GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 802 B AIRFOIL (goe802b-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.3 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe802b-il-1000000-n5.txt Download as CSV file: xf-goe802b-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 B 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2492 0.10594 0.10401 -0.0394 0.8922 0.0092
-10.000 -0.2434 0.10258 0.10062 -0.0409 0.8840 0.0096
-9.750 -0.2435 0.09743 0.09543 -0.0433 0.8754 0.0103
-9.500 -0.2344 0.09509 0.09306 -0.0446 0.8679 0.0104
-9.250 -0.2248 0.09275 0.09071 -0.0460 0.8605 0.0105
-9.000 -0.2153 0.09041 0.08833 -0.0474 0.8527 0.0106
-8.750 -0.2057 0.08794 0.08584 -0.0491 0.8458 0.0108
-8.500 -0.1963 0.08535 0.08324 -0.0509 0.8383 0.0110
-8.000 -0.1741 0.07975 0.07759 -0.0564 0.8248 0.0118
-7.750 -0.1599 0.07593 0.07373 -0.0609 0.8174 0.0123
-7.500 -0.1440 0.06997 0.06771 -0.0684 0.8105 0.0131
-7.250 -0.1246 0.06748 0.06520 -0.0717 0.8042 0.0132
-7.000 -0.1042 0.06495 0.06263 -0.0751 0.7973 0.0133
-6.750 -0.0827 0.06232 0.05993 -0.0786 0.7907 0.0136
-6.500 -0.0598 0.05953 0.05711 -0.0823 0.7836 0.0139
-6.250 -0.0360 0.05667 0.05418 -0.0860 0.7758 0.0144
-6.000 -0.0103 0.05320 0.05062 -0.0903 0.7690 0.0150
-5.750 0.0237 0.04637 0.04362 -0.0981 0.7615 0.0161
-5.500 0.0482 0.04408 0.04122 -0.1003 0.7517 0.0162
-5.250 0.0734 0.04224 0.03929 -0.1021 0.7390 0.0164
-5.000 0.0989 0.04052 0.03746 -0.1037 0.7243 0.0166
-4.750 0.1249 0.03879 0.03561 -0.1053 0.7093 0.0170
-4.500 0.1522 0.03664 0.03332 -0.1071 0.6958 0.0175
-4.250 0.1807 0.03420 0.03073 -0.1089 0.6839 0.0179
-4.000 0.2092 0.03180 0.02815 -0.1104 0.6721 0.0183
-3.750 0.2381 0.02940 0.02555 -0.1117 0.6584 0.0187
-3.500 0.2672 0.02693 0.02284 -0.1128 0.6442 0.0190
-3.250 0.2970 0.02398 0.01955 -0.1137 0.6304 0.0197
-3.000 0.3238 0.02286 0.01827 -0.1142 0.6156 0.0199
-2.750 0.3508 0.02198 0.01727 -0.1146 0.6021 0.0201
-2.500 0.3781 0.02111 0.01626 -0.1150 0.5897 0.0204
-2.250 0.4054 0.02024 0.01524 -0.1154 0.5765 0.0207
-2.000 0.4331 0.01928 0.01410 -0.1157 0.5630 0.0211
-1.750 0.4610 0.01829 0.01294 -0.1160 0.5511 0.0213
-1.250 0.5172 0.01629 0.01057 -0.1165 0.5307 0.0217
-0.750 0.5734 0.01195 0.00542 -0.1170 0.5143 0.0230
-0.500 0.6001 0.01124 0.00455 -0.1172 0.5054 0.0234
-0.250 0.6270 0.01089 0.00412 -0.1173 0.4969 0.0236
0.000 0.6539 0.01042 0.00356 -0.1175 0.4874 0.0240
0.250 0.6810 0.01025 0.00333 -0.1176 0.4779 0.0243
0.500 0.7084 0.01012 0.00317 -0.1178 0.4687 0.0246
0.750 0.7355 0.01005 0.00306 -0.1178 0.4598 0.0249
1.000 0.7630 0.00997 0.00298 -0.1180 0.4518 0.0254
1.250 0.7901 0.00995 0.00293 -0.1180 0.4425 0.0260
1.500 0.8176 0.00992 0.00289 -0.1181 0.4345 0.0265
1.750 0.8447 0.00997 0.00289 -0.1181 0.4237 0.0270
2.000 0.8718 0.01004 0.00292 -0.1181 0.4103 0.0275
2.250 0.8983 0.01018 0.00299 -0.1180 0.3930 0.0280
2.500 0.9250 0.01036 0.00311 -0.1179 0.3781 0.0286
2.750 0.9519 0.01053 0.00324 -0.1178 0.3664 0.0297
3.000 0.9787 0.01064 0.00333 -0.1178 0.3561 0.0309
3.250 1.0048 0.01078 0.00343 -0.1177 0.3444 0.0322
3.500 1.0312 0.01086 0.00351 -0.1176 0.3341 0.0347
3.750 1.0576 0.01114 0.00381 -0.1175 0.3227 0.0537
4.000 1.0835 0.01122 0.00387 -0.1174 0.3126 0.0623
4.250 1.1094 0.01136 0.00399 -0.1173 0.3046 0.0653
4.500 1.1361 0.01148 0.00412 -0.1173 0.2990 0.0673
4.750 1.1620 0.01160 0.00422 -0.1172 0.2922 0.0691
5.000 1.1880 0.01175 0.00437 -0.1170 0.2858 0.0712
5.250 1.2141 0.01190 0.00453 -0.1169 0.2796 0.0745
5.500 1.2390 0.01209 0.00469 -0.1167 0.2695 0.0753
5.750 1.2640 0.01224 0.00482 -0.1164 0.2559 0.0758
6.000 1.2881 0.01247 0.00500 -0.1161 0.2403 0.0762
6.250 1.3116 0.01276 0.00521 -0.1156 0.2230 0.0765
6.500 1.3339 0.01314 0.00550 -0.1150 0.2012 0.0770
6.750 1.3543 0.01367 0.00588 -0.1140 0.1748 0.0775
7.000 1.3754 0.01412 0.00625 -0.1132 0.1563 0.0781
7.250 1.3966 0.01454 0.00661 -0.1124 0.1414 0.0786
7.500 1.4177 0.01495 0.00696 -0.1116 0.1291 0.0791
8.000 1.4610 0.01563 0.00760 -0.1101 0.1126 0.0800
8.250 1.4819 0.01600 0.00796 -0.1092 0.1035 0.0807
8.500 1.5009 0.01648 0.00839 -0.1081 0.0921 0.0820
9.000 1.5313 0.01781 0.00955 -0.1045 0.0626 0.0836
9.250 1.5446 0.01829 0.01003 -0.1023 0.0564 0.0843
9.750 1.5731 0.01940 0.01116 -0.0984 0.0477 0.0862
10.000 1.5895 0.01991 0.01170 -0.0970 0.0451 0.0868
10.250 1.6017 0.02069 0.01246 -0.0950 0.0389 0.0869
10.500 1.6007 0.02235 0.01400 -0.0913 0.0165 0.0869
10.750 1.6125 0.02322 0.01492 -0.0895 0.0144 0.0870
11.000 1.6248 0.02408 0.01584 -0.0879 0.0127 0.0872
11.250 1.6378 0.02491 0.01674 -0.0864 0.0121 0.0877
11.500 1.6495 0.02586 0.01774 -0.0849 0.0113 0.0881
11.750 1.6601 0.02692 0.01886 -0.0833 0.0106 0.0883
12.000 1.6694 0.02810 0.02011 -0.0817 0.0099 0.0884
12.250 1.6783 0.02936 0.02144 -0.0802 0.0094 0.0884
12.500 1.6885 0.03055 0.02270 -0.0789 0.0092 0.0885
12.750 1.6976 0.03186 0.02408 -0.0776 0.0089 0.0887
13.000 1.7056 0.03331 0.02559 -0.0763 0.0086 0.0890
13.250 1.7125 0.03488 0.02724 -0.0750 0.0083 0.0894
13.500 1.7183 0.03659 0.02903 -0.0738 0.0080 0.0897
13.750 1.7232 0.03844 0.03095 -0.0726 0.0077 0.0898
14.000 1.7266 0.04050 0.03308 -0.0715 0.0074 0.0899
14.250 1.7286 0.04276 0.03541 -0.0705 0.0071 0.0901
14.500 1.7285 0.04532 0.03806 -0.0695 0.0068 0.0903
14.750 1.7303 0.04780 0.04062 -0.0688 0.0067 0.0906
15.000 1.7321 0.05032 0.04323 -0.0683 0.0066 0.0910
15.250 1.7329 0.05304 0.04604 -0.0679 0.0064 0.0913
15.500 1.7327 0.05597 0.04906 -0.0676 0.0063 0.0915
16.000 1.7289 0.06249 0.05577 -0.0674 0.0060 0.0918
16.250 1.7253 0.06604 0.05941 -0.0674 0.0059 0.0924
16.500 1.7209 0.06979 0.06327 -0.0677 0.0058 0.0930
16.750 1.7155 0.07374 0.06732 -0.0680 0.0057 0.0934
17.000 1.7091 0.07787 0.07155 -0.0685 0.0056 0.0935
17.250 1.7017 0.08220 0.07597 -0.0691 0.0055 0.0937
17.500 1.6936 0.08667 0.08055 -0.0698 0.0054 0.0940
17.750 1.6847 0.09135 0.08532 -0.0707 0.0053 0.0944
18.000 1.6751 0.09615 0.09023 -0.0717 0.0052 0.0948
18.250 1.6645 0.10116 0.09534 -0.0729 0.0052 0.0952
18.500 1.6534 0.10636 0.10064 -0.0743 0.0051 0.0956
18.750 1.6421 0.11164 0.10603 -0.0758 0.0050 0.0958
19.000 1.6302 0.11707 0.11157 -0.0776 0.0050 0.0961
19.250 1.6180 0.12262 0.11722 -0.0795 0.0049 0.0964
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