GOE 483 AIRFOIL (goe483-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 483 AIRFOIL (goe483-il) Reynolds number: 50,000 Max Cl/Cd: 44.55 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe483-il-50000-n5.txt Download as CSV file: xf-goe483-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2828 0.10309 0.09693 -0.0265 1.0000 0.0671
-7.000 -0.2856 0.10227 0.09625 -0.0273 1.0000 0.0676
-6.750 -0.2877 0.10142 0.09551 -0.0284 1.0000 0.0680
-6.500 -0.2887 0.10046 0.09465 -0.0297 1.0000 0.0682
-6.250 -0.2882 0.09819 0.09249 -0.0296 1.0000 0.0685
-6.000 -0.2873 0.09266 0.08702 -0.0240 1.0000 0.0702
-5.750 -0.2878 0.09015 0.08458 -0.0219 1.0000 0.0724
-5.500 -0.2881 0.08818 0.08268 -0.0211 1.0000 0.0750
-5.250 -0.2866 0.08637 0.08091 -0.0214 1.0000 0.0778
-5.000 -0.2772 0.08554 0.08009 -0.0261 1.0000 0.0813
-4.750 -0.2592 0.08299 0.07754 -0.0313 0.9982 0.0825
-4.500 -0.2429 0.07757 0.07214 -0.0305 0.9917 0.0864
-4.250 -0.2051 0.07367 0.06810 -0.0383 0.9833 0.0924
-3.750 -0.1161 0.06551 0.05963 -0.0569 0.9675 0.0967
-3.500 -0.0646 0.05883 0.05259 -0.0659 0.9602 0.0541
-3.250 -0.0321 0.05453 0.04822 -0.0696 0.9541 0.0512
-3.000 0.0102 0.05061 0.04407 -0.0759 0.9456 0.0520
-2.750 0.0608 0.04625 0.03939 -0.0832 0.9401 0.0522
-2.500 0.1017 0.04247 0.03529 -0.0878 0.9318 0.0514
-2.250 0.1542 0.03811 0.03044 -0.0943 0.9267 0.0523
-2.000 0.1913 0.03559 0.02761 -0.0972 0.9178 0.0597
-1.750 0.2422 0.03180 0.02314 -0.1021 0.9131 0.0639
-1.500 0.2787 0.02983 0.02071 -0.1041 0.9038 0.0760
-1.250 0.3243 0.02745 0.01763 -0.1072 0.8982 0.0886
-1.000 0.3586 0.02624 0.01592 -0.1082 0.8882 0.1088
-0.750 0.3947 0.02529 0.01461 -0.1093 0.8790 0.1269
-0.500 0.4344 0.02462 0.01362 -0.1110 0.8711 0.1542
-0.250 0.4659 0.02431 0.01313 -0.1113 0.8596 0.1830
0.000 0.4975 0.02395 0.01261 -0.1117 0.8482 0.2120
0.250 0.5292 0.02353 0.01202 -0.1119 0.8369 0.2395
0.500 0.5607 0.02309 0.01149 -0.1121 0.8256 0.2675
0.750 0.5926 0.02260 0.01096 -0.1124 0.8146 0.2971
1.000 0.6216 0.02219 0.01057 -0.1122 0.8021 0.3309
1.250 0.6492 0.02173 0.01033 -0.1120 0.7886 0.3839
1.500 0.6770 0.02062 0.01010 -0.1113 0.7751 1.0000
1.750 0.7044 0.02076 0.01000 -0.1107 0.7612 1.0000
2.000 0.7313 0.02091 0.00998 -0.1101 0.7471 1.0000
2.250 0.7578 0.02106 0.01000 -0.1093 0.7329 1.0000
2.500 0.7839 0.02123 0.01007 -0.1086 0.7186 1.0000
2.750 0.8098 0.02141 0.01021 -0.1079 0.7042 1.0000
3.000 0.8356 0.02160 0.01035 -0.1071 0.6898 1.0000
3.250 0.8612 0.02180 0.01052 -0.1063 0.6753 1.0000
3.500 0.8867 0.02201 0.01073 -0.1055 0.6608 1.0000
3.750 0.9121 0.02223 0.01101 -0.1047 0.6462 1.0000
4.000 0.9375 0.02247 0.01128 -0.1039 0.6316 1.0000
4.250 0.9629 0.02273 0.01158 -0.1031 0.6169 1.0000
4.500 0.9882 0.02301 0.01198 -0.1023 0.6022 1.0000
4.750 1.0135 0.02331 0.01236 -0.1015 0.5875 1.0000
5.000 1.0384 0.02367 0.01282 -0.1007 0.5724 1.0000
5.250 1.0629 0.02409 0.01337 -0.0998 0.5569 1.0000
5.500 1.0871 0.02455 0.01404 -0.0989 0.5413 1.0000
5.750 1.1110 0.02506 0.01473 -0.0980 0.5255 1.0000
6.000 1.1346 0.02561 0.01550 -0.0971 0.5097 1.0000
6.250 1.1580 0.02621 0.01634 -0.0961 0.4940 1.0000
6.500 1.1808 0.02680 0.01722 -0.0949 0.4772 1.0000
6.750 1.1918 0.02675 0.01719 -0.0913 0.4303 1.0000
7.000 1.2025 0.02715 0.01758 -0.0881 0.3845 1.0000
7.250 1.2087 0.02797 0.01819 -0.0847 0.3189 1.0000
7.500 1.2138 0.02945 0.01928 -0.0815 0.2319 1.0000
8.000 1.2011 0.03632 0.02430 -0.0754 0.0446 1.0000
8.250 1.2034 0.03869 0.02675 -0.0727 0.0388 1.0000
8.500 1.2056 0.04093 0.02922 -0.0703 0.0361 1.0000
8.750 1.2042 0.04353 0.03201 -0.0680 0.0340 1.0000
9.000 1.2004 0.04643 0.03508 -0.0660 0.0325 1.0000
9.250 1.1995 0.04919 0.03811 -0.0645 0.0308 1.0000
9.500 1.1973 0.05223 0.04139 -0.0633 0.0292 1.0000
9.750 1.1949 0.05543 0.04479 -0.0623 0.0279 1.0000
10.000 1.1928 0.05873 0.04827 -0.0615 0.0269 1.0000
10.250 1.1928 0.06190 0.05175 -0.0606 0.0263 1.0000
10.500 1.1961 0.06483 0.05483 -0.0593 0.0256 1.0000
10.750 1.2109 0.06690 0.05703 -0.0567 0.0248 1.0000
11.000 1.2359 0.06877 0.05917 -0.0541 0.0239 1.0000
11.250 1.2475 0.07175 0.06254 -0.0529 0.0230 1.0000
11.500 1.2529 0.07532 0.06648 -0.0521 0.0223 1.0000
11.750 1.2536 0.07935 0.07085 -0.0518 0.0219 1.0000
12.000 1.2501 0.08381 0.07565 -0.0520 0.0217 1.0000
12.250 1.2433 0.08867 0.08082 -0.0527 0.0216 1.0000
12.500 1.2339 0.09394 0.08637 -0.0541 0.0217 1.0000
12.750 1.2227 0.09963 0.09232 -0.0562 0.0217 1.0000
13.000 1.2101 0.10574 0.09867 -0.0589 0.0218 1.0000
13.250 1.1967 0.11225 0.10541 -0.0622 0.0220 1.0000
13.500 1.1831 0.11918 0.11253 -0.0661 0.0221 1.0000
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Polar data table (+)
Polar graphs
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