GOE 362 AIRFOIL (goe362-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 362 AIRFOIL (goe362-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.73 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe362-il-1000000-n5.txt Download as CSV file: xf-goe362-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 362 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 -0.3006 0.10206 0.10044 -0.0248 1.0000 0.0045
-8.750 -0.2969 0.09923 0.09763 -0.0253 1.0000 0.0045
-8.500 -0.2937 0.09648 0.09491 -0.0256 1.0000 0.0044
-8.250 -0.2834 0.09331 0.09174 -0.0277 0.9934 0.0042
-8.000 -0.2700 0.08902 0.08746 -0.0317 0.9859 0.0044
-7.750 -0.2531 0.08533 0.08376 -0.0360 0.9784 0.0042
-7.500 -0.2305 0.08080 0.07922 -0.0425 0.9701 0.0043
-6.000 -0.0977 0.01549 0.01194 -0.1133 0.8389 0.0046
-5.750 -0.0722 0.01375 0.00979 -0.1135 0.8219 0.0047
-5.500 -0.0468 0.01195 0.00755 -0.1135 0.8048 0.0050
-5.250 -0.0206 0.01117 0.00653 -0.1133 0.7879 0.0052
-5.000 0.0060 0.01066 0.00583 -0.1130 0.7706 0.0054
-4.750 0.0328 0.01024 0.00524 -0.1127 0.7555 0.0057
-4.500 0.0597 0.00982 0.00466 -0.1124 0.7412 0.0060
-4.250 0.0867 0.00949 0.00419 -0.1122 0.7265 0.0064
-4.000 0.1138 0.00924 0.00379 -0.1119 0.7108 0.0069
-3.750 0.1408 0.00896 0.00336 -0.1116 0.6952 0.0072
-3.500 0.1679 0.00852 0.00278 -0.1113 0.6817 0.0080
-3.250 0.1951 0.00833 0.00250 -0.1110 0.6686 0.0086
-3.000 0.2224 0.00817 0.00224 -0.1107 0.6559 0.0095
-2.750 0.2498 0.00804 0.00201 -0.1105 0.6438 0.0103
-2.250 0.3046 0.00775 0.00159 -0.1100 0.6217 0.0146
-2.000 0.3320 0.00765 0.00143 -0.1097 0.6112 0.0176
-1.750 0.3594 0.00758 0.00133 -0.1095 0.6006 0.0233
-1.500 0.3869 0.00753 0.00123 -0.1093 0.5892 0.0281
-1.250 0.4143 0.00748 0.00115 -0.1090 0.5771 0.0334
-1.000 0.4417 0.00745 0.00107 -0.1088 0.5645 0.0400
-0.750 0.4689 0.00744 0.00102 -0.1086 0.5495 0.0490
-0.500 0.4960 0.00742 0.00100 -0.1083 0.5321 0.0716
-0.250 0.5229 0.00747 0.00100 -0.1081 0.5120 0.0852
0.000 0.5498 0.00755 0.00100 -0.1078 0.4896 0.0928
0.250 0.5766 0.00766 0.00101 -0.1075 0.4696 0.0991
0.500 0.6035 0.00775 0.00103 -0.1072 0.4526 0.1040
0.750 0.6304 0.00782 0.00106 -0.1070 0.4391 0.1124
1.250 0.6845 0.00786 0.00117 -0.1065 0.4178 0.1746
1.500 0.7115 0.00791 0.00124 -0.1063 0.4090 0.2026
1.750 0.7386 0.00796 0.00130 -0.1061 0.4008 0.2232
2.000 0.7656 0.00800 0.00137 -0.1059 0.3935 0.2490
2.250 0.7923 0.00789 0.00149 -0.1058 0.3857 0.3694
2.750 0.8485 0.00691 0.00177 -0.1062 0.3716 1.0000
3.000 0.8754 0.00703 0.00186 -0.1059 0.3653 1.0000
3.250 0.9023 0.00716 0.00195 -0.1057 0.3558 1.0000
3.500 0.9289 0.00731 0.00205 -0.1054 0.3452 1.0000
3.750 0.9554 0.00748 0.00217 -0.1051 0.3331 1.0000
4.000 0.9814 0.00769 0.00230 -0.1048 0.3145 1.0000
4.250 1.0070 0.00796 0.00245 -0.1044 0.2940 1.0000
4.500 1.0331 0.00816 0.00261 -0.1041 0.2803 1.0000
4.750 1.0588 0.00841 0.00279 -0.1037 0.2641 1.0000
5.000 1.0838 0.00872 0.00300 -0.1033 0.2410 1.0000
5.250 1.1084 0.00908 0.00325 -0.1028 0.2174 1.0000
5.500 1.1333 0.00940 0.00350 -0.1023 0.1991 1.0000
6.000 1.1820 0.01016 0.00408 -0.1013 0.1581 1.0000
6.250 1.2054 0.01064 0.00444 -0.1006 0.1327 1.0000
6.500 1.2267 0.01137 0.00495 -0.0997 0.0942 1.0000
6.750 1.2489 0.01196 0.00542 -0.0989 0.0716 1.0000
7.000 1.2727 0.01235 0.00577 -0.0983 0.0619 1.0000
7.250 1.2967 0.01270 0.00611 -0.0977 0.0548 1.0000
7.500 1.3197 0.01316 0.00653 -0.0970 0.0454 1.0000
7.750 1.3430 0.01356 0.00692 -0.0964 0.0391 1.0000
8.000 1.3655 0.01403 0.00735 -0.0956 0.0309 1.0000
8.250 1.3847 0.01485 0.00805 -0.0944 0.0132 1.0000
8.500 1.4055 0.01546 0.00866 -0.0934 0.0085 1.0000
8.750 1.4270 0.01597 0.00920 -0.0925 0.0069 1.0000
9.000 1.4476 0.01654 0.00981 -0.0915 0.0057 1.0000
9.250 1.4686 0.01704 0.01039 -0.0905 0.0050 1.0000
9.500 1.4883 0.01763 0.01102 -0.0894 0.0044 1.0000
9.750 1.5072 0.01827 0.01171 -0.0881 0.0038 1.0000
10.000 1.5263 0.01885 0.01235 -0.0869 0.0036 1.0000
10.250 1.5443 0.01948 0.01304 -0.0856 0.0032 1.0000
10.500 1.5611 0.02016 0.01379 -0.0841 0.0030 1.0000
10.750 1.5761 0.02094 0.01462 -0.0823 0.0027 1.0000
11.000 1.5873 0.02185 0.01561 -0.0800 0.0025 1.0000
11.250 1.5977 0.02261 0.01645 -0.0774 0.0025 1.0000
11.500 1.6068 0.02343 0.01739 -0.0748 0.0024 1.0000
11.750 1.6147 0.02437 0.01841 -0.0722 0.0023 1.0000
12.000 1.6221 0.02538 0.01951 -0.0697 0.0021 1.0000
12.250 1.6281 0.02654 0.02076 -0.0673 0.0021 1.0000
12.500 1.6339 0.02780 0.02211 -0.0651 0.0020 1.0000
12.750 1.6392 0.02917 0.02356 -0.0631 0.0019 1.0000
13.000 1.6436 0.03070 0.02519 -0.0613 0.0018 1.0000
13.250 1.6464 0.03247 0.02705 -0.0596 0.0017 1.0000
13.500 1.6466 0.03461 0.02930 -0.0581 0.0016 1.0000
13.750 1.6441 0.03718 0.03198 -0.0568 0.0016 1.0000
14.000 1.6385 0.04027 0.03520 -0.0559 0.0015 1.0000
14.250 1.6378 0.04299 0.03804 -0.0554 0.0015 1.0000
14.500 1.6351 0.04614 0.04132 -0.0552 0.0014 1.0000
14.750 1.6300 0.04974 0.04503 -0.0553 0.0014 1.0000
15.000 1.6248 0.05353 0.04897 -0.0557 0.0014 1.0000
15.250 1.6175 0.05779 0.05336 -0.0565 0.0014 1.0000
15.500 1.6088 0.06242 0.05813 -0.0576 0.0014 1.0000
15.750 1.5983 0.06758 0.06343 -0.0592 0.0014 1.0000
16.000 1.5889 0.07279 0.06876 -0.0609 0.0013 1.0000
16.250 1.5764 0.07872 0.07484 -0.0631 0.0013 1.0000
16.500 1.5619 0.08526 0.08151 -0.0658 0.0013 1.0000
16.750 1.5508 0.09132 0.08770 -0.0683 0.0013 1.0000
17.000 1.5348 0.09847 0.09499 -0.0715 0.0013 1.0000
17.250 1.5197 0.10561 0.10226 -0.0748 0.0013 1.0000
17.500 1.5052 0.11278 0.10956 -0.0783 0.0013 1.0000
17.750 1.4893 0.12039 0.11730 -0.0821 0.0013 1.0000
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Polar data table (+)
Polar graphs
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