0.250 0.3820 0.00623 0.00051 -0.0986 0.6802 0.2419
0.000 0.4081 0.00631 0.00053 -0.0983 0.6605 0.2546
0.250 0.4346 0.00637 0.00057 -0.0981 0.6449 0.2662
0.500 0.4611 0.00642 0.00061 -0.0979 0.6314 0.2782
0.750 0.4877 0.00646 0.00066 -0.0977 0.6194 0.2933
1.000 0.5145 0.00650 0.00071 -0.0975 0.6081 0.3064
1.250 0.5414 0.00652 0.00077 -0.0974 0.5981 0.3187
1.500 0.5673 0.00663 0.00083 -0.0970 0.5772 0.3294
1.750 0.5927 0.00673 0.00093 -0.0966 0.5465 0.3531
2.000 0.6160 0.00645 0.00108 -0.0961 0.5103 0.5833
2.250 0.6351 0.00671 0.00133 -0.0946 0.4174 0.7215
2.500 0.6538 0.00704 0.00159 -0.0930 0.3294 0.8251
2.750 0.6768 0.00828 0.00222 -0.0928 0.1043 1.0000
3.000 0.7000 0.00880 0.00248 -0.0921 0.0400 1.0000
3.250 0.7245 0.00916 0.00273 -0.0915 0.0147 1.0000
3.500 0.7500 0.00942 0.00299 -0.0911 0.0089 1.0000
3.750 0.7754 0.00967 0.00328 -0.0906 0.0073 1.0000
4.000 0.7997 0.01007 0.00372 -0.0900 0.0056 1.0000
4.250 0.8244 0.01040 0.00409 -0.0894 0.0050 1.0000
4.500 0.8493 0.01069 0.00439 -0.0889 0.0042 1.0000
4.750 0.8733 0.01109 0.00483 -0.0882 0.0036 1.0000
5.000 0.8951 0.01178 0.00561 -0.0871 0.0032 1.0000
5.250 0.9182 0.01229 0.00618 -0.0862 0.0030 1.0000
5.500 0.9401 0.01295 0.00694 -0.0851 0.0027 1.0000
5.750 0.9610 0.01375 0.00784 -0.0838 0.0024 1.0000
6.000 0.9811 0.01473 0.00892 -0.0824 0.0023 1.0000
6.250 1.0010 0.01589 0.01020 -0.0809 0.0022 1.0000
6.500 1.0229 0.01675 0.01119 -0.0799 0.0021 1.0000
6.750 1.0452 0.01746 0.01196 -0.0791 0.0020 1.0000
7.000 1.0645 0.01932 0.01403 -0.0776 0.0017 1.0000
7.250 1.0855 0.02111 0.01606 -0.0764 0.0017 1.0000
7.500 1.1040 0.02486 0.02023 -0.0742 0.0016 1.0000
7.750 1.1128 0.03367 0.02976 -0.0693 0.0013 1.0000
8.000 1.1191 0.03944 0.03597 -0.0653 0.0012 1.0000
8.250 1.1220 0.04492 0.04181 -0.0615 0.0011 1.0000
8.500 1.1224 0.05022 0.04741 -0.0579 0.0011 1.0000
8.750 1.1191 0.05536 0.05282 -0.0544 0.0012 1.0000
9.000 1.1130 0.06006 0.05773 -0.0512 0.0012 1.0000
9.250 1.1028 0.06452 0.06239 -0.0480 0.0012 1.0000
9.500 1.0865 0.06830 0.06631 -0.0443 0.0012 1.0000
9.750 1.0672 0.07153 0.06965 -0.0410 0.0012 1.0000
10.000 1.0462 0.07535 0.07358 -0.0392 0.0012 1.0000
10.250 1.0261 0.07972 0.07805 -0.0392 0.0013 1.0000
10.500 1.0043 0.08522 0.08365 -0.0410 0.0013 1.0000
10.750 0.9843 0.09173 0.09024 -0.0450 0.0013 1.0000
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Polar data table (+)
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