GOE 610-B MOD. AIRFOIL (goe610bm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610-B MOD. AIRFOIL (goe610bm-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.04 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610bm-il-1000000-n5.txt Download as CSV file: xf-goe610bm-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610-B MOD. 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3252 0.11129 0.10965 -0.0201 0.9408 0.0033
-9.000 -0.3201 0.10800 0.10632 -0.0211 0.9266 0.0033
-8.750 -0.3146 0.10474 0.10302 -0.0222 0.9138 0.0033
-8.500 -0.3084 0.10156 0.09980 -0.0235 0.9020 0.0034
-8.250 -0.3019 0.09840 0.09661 -0.0249 0.8906 0.0035
-8.000 -0.2956 0.09512 0.09329 -0.0265 0.8792 0.0036
-7.750 -0.2891 0.09183 0.08996 -0.0281 0.8676 0.0037
-7.500 -0.2828 0.08847 0.08657 -0.0299 0.8547 0.0038
-7.250 -0.2771 0.08511 0.08317 -0.0320 0.8396 0.0039
-7.000 -0.2658 0.08112 0.07911 -0.0359 0.8237 0.0040
-6.750 -0.2520 0.07656 0.07450 -0.0409 0.8078 0.0043
-6.500 -0.2352 0.07152 0.06939 -0.0469 0.7925 0.0044
-6.250 -0.2142 0.06537 0.06315 -0.0550 0.7777 0.0045
-6.000 -0.1858 0.05738 0.05506 -0.0664 0.7649 0.0049
-5.750 -0.1565 0.05294 0.05053 -0.0731 0.7534 0.0051
-5.500 -0.0690 0.01255 0.00770 -0.1129 0.7534 0.0072
-5.250 -0.0398 0.01180 0.00680 -0.1134 0.7439 0.0084
-5.000 -0.0106 0.01097 0.00576 -0.1139 0.7357 0.0097
-4.750 0.0186 0.01050 0.00516 -0.1143 0.7277 0.0114
-4.500 0.0471 0.01073 0.00542 -0.1143 0.7199 0.0132
-4.250 0.0761 0.01052 0.00512 -0.1145 0.7121 0.0148
-4.000 0.1047 0.01073 0.00533 -0.1146 0.7051 0.0159
-3.750 0.1332 0.01110 0.00572 -0.1146 0.6971 0.0169
-3.500 0.1618 0.01129 0.00588 -0.1147 0.6889 0.0182
-3.250 0.1907 0.01117 0.00568 -0.1149 0.6800 0.0197
-3.000 0.2195 0.01114 0.00558 -0.1150 0.6713 0.0211
-2.750 0.2483 0.01114 0.00550 -0.1152 0.6599 0.0220
-2.500 0.2769 0.01122 0.00551 -0.1153 0.6459 0.0225
-2.250 0.3055 0.01130 0.00549 -0.1155 0.6266 0.0229
-2.000 0.3352 0.01023 0.00417 -0.1161 0.6019 0.0247
-1.750 0.3638 0.01006 0.00385 -0.1164 0.5728 0.0255
-1.500 0.3925 0.00993 0.00358 -0.1166 0.5505 0.0260
-1.250 0.4214 0.00977 0.00330 -0.1169 0.5342 0.0263
-1.000 0.4503 0.00959 0.00304 -0.1172 0.5233 0.0265
-0.750 0.4792 0.00944 0.00280 -0.1174 0.5138 0.0267
-0.500 0.5081 0.00932 0.00264 -0.1177 0.5054 0.0271
-0.250 0.5371 0.00920 0.00246 -0.1179 0.4977 0.0271
0.000 0.5661 0.00908 0.00228 -0.1182 0.4911 0.0269
0.250 0.5950 0.00900 0.00215 -0.1184 0.4846 0.0268
0.500 0.6240 0.00893 0.00204 -0.1187 0.4788 0.0268
0.750 0.6528 0.00890 0.00197 -0.1189 0.4726 0.0269
1.000 0.6815 0.00888 0.00192 -0.1191 0.4675 0.0271
1.250 0.7103 0.00886 0.00188 -0.1193 0.4622 0.0275
1.500 0.7389 0.00888 0.00187 -0.1195 0.4564 0.0285
1.750 0.7675 0.00890 0.00187 -0.1197 0.4499 0.0309
2.000 0.7958 0.00896 0.00191 -0.1199 0.4401 0.0335
2.250 0.8242 0.00901 0.00194 -0.1200 0.4306 0.0382
2.500 0.8526 0.00903 0.00202 -0.1203 0.4222 0.0821
2.750 0.8814 0.00890 0.00215 -0.1207 0.4147 0.2159
3.000 0.9102 0.00867 0.00232 -0.1213 0.4081 0.4253
3.500 0.9611 0.00777 0.00255 -0.1206 0.3908 1.0000
3.750 0.9891 0.00792 0.00265 -0.1207 0.3816 1.0000
4.000 1.0166 0.00813 0.00278 -0.1208 0.3641 1.0000
4.250 1.0432 0.00849 0.00296 -0.1208 0.3273 1.0000
4.500 1.0691 0.00897 0.00322 -0.1208 0.2848 1.0000
4.750 1.0912 0.01011 0.00381 -0.1203 0.1855 1.0000
5.000 1.1150 0.01091 0.00430 -0.1200 0.1296 1.0000
5.250 1.1396 0.01153 0.00470 -0.1198 0.0926 1.0000
5.500 1.1606 0.01271 0.00547 -0.1190 0.0201 1.0000
5.750 1.1869 0.01298 0.00576 -0.1189 0.0133 1.0000
6.000 1.2128 0.01329 0.00610 -0.1187 0.0112 1.0000
6.250 1.2381 0.01368 0.00653 -0.1184 0.0089 1.0000
6.500 1.2637 0.01399 0.00688 -0.1182 0.0079 1.0000
6.750 1.2888 0.01434 0.00725 -0.1179 0.0069 1.0000
7.000 1.3130 0.01480 0.00774 -0.1175 0.0059 1.0000
7.250 1.3373 0.01523 0.00820 -0.1171 0.0055 1.0000
7.500 1.3613 0.01566 0.00868 -0.1166 0.0050 1.0000
7.750 1.3849 0.01610 0.00916 -0.1161 0.0045 1.0000
8.000 1.4079 0.01658 0.00966 -0.1156 0.0041 1.0000
8.250 1.4293 0.01724 0.01037 -0.1147 0.0037 1.0000
8.500 1.4511 0.01779 0.01098 -0.1139 0.0035 1.0000
8.750 1.4720 0.01840 0.01165 -0.1130 0.0033 1.0000
9.000 1.4920 0.01906 0.01238 -0.1119 0.0031 1.0000
9.250 1.5112 0.01973 0.01314 -0.1108 0.0029 1.0000
9.500 1.5298 0.02042 0.01388 -0.1096 0.0027 1.0000
9.750 1.5470 0.02116 0.01468 -0.1081 0.0026 1.0000
10.000 1.5622 0.02198 0.01556 -0.1064 0.0025 1.0000
10.250 1.5714 0.02314 0.01681 -0.1037 0.0023 1.0000
10.500 1.5764 0.02436 0.01815 -0.1003 0.0023 1.0000
10.750 1.5827 0.02542 0.01930 -0.0973 0.0022 1.0000
11.000 1.5892 0.02659 0.02057 -0.0945 0.0021 1.0000
11.250 1.5946 0.02796 0.02204 -0.0920 0.0021 1.0000
11.500 1.5994 0.02949 0.02367 -0.0896 0.0020 1.0000
11.750 1.6036 0.03116 0.02545 -0.0875 0.0019 1.0000
12.000 1.6067 0.03305 0.02744 -0.0855 0.0018 1.0000
12.250 1.6077 0.03524 0.02978 -0.0837 0.0018 1.0000
12.500 1.6083 0.03759 0.03223 -0.0821 0.0017 1.0000
12.750 1.6081 0.04016 0.03493 -0.0807 0.0017 1.0000
13.000 1.6075 0.04288 0.03776 -0.0796 0.0016 1.0000
13.250 1.6063 0.04577 0.04076 -0.0787 0.0016 1.0000
13.500 1.6037 0.04895 0.04406 -0.0780 0.0016 1.0000
13.750 1.6009 0.05220 0.04743 -0.0775 0.0015 1.0000
14.000 1.5966 0.05575 0.05109 -0.0771 0.0015 1.0000
14.250 1.5917 0.05948 0.05494 -0.0770 0.0015 1.0000
14.500 1.5872 0.06331 0.05889 -0.0772 0.0015 1.0000
14.750 1.5816 0.06744 0.06313 -0.0775 0.0014 1.0000
15.000 1.5744 0.07193 0.06775 -0.0781 0.0014 1.0000
15.250 1.5674 0.07655 0.07248 -0.0789 0.0014 1.0000
15.500 1.5592 0.08139 0.07744 -0.0799 0.0014 1.0000
15.750 1.5502 0.08645 0.08262 -0.0810 0.0014 1.0000
16.000 1.5405 0.09174 0.08804 -0.0824 0.0014 1.0000
16.250 1.5300 0.09723 0.09366 -0.0839 0.0014 1.0000
16.500 1.5186 0.10293 0.09948 -0.0856 0.0013 1.0000
16.750 1.5058 0.10898 0.10565 -0.0875 0.0013 1.0000
17.000 1.4936 0.11509 0.11189 -0.0896 0.0013 1.0000
17.250 1.4804 0.12149 0.11843 -0.0920 0.0013 1.0000
17.500 1.4670 0.12808 0.12514 -0.0946 0.0013 1.0000
17.750 1.4530 0.13495 0.13215 -0.0976 0.0013 1.0000
18.000 1.4392 0.14200 0.13934 -0.1009 0.0013 1.0000
18.250 1.4243 0.14957 0.14706 -0.1047 0.0013 1.0000
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Polar data table (+)
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