GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 500,000 Max Cl/Cd: 111.2 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe396-il-500000-n5.txt Download as CSV file: xf-goe396-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 396 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2932 0.10932 0.10708 -0.0295 1.0000 0.0046
-8.750 -0.2894 0.10677 0.10455 -0.0296 1.0000 0.0049
-8.500 -0.2860 0.10438 0.10219 -0.0296 1.0000 0.0052
-8.250 -0.2767 0.10139 0.09922 -0.0314 0.9989 0.0057
-8.000 -0.2614 0.09790 0.09574 -0.0347 0.9926 0.0070
-7.750 -0.2447 0.09463 0.09247 -0.0384 0.9846 0.0079
-7.500 -0.2279 0.09119 0.08903 -0.0424 0.9761 0.0081
-7.250 -0.2091 0.08736 0.08519 -0.0471 0.9667 0.0081
-7.000 -0.1900 0.07984 0.07768 -0.0554 0.9544 0.0027
-6.750 -0.1594 0.07595 0.07376 -0.0627 0.9429 0.0025
-6.500 -0.1293 0.07186 0.06963 -0.0699 0.9296 0.0025
-6.250 -0.1042 0.06664 0.06434 -0.0772 0.9112 0.0025
-6.000 -0.0828 0.06269 0.06028 -0.0823 0.8924 0.0026
-5.750 -0.0645 0.05921 0.05671 -0.0861 0.8765 0.0028
-5.500 -0.0449 0.05628 0.05370 -0.0893 0.8636 0.0030
-5.250 -0.0243 0.05379 0.05114 -0.0921 0.8531 0.0033
-5.000 -0.0021 0.05115 0.04842 -0.0950 0.8438 0.0037
-4.750 0.0217 0.04852 0.04570 -0.0980 0.8353 0.0048
-4.500 0.0479 0.04557 0.04267 -0.1013 0.8273 0.0067
-4.250 0.0760 0.04200 0.03898 -0.1049 0.8202 0.0069
-4.000 0.1057 0.03822 0.03508 -0.1085 0.8131 0.0068
-3.750 0.1367 0.03428 0.03097 -0.1118 0.8068 0.0068
-3.500 0.1688 0.02989 0.02639 -0.1148 0.8002 0.0069
-3.250 0.2028 0.02382 0.01996 -0.1175 0.7944 0.0074
-3.000 0.2337 0.01798 0.01361 -0.1183 0.7886 0.0088
-2.750 0.2585 0.01618 0.01153 -0.1186 0.7819 0.0113
-2.500 0.2846 0.01552 0.01067 -0.1185 0.7734 0.0141
-2.250 0.3107 0.01309 0.00766 -0.1179 0.7651 0.0133
-2.000 0.3368 0.01154 0.00561 -0.1173 0.7554 0.0128
-1.750 0.3630 0.01052 0.00427 -0.1167 0.7446 0.0125
-1.500 0.3890 0.00979 0.00332 -0.1161 0.7333 0.0125
-1.250 0.4149 0.00925 0.00260 -0.1155 0.7216 0.0130
-1.000 0.4409 0.00889 0.00210 -0.1149 0.7102 0.0148
-0.750 0.4672 0.00880 0.00194 -0.1145 0.6982 0.0169
-0.500 0.4931 0.00860 0.00164 -0.1141 0.6856 0.0190
-0.250 0.5188 0.00844 0.00140 -0.1136 0.6728 0.0245
0.000 0.5448 0.00840 0.00125 -0.1132 0.6597 0.0246
0.250 0.5708 0.00839 0.00115 -0.1127 0.6466 0.0249
0.500 0.5967 0.00840 0.00108 -0.1123 0.6337 0.0257
0.750 0.6225 0.00843 0.00105 -0.1119 0.6202 0.0295
1.000 0.6475 0.00836 0.00105 -0.1114 0.6047 0.0786
1.250 0.6730 0.00840 0.00110 -0.1109 0.5906 0.1065
1.500 0.6986 0.00844 0.00115 -0.1105 0.5774 0.1291
1.750 0.7241 0.00849 0.00123 -0.1101 0.5637 0.1556
2.000 0.7495 0.00854 0.00132 -0.1097 0.5500 0.1874
2.250 0.7745 0.00857 0.00145 -0.1093 0.5348 0.2447
2.500 0.8207 0.00740 0.00175 -0.1142 0.5156 1.0000
2.750 0.8451 0.00760 0.00186 -0.1135 0.4946 1.0000
3.000 0.8693 0.00782 0.00198 -0.1129 0.4735 1.0000
3.250 0.8935 0.00804 0.00213 -0.1122 0.4528 1.0000
3.500 0.9175 0.00828 0.00230 -0.1116 0.4315 1.0000
3.750 0.9388 0.00875 0.00255 -0.1104 0.3840 1.0000
4.000 0.9403 0.01116 0.00361 -0.1064 0.1290 1.0000
4.250 0.9612 0.01176 0.00403 -0.1053 0.0929 1.0000
4.500 0.9773 0.01285 0.00473 -0.1033 0.0052 1.0000
4.750 1.0005 0.01319 0.00524 -0.1025 0.0042 1.0000
5.000 1.0217 0.01376 0.00595 -0.1012 0.0025 1.0000
5.250 1.0425 0.01435 0.00663 -0.0999 0.0022 1.0000
5.500 1.0619 0.01507 0.00745 -0.0983 0.0020 1.0000
5.750 1.0795 0.01596 0.00843 -0.0964 0.0019 1.0000
6.000 1.0950 0.01701 0.00958 -0.0942 0.0018 1.0000
6.250 1.1096 0.01813 0.01078 -0.0918 0.0018 1.0000
6.500 1.1232 0.01939 0.01213 -0.0893 0.0018 1.0000
6.750 1.1370 0.02083 0.01366 -0.0868 0.0018 1.0000
7.000 1.1530 0.02237 0.01528 -0.0848 0.0019 1.0000
7.250 1.1717 0.02419 0.01721 -0.0831 0.0019 1.0000
7.500 1.1929 0.02632 0.01949 -0.0819 0.0020 1.0000
7.750 1.2143 0.02878 0.02214 -0.0807 0.0021 1.0000
8.000 1.2335 0.03204 0.02568 -0.0793 0.0022 1.0000
8.250 1.2528 0.03533 0.02912 -0.0782 0.0025 1.0000
8.500 1.2675 0.03684 0.03096 -0.0762 0.0026 1.0000
8.750 1.2803 0.03867 0.03303 -0.0740 0.0027 1.0000
9.000 1.2901 0.04093 0.03555 -0.0714 0.0027 1.0000
9.250 1.2954 0.04361 0.03851 -0.0684 0.0028 1.0000
9.500 1.2964 0.04650 0.04166 -0.0652 0.0027 1.0000
9.750 1.2929 0.04935 0.04476 -0.0615 0.0027 1.0000
10.000 1.2846 0.05185 0.04747 -0.0573 0.0027 1.0000
10.250 1.2733 0.05453 0.05036 -0.0533 0.0027 1.0000
10.500 1.2604 0.05746 0.05349 -0.0499 0.0027 1.0000
10.750 1.2461 0.06071 0.05693 -0.0472 0.0027 1.0000
11.000 1.2322 0.06413 0.06053 -0.0454 0.0027 1.0000
11.250 1.2155 0.06819 0.06477 -0.0443 0.0027 1.0000
11.500 1.1990 0.07258 0.06933 -0.0439 0.0027 1.0000
11.750 1.1838 0.07712 0.07403 -0.0444 0.0027 1.0000
12.000 1.1669 0.08238 0.07945 -0.0457 0.0027 1.0000
12.250 1.1502 0.08813 0.08535 -0.0478 0.0027 1.0000
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Polar data table (+)
Polar graphs
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