GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 500,000 Max Cl/Cd: 112.26 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe483-il-500000-n5.txt Download as CSV file: xf-goe483-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 483 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.2812 0.14084 0.13867 -0.0175 1.0000 0.0047
-12.750 -0.2755 0.13808 0.13592 -0.0186 1.0000 0.0048
-7.250 -0.2155 0.08487 0.08277 -0.0405 0.9653 0.0074
-7.000 -0.1900 0.08096 0.07883 -0.0468 0.9506 0.0077
-6.750 -0.1641 0.07700 0.07483 -0.0533 0.9329 0.0082
-6.500 -0.1426 0.07346 0.07122 -0.0584 0.9123 0.0084
-6.000 -0.0879 0.05087 0.04847 -0.0560 0.8292 0.0106
-5.000 -0.0310 0.05273 0.05002 -0.0802 0.8261 0.0061
-4.750 -0.0061 0.04911 0.04630 -0.0842 0.8176 0.0059
-4.500 0.0215 0.04535 0.04245 -0.0884 0.8099 0.0057
-4.250 0.0520 0.04121 0.03818 -0.0929 0.8024 0.0055
-4.000 0.0861 0.03638 0.03320 -0.0977 0.7955 0.0056
-3.750 0.1238 0.03031 0.02688 -0.1030 0.7887 0.0058
-3.500 0.1703 0.01549 0.01091 -0.1109 0.7840 0.0062
-3.250 0.1987 0.01337 0.00827 -0.1113 0.7767 0.0067
-3.000 0.2266 0.01146 0.00586 -0.1113 0.7697 0.0072
-2.750 0.2541 0.01064 0.00479 -0.1112 0.7614 0.0079
-2.500 0.2815 0.01006 0.00401 -0.1109 0.7523 0.0088
-2.250 0.3088 0.00961 0.00338 -0.1106 0.7424 0.0102
-2.000 0.3361 0.00909 0.00269 -0.1103 0.7318 0.0134
-1.750 0.3634 0.00878 0.00230 -0.1100 0.7212 0.0183
-1.500 0.3906 0.00859 0.00204 -0.1098 0.7103 0.0282
-1.250 0.4176 0.00847 0.00184 -0.1095 0.6982 0.0364
-1.000 0.4445 0.00837 0.00167 -0.1092 0.6849 0.0452
-0.750 0.4714 0.00828 0.00152 -0.1090 0.6699 0.0550
-0.500 0.4981 0.00821 0.00142 -0.1087 0.6528 0.0731
-0.250 0.5246 0.00821 0.00137 -0.1083 0.6328 0.0915
0.000 0.5511 0.00826 0.00130 -0.1080 0.6112 0.1019
0.250 0.5773 0.00834 0.00126 -0.1076 0.5888 0.1106
0.500 0.6036 0.00841 0.00126 -0.1073 0.5693 0.1202
0.750 0.6299 0.00849 0.00128 -0.1070 0.5528 0.1325
1.000 0.6564 0.00856 0.00132 -0.1068 0.5387 0.1512
1.250 0.6829 0.00865 0.00140 -0.1065 0.5263 0.1743
1.500 0.7094 0.00875 0.00148 -0.1063 0.5151 0.1938
1.750 0.7361 0.00884 0.00155 -0.1060 0.5043 0.2068
2.000 0.7628 0.00892 0.00163 -0.1058 0.4945 0.2170
2.250 0.7894 0.00902 0.00171 -0.1056 0.4844 0.2265
2.500 0.8159 0.00912 0.00181 -0.1054 0.4735 0.2365
2.750 0.8424 0.00922 0.00192 -0.1052 0.4611 0.2477
3.000 0.8688 0.00933 0.00203 -0.1049 0.4481 0.2615
3.250 0.8951 0.00943 0.00217 -0.1047 0.4361 0.2779
3.500 0.9213 0.00953 0.00231 -0.1045 0.4240 0.3053
4.500 1.0249 0.00913 0.00306 -0.1035 0.3682 1.0000
4.750 1.0489 0.00952 0.00331 -0.1030 0.3356 1.0000
5.000 1.0722 0.01001 0.00361 -0.1024 0.2987 1.0000
5.250 1.0935 0.01075 0.00405 -0.1015 0.2369 1.0000
5.500 1.1098 0.01213 0.00482 -0.1001 0.1323 1.0000
5.750 1.1227 0.01402 0.00608 -0.0981 0.0138 1.0000
6.000 1.1456 0.01459 0.00675 -0.0973 0.0091 1.0000
6.250 1.1692 0.01502 0.00725 -0.0967 0.0074 1.0000
6.500 1.1914 0.01562 0.00795 -0.0958 0.0063 1.0000
6.750 1.2115 0.01649 0.00895 -0.0946 0.0055 1.0000
7.000 1.2320 0.01726 0.00982 -0.0935 0.0051 1.0000
7.250 1.2528 0.01793 0.01055 -0.0925 0.0043 1.0000
7.500 1.2721 0.01871 0.01138 -0.0914 0.0038 1.0000
7.750 1.2863 0.01999 0.01278 -0.0894 0.0035 1.0000
8.000 1.3014 0.02110 0.01401 -0.0875 0.0033 1.0000
8.250 1.3139 0.02240 0.01548 -0.0853 0.0031 1.0000
8.500 1.3244 0.02381 0.01702 -0.0828 0.0029 1.0000
8.750 1.3333 0.02535 0.01869 -0.0801 0.0028 1.0000
9.000 1.3400 0.02695 0.02041 -0.0771 0.0027 1.0000
9.250 1.3474 0.02867 0.02225 -0.0742 0.0027 1.0000
9.500 1.3561 0.03066 0.02438 -0.0717 0.0026 1.0000
9.750 1.3667 0.03273 0.02660 -0.0696 0.0026 1.0000
10.000 1.3738 0.03402 0.02800 -0.0675 0.0024 1.0000
10.250 1.3800 0.03558 0.02968 -0.0654 0.0023 1.0000
10.500 1.3832 0.03784 0.03207 -0.0634 0.0021 1.0000
10.750 1.3888 0.04046 0.03498 -0.0612 0.0019 1.0000
11.000 1.3919 0.04370 0.03849 -0.0591 0.0019 1.0000
11.250 1.3907 0.04741 0.04249 -0.0569 0.0018 1.0000
11.500 1.3858 0.05119 0.04653 -0.0550 0.0017 1.0000
11.750 1.3778 0.05502 0.05060 -0.0535 0.0017 1.0000
12.000 1.3663 0.05950 0.05534 -0.0524 0.0016 1.0000
12.250 1.3537 0.06401 0.06007 -0.0520 0.0016 1.0000
12.500 1.3397 0.06891 0.06518 -0.0523 0.0016 1.0000
12.750 1.3249 0.07420 0.07067 -0.0533 0.0016 1.0000
13.000 1.3085 0.08015 0.07682 -0.0550 0.0016 1.0000
13.250 1.2925 0.08633 0.08317 -0.0575 0.0016 1.0000
13.500 1.2755 0.09316 0.09018 -0.0607 0.0016 1.0000
13.750 1.2597 0.10019 0.09738 -0.0645 0.0016 1.0000
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Polar data table (+)
Polar graphs
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