GOE 802 AIRFOIL (goe802-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 AIRFOIL (goe802-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.04 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802-il-1000000.txt Download as CSV file: xf-goe802-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2075 0.09702 0.09525 -0.0498 0.9295 0.0173
-8.750 -0.2045 0.09364 0.09183 -0.0522 0.9186 0.0173
-8.500 -0.1955 0.09035 0.08851 -0.0514 0.9112 0.0175
-8.250 -0.1862 0.08785 0.08599 -0.0517 0.9034 0.0176
-8.000 -0.1773 0.08541 0.08353 -0.0525 0.8950 0.0177
-7.750 -0.1682 0.08295 0.08104 -0.0537 0.8872 0.0179
-7.500 -0.1592 0.08042 0.07849 -0.0553 0.8789 0.0181
-7.250 -0.1497 0.07783 0.07587 -0.0573 0.8713 0.0184
-7.000 -0.1360 0.07487 0.07288 -0.0606 0.8637 0.0187
-6.750 -0.1205 0.07171 0.06968 -0.0644 0.8568 0.0193
-6.500 -0.0914 0.06555 0.06345 -0.0776 0.8486 0.0205
-6.250 -0.0672 0.06097 0.05878 -0.0842 0.8419 0.0206
-6.000 -0.0453 0.05598 0.05373 -0.0898 0.8351 0.0207
-5.750 -0.0277 0.05331 0.05101 -0.0913 0.8284 0.0209
-5.500 -0.0065 0.05092 0.04859 -0.0933 0.8210 0.0210
-5.250 0.0166 0.04847 0.04606 -0.0957 0.8125 0.0212
-5.000 0.0418 0.04587 0.04340 -0.0985 0.8038 0.0215
-4.750 0.0685 0.04320 0.04062 -0.1014 0.7954 0.0220
-4.500 0.1095 0.03820 0.03542 -0.1076 0.7882 0.0241
-4.250 0.1436 0.03364 0.03061 -0.1112 0.7807 0.0243
-4.000 0.1701 0.02880 0.02554 -0.1139 0.7735 0.0246
-3.750 0.1954 0.02715 0.02380 -0.1148 0.7648 0.0248
-3.500 0.2219 0.02565 0.02220 -0.1156 0.7559 0.0250
-3.000 0.2768 0.02267 0.01897 -0.1170 0.7365 0.0260
-2.750 0.3059 0.02076 0.01684 -0.1176 0.7265 0.0272
-2.500 0.3381 0.01721 0.01265 -0.1180 0.7159 0.0291
-2.250 0.3655 0.01624 0.01162 -0.1184 0.7031 0.0294
-2.000 0.3932 0.01548 0.01074 -0.1186 0.6897 0.0299
-1.750 0.4212 0.01477 0.00989 -0.1188 0.6762 0.0305
-1.500 0.4496 0.01405 0.00899 -0.1188 0.6622 0.0316
-1.250 0.4790 0.01435 0.00900 -0.1185 0.6471 0.0335
-1.000 0.2166 0.02232 0.01835 -0.0778 0.6578 0.0269
-0.750 0.5348 0.01204 0.00640 -0.1189 0.6167 0.0355
-0.500 0.5628 0.01168 0.00592 -0.1189 0.6018 0.0368
0.250 0.5136 0.01258 0.00668 -0.0882 0.5732 0.0335
0.500 0.6766 0.01004 0.00368 -0.1185 0.5517 0.0340
0.750 0.7044 0.00959 0.00321 -0.1184 0.5400 0.0326
1.000 0.7324 0.00937 0.00295 -0.1184 0.5289 0.0325
1.250 0.7604 0.00928 0.00281 -0.1183 0.5187 0.0328
1.500 0.7883 0.00915 0.00264 -0.1183 0.5085 0.0328
1.750 0.8164 0.00906 0.00252 -0.1183 0.4987 0.0330
2.000 0.8441 0.00905 0.00247 -0.1183 0.4872 0.0334
2.250 0.8716 0.00903 0.00238 -0.1182 0.4738 0.0342
2.500 0.8992 0.00903 0.00233 -0.1182 0.4598 0.0353
2.750 0.9268 0.00908 0.00234 -0.1181 0.4466 0.0364
3.000 0.9543 0.00915 0.00238 -0.1181 0.4348 0.0380
3.250 0.9815 0.00925 0.00243 -0.1180 0.4235 0.0401
3.750 1.0313 0.00784 0.00285 -0.1174 0.4010 1.0000
4.000 1.0583 0.00803 0.00295 -0.1172 0.3897 1.0000
4.250 1.0848 0.00824 0.00308 -0.1171 0.3776 1.0000
4.500 1.1113 0.00845 0.00322 -0.1169 0.3652 1.0000
4.750 1.1381 0.00864 0.00335 -0.1167 0.3548 1.0000
5.000 1.1644 0.00885 0.00351 -0.1165 0.3454 1.0000
5.250 1.1911 0.00903 0.00366 -0.1164 0.3376 1.0000
5.500 1.2173 0.00924 0.00383 -0.1162 0.3303 1.0000
5.750 1.2438 0.00942 0.00399 -0.1161 0.3230 1.0000
6.000 1.2696 0.00965 0.00418 -0.1158 0.3149 1.0000
6.250 1.2957 0.00985 0.00436 -0.1156 0.3068 1.0000
6.500 1.3213 0.01008 0.00456 -0.1153 0.2980 1.0000
6.750 1.3464 0.01034 0.00477 -0.1150 0.2873 1.0000
7.000 1.3715 0.01060 0.00499 -0.1147 0.2752 1.0000
7.250 1.3957 0.01092 0.00524 -0.1142 0.2600 1.0000
7.500 1.4189 0.01132 0.00554 -0.1136 0.2417 1.0000
7.750 1.4403 0.01184 0.00592 -0.1127 0.2152 1.0000
8.000 1.4594 0.01253 0.00642 -0.1115 0.1853 1.0000
8.250 1.4796 0.01310 0.00688 -0.1104 0.1674 1.0000
8.750 1.5211 0.01406 0.00773 -0.1085 0.1443 1.0000
9.000 1.5419 0.01450 0.00814 -0.1075 0.1349 1.0000
9.250 1.5615 0.01500 0.00859 -0.1064 0.1253 1.0000
9.500 1.5803 0.01551 0.00906 -0.1051 0.1159 1.0000
9.750 1.5986 0.01600 0.00953 -0.1038 0.1069 1.0000
10.000 1.6136 0.01659 0.01006 -0.1018 0.0960 1.0000
10.250 1.6235 0.01742 0.01078 -0.0992 0.0801 1.0000
10.500 1.6321 0.01837 0.01163 -0.0964 0.0658 1.0000
10.750 1.6425 0.01925 0.01248 -0.0941 0.0575 1.0000
11.000 1.6523 0.02020 0.01340 -0.0918 0.0504 1.0000
11.250 1.6623 0.02118 0.01435 -0.0896 0.0428 1.0000
11.500 1.6591 0.02309 0.01611 -0.0861 0.0203 1.0000
11.750 1.6642 0.02453 0.01758 -0.0836 0.0163 1.0000
12.000 1.6721 0.02582 0.01894 -0.0817 0.0151 1.0000
12.250 1.6792 0.02722 0.02040 -0.0798 0.0140 1.0000
12.500 1.6884 0.02849 0.02174 -0.0783 0.0136 1.0000
12.750 1.6962 0.02992 0.02325 -0.0767 0.0131 1.0000
13.000 1.7021 0.03154 0.02495 -0.0752 0.0126 1.0000
13.250 1.7061 0.03339 0.02688 -0.0736 0.0122 1.0000
13.500 1.7075 0.03555 0.02912 -0.0720 0.0117 1.0000
13.750 1.7050 0.03816 0.03185 -0.0704 0.0113 1.0000
14.000 1.7094 0.04017 0.03394 -0.0694 0.0111 1.0000
14.250 1.7122 0.04242 0.03627 -0.0684 0.0109 1.0000
14.500 1.7133 0.04492 0.03886 -0.0676 0.0107 1.0000
14.750 1.7132 0.04765 0.04168 -0.0669 0.0105 1.0000
15.000 1.7120 0.05060 0.04473 -0.0663 0.0103 1.0000
15.250 1.7095 0.05383 0.04806 -0.0660 0.0101 1.0000
15.500 1.7058 0.05731 0.05163 -0.0658 0.0099 1.0000
15.750 1.7006 0.06105 0.05548 -0.0657 0.0098 1.0000
16.000 1.6937 0.06514 0.05968 -0.0659 0.0096 1.0000
16.250 1.6853 0.06954 0.06418 -0.0663 0.0095 1.0000
16.500 1.6735 0.07447 0.06923 -0.0669 0.0093 1.0000
16.750 1.6598 0.07979 0.07467 -0.0677 0.0092 1.0000
17.000 1.6431 0.08569 0.08070 -0.0688 0.0091 1.0000
17.250 1.6253 0.09183 0.08697 -0.0701 0.0090 1.0000
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