GOE 492 AIRFOIL (goe492-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 492 AIRFOIL (goe492-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.59 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe492-il-1000000.txt Download as CSV file: xf-goe492-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4035 0.08872 0.08715 -0.0302 1.0000 0.0098
-8.000 -0.4081 0.08623 0.08469 -0.0293 1.0000 0.0098
-7.750 -0.4199 0.08445 0.08295 -0.0267 1.0000 0.0098
-7.500 -0.4033 0.07942 0.07793 -0.0333 0.9972 0.0098
-7.250 -0.3797 0.07349 0.07199 -0.0424 0.9941 0.0098
-7.000 -0.3579 0.06751 0.06599 -0.0512 0.9899 0.0099
-6.750 -0.3317 0.02208 0.01941 -0.0961 0.9775 0.0062
-6.500 -0.3034 0.01767 0.01444 -0.0988 0.9746 0.0068
-6.250 -0.2714 0.01676 0.01335 -0.1004 0.9727 0.0075
-6.000 -0.2406 0.01481 0.01108 -0.1018 0.9705 0.0080
-5.750 -0.2126 0.01301 0.00895 -0.1023 0.9668 0.0084
-5.500 -0.1859 0.01162 0.00731 -0.1023 0.9622 0.0088
-5.250 -0.1567 0.01089 0.00643 -0.1027 0.9588 0.0094
-5.000 -0.1260 0.01049 0.00593 -0.1034 0.9560 0.0099
-4.750 -0.1031 0.00865 0.00375 -0.1025 0.9495 0.0121
-4.500 -0.0749 0.00830 0.00334 -0.1026 0.9451 0.0138
-4.250 -0.0467 0.00800 0.00297 -0.1026 0.9409 0.0155
-4.000 -0.0205 0.00755 0.00245 -0.1023 0.9351 0.0200
-3.750 0.0079 0.00756 0.00249 -0.1023 0.9304 0.0247
-3.500 0.0349 0.00731 0.00221 -0.1022 0.9250 0.0316
-3.250 0.0622 0.00725 0.00213 -0.1020 0.9195 0.0349
-3.000 0.0902 0.00728 0.00214 -0.1020 0.9144 0.0364
-2.750 0.1163 0.00691 0.00170 -0.1017 0.9080 0.0405
-2.250 0.1703 0.00665 0.00136 -0.1012 0.8945 0.0487
-2.000 0.1976 0.00652 0.00117 -0.1010 0.8878 0.0518
-1.750 0.2241 0.00636 0.00100 -0.1007 0.8790 0.0585
-1.500 0.2507 0.00617 0.00086 -0.1004 0.8705 0.0839
-1.250 0.2763 0.00571 0.00080 -0.1002 0.8625 0.2281
-1.000 0.3034 0.00565 0.00079 -0.1000 0.8545 0.2557
-0.750 0.3305 0.00563 0.00076 -0.0998 0.8462 0.2709
-0.500 0.3574 0.00561 0.00074 -0.0996 0.8360 0.2846
-0.250 0.3842 0.00559 0.00073 -0.0993 0.8244 0.2977
0.000 0.4111 0.00558 0.00071 -0.0991 0.8123 0.3083
0.250 0.4376 0.00556 0.00069 -0.0988 0.7983 0.3202
0.750 0.4887 0.00521 0.00071 -0.0980 0.7643 0.4897
1.000 0.5085 0.00451 0.00084 -0.0964 0.7446 0.8046
1.250 0.5478 0.00426 0.00087 -0.0989 0.7177 1.0000
1.500 0.5718 0.00447 0.00092 -0.0980 0.6845 1.0000
1.750 0.5961 0.00467 0.00100 -0.0973 0.6535 1.0000
2.000 0.6201 0.00492 0.00109 -0.0964 0.6192 1.0000
2.250 0.6442 0.00518 0.00122 -0.0957 0.5812 1.0000
2.500 0.6677 0.00549 0.00133 -0.0948 0.5300 1.0000
2.750 0.6872 0.00618 0.00155 -0.0933 0.4197 1.0000
3.000 0.7006 0.00764 0.00207 -0.0910 0.2087 1.0000
3.250 0.7178 0.00883 0.00259 -0.0894 0.0486 1.0000
3.500 0.7413 0.00934 0.00298 -0.0885 0.0185 1.0000
3.750 0.7661 0.00969 0.00340 -0.0878 0.0149 1.0000
4.000 0.7908 0.01003 0.00378 -0.0872 0.0133 1.0000
4.250 0.8151 0.01042 0.00421 -0.0865 0.0120 1.0000
4.500 0.8379 0.01099 0.00484 -0.0855 0.0105 1.0000
4.750 0.8519 0.01273 0.00677 -0.0826 0.0093 1.0000
5.000 0.8760 0.01314 0.00721 -0.0819 0.0089 1.0000
5.250 0.8996 0.01361 0.00775 -0.0811 0.0083 1.0000
5.500 0.9211 0.01451 0.00871 -0.0799 0.0080 1.0000
5.750 0.9431 0.01549 0.00976 -0.0787 0.0076 1.0000
6.000 0.9659 0.01640 0.01074 -0.0778 0.0070 1.0000
6.250 0.9892 0.01704 0.01142 -0.0771 0.0064 1.0000
6.500 1.0117 0.01798 0.01242 -0.0762 0.0059 1.0000
6.750 1.0332 0.02010 0.01472 -0.0750 0.0056 1.0000
7.000 1.0041 0.02466 0.02079 -0.0650 0.0091 1.0000
7.250 1.0149 0.02815 0.02454 -0.0627 0.0091 1.0000
7.500 1.0235 0.03182 0.02849 -0.0601 0.0091 1.0000
7.750 1.0329 0.03495 0.03185 -0.0577 0.0090 1.0000
8.000 1.0605 0.03481 0.03181 -0.0566 0.0076 1.0000
8.250 1.0684 0.03825 0.03544 -0.0543 0.0069 1.0000
8.500 1.0706 0.04227 0.03966 -0.0517 0.0066 1.0000
8.750 1.0689 0.04640 0.04398 -0.0490 0.0064 1.0000
9.000 1.0637 0.05034 0.04807 -0.0462 0.0063 1.0000
9.250 1.0528 0.05413 0.05200 -0.0430 0.0062 1.0000
9.500 1.0319 0.05746 0.05546 -0.0387 0.0062 1.0000
9.750 1.0083 0.06129 0.05941 -0.0357 0.0062 1.0000
10.000 0.9811 0.06631 0.06456 -0.0343 0.0062 1.0000
10.250 0.9511 0.07257 0.07095 -0.0347 0.0063 1.0000
10.500 0.9186 0.08043 0.07893 -0.0374 0.0065 1.0000
10.750 0.8852 0.09010 0.08872 -0.0427 0.0068 1.0000
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Polar data table (+)
Polar graphs
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