GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 396 AIRFOIL (goe396-il) Reynolds number: 200,000 Max Cl/Cd: 89.06 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe396-il-200000-n5.txt Download as CSV file: xf-goe396-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2825 0.10628 0.10288 -0.0319 1.0000 0.0087
-8.000 -0.2820 0.10395 0.10061 -0.0312 1.0000 0.0087
-7.750 -0.2840 0.10182 0.09854 -0.0300 1.0000 0.0086
-7.500 -0.2805 0.09914 0.09592 -0.0303 0.9982 0.0086
-7.250 -0.2641 0.09441 0.09119 -0.0335 0.9924 0.0084
-7.000 -0.2473 0.09020 0.08699 -0.0376 0.9847 0.0082
-6.750 -0.2288 0.08604 0.08284 -0.0420 0.9774 0.0077
-6.500 -0.2084 0.08206 0.07885 -0.0471 0.9683 0.0075
-6.250 -0.1855 0.07791 0.07470 -0.0529 0.9592 0.0076
-6.000 -0.1577 0.07371 0.07044 -0.0598 0.9520 0.0079
-5.750 -0.1262 0.07111 0.06783 -0.0673 0.9433 0.0165
-5.500 -0.0897 0.06729 0.06395 -0.0767 0.9337 0.0169
-5.250 -0.0561 0.06308 0.05967 -0.0836 0.9265 0.0170
-5.000 -0.0263 0.05897 0.05550 -0.0889 0.9176 0.0170
-4.750 0.0035 0.05490 0.05135 -0.0938 0.9091 0.0170
-4.500 0.0335 0.05076 0.04711 -0.0984 0.9016 0.0169
-4.250 0.0522 0.04700 0.04330 -0.1001 0.8925 0.0152
-4.000 0.0846 0.04317 0.03934 -0.1046 0.8847 0.0143
-3.750 0.1178 0.03937 0.03538 -0.1087 0.8766 0.0139
-3.500 0.1511 0.03558 0.03139 -0.1122 0.8686 0.0140
-3.250 0.1863 0.03145 0.02700 -0.1154 0.8617 0.0149
-3.000 0.2168 0.02905 0.02439 -0.1172 0.8536 0.0239
-2.750 0.2489 0.02519 0.02015 -0.1188 0.8470 0.0237
-2.500 0.2780 0.02132 0.01581 -0.1195 0.8393 0.0216
-2.250 0.3078 0.01738 0.01096 -0.1196 0.8330 0.0197
-2.000 0.3351 0.01546 0.00846 -0.1191 0.8253 0.0191
-1.750 0.3624 0.01419 0.00677 -0.1187 0.8184 0.0190
-1.500 0.3891 0.01324 0.00555 -0.1182 0.8107 0.0197
-1.250 0.4155 0.01255 0.00468 -0.1177 0.8031 0.0215
-1.000 0.4421 0.01208 0.00406 -0.1172 0.7955 0.0245
-0.750 0.4682 0.01171 0.00359 -0.1167 0.7873 0.0275
-0.500 0.4947 0.01152 0.00335 -0.1164 0.7796 0.0354
-0.250 0.5205 0.01120 0.00295 -0.1157 0.7695 0.0411
0.000 0.5460 0.01098 0.00272 -0.1151 0.7581 0.0618
0.250 0.5715 0.01084 0.00264 -0.1146 0.7460 0.1130
0.500 0.5969 0.01075 0.00258 -0.1140 0.7333 0.1473
0.750 0.6224 0.01070 0.00252 -0.1134 0.7209 0.1701
1.000 0.6480 0.01066 0.00248 -0.1129 0.7090 0.1933
1.250 0.6736 0.01062 0.00247 -0.1124 0.6975 0.2248
1.500 0.6982 0.01041 0.00254 -0.1119 0.6852 0.3499
1.750 0.7451 0.00935 0.00250 -0.1163 0.6702 1.0000
2.000 0.7703 0.00947 0.00252 -0.1157 0.6565 1.0000
2.250 0.7955 0.00961 0.00258 -0.1151 0.6436 1.0000
2.500 0.8206 0.00975 0.00274 -0.1145 0.6307 1.0000
2.750 0.8455 0.00991 0.00285 -0.1139 0.6177 1.0000
3.000 0.8703 0.01008 0.00297 -0.1133 0.6036 1.0000
3.250 0.8947 0.01027 0.00312 -0.1126 0.5883 1.0000
3.500 0.9193 0.01047 0.00330 -0.1119 0.5742 1.0000
3.750 0.9438 0.01066 0.00351 -0.1112 0.5598 1.0000
4.000 0.9681 0.01087 0.00375 -0.1106 0.5449 1.0000
4.250 0.9858 0.01138 0.00394 -0.1085 0.4784 1.0000
4.500 0.9950 0.01260 0.00454 -0.1052 0.3456 1.0000
4.750 0.9936 0.01526 0.00584 -0.1010 0.1208 1.0000
5.000 1.0052 0.01681 0.00687 -0.0984 0.0137 1.0000
5.250 1.0249 0.01752 0.00771 -0.0968 0.0102 1.0000
5.500 1.0439 0.01829 0.00861 -0.0952 0.0077 1.0000
5.750 1.0620 0.01910 0.00953 -0.0936 0.0051 1.0000
6.000 1.0791 0.02004 0.01065 -0.0917 0.0046 1.0000
6.250 1.0947 0.02109 0.01185 -0.0896 0.0043 1.0000
6.500 1.1079 0.02231 0.01321 -0.0872 0.0042 1.0000
6.750 1.1191 0.02370 0.01469 -0.0844 0.0040 1.0000
7.000 1.1308 0.02517 0.01624 -0.0818 0.0040 1.0000
7.250 1.1442 0.02678 0.01793 -0.0795 0.0040 1.0000
7.500 1.1612 0.02858 0.01983 -0.0776 0.0040 1.0000
7.750 1.1821 0.03060 0.02198 -0.0763 0.0041 1.0000
8.000 1.2050 0.03286 0.02445 -0.0753 0.0043 1.0000
8.250 1.2270 0.03542 0.02728 -0.0742 0.0045 1.0000
8.500 1.2456 0.03804 0.03020 -0.0726 0.0047 1.0000
8.750 1.2607 0.04103 0.03378 -0.0706 0.0050 1.0000
9.000 1.2711 0.04405 0.03714 -0.0682 0.0053 1.0000
9.250 1.2773 0.04714 0.04056 -0.0656 0.0055 1.0000
9.500 1.2796 0.05035 0.04406 -0.0628 0.0057 1.0000
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Polar data table (+)
Polar graphs
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