GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 1,000,000 Max Cl/Cd: 147.02 at α=0° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe804-il-1000000-n5.txt Download as CSV file: xf-goe804-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 804 (EA 8) 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0296 0.09451 0.09269 -0.1075 0.9610 0.0047
-10.750 -0.0218 0.09123 0.08942 -0.1089 0.9596 0.0051
-10.500 -0.0134 0.08791 0.08609 -0.1105 0.9584 0.0051
-10.250 -0.0048 0.08397 0.08216 -0.1125 0.9575 0.0055
-10.000 0.0047 0.08039 0.07857 -0.1146 0.9566 0.0055
-9.500 0.0200 0.07373 0.07191 -0.1174 0.9519 0.0055
-9.000 0.0362 0.06585 0.06402 -0.1212 0.9471 0.0038
-8.750 0.0477 0.06194 0.06010 -0.1241 0.9454 0.0038
-8.500 -0.0285 0.08111 0.07922 -0.1196 0.9523 0.0041
-8.250 -0.0144 0.07844 0.07654 -0.1223 0.9484 0.0056
-8.000 0.0007 0.07528 0.07337 -0.1254 0.9459 0.0036
-7.750 0.0942 0.04642 0.04455 -0.1364 0.9343 0.0041
-7.500 0.1116 0.04464 0.04275 -0.1388 0.9313 0.0047
-7.000 0.0764 0.06069 0.05873 -0.1452 0.9314 0.0043
-6.500 0.1824 0.01312 0.00957 -0.2173 0.9122 0.0042
-6.250 0.2125 0.01178 0.00797 -0.2189 0.9104 0.0044
-6.000 0.2424 0.01085 0.00684 -0.2200 0.9085 0.0046
-5.750 0.2727 0.01004 0.00584 -0.2211 0.9065 0.0050
-5.500 0.3032 0.00938 0.00500 -0.2221 0.9046 0.0053
-5.250 0.3339 0.00888 0.00434 -0.2230 0.9024 0.0056
-5.000 0.3650 0.00838 0.00373 -0.2241 0.9002 0.0063
-4.750 0.3958 0.00808 0.00334 -0.2250 0.8980 0.0071
-4.500 0.4243 0.00778 0.00296 -0.2253 0.8958 0.0077
-4.250 0.4530 0.00744 0.00256 -0.2257 0.8930 0.0087
-4.000 0.4817 0.00722 0.00229 -0.2260 0.8897 0.0100
-3.750 0.5116 0.00699 0.00200 -0.2266 0.8852 0.0122
-3.500 0.5400 0.00681 0.00177 -0.2268 0.8802 0.0150
-3.250 0.5682 0.00664 0.00158 -0.2270 0.8756 0.0205
-3.000 0.5972 0.00650 0.00148 -0.2274 0.8727 0.0326
-2.750 0.6261 0.00644 0.00141 -0.2277 0.8701 0.0404
-2.500 0.6543 0.00640 0.00136 -0.2279 0.8673 0.0458
-2.250 0.6816 0.00637 0.00133 -0.2278 0.8638 0.0489
-2.000 0.7097 0.00633 0.00126 -0.2280 0.8604 0.0511
-1.750 0.7382 0.00625 0.00116 -0.2282 0.8558 0.0552
-1.500 0.7655 0.00620 0.00110 -0.2282 0.8492 0.0575
-1.250 0.7930 0.00617 0.00104 -0.2281 0.8426 0.0589
-1.000 0.8205 0.00615 0.00099 -0.2281 0.8364 0.0602
-0.750 0.8469 0.00615 0.00095 -0.2278 0.8247 0.0614
-0.500 0.8726 0.00618 0.00092 -0.2274 0.8084 0.0646
-0.250 0.8984 0.00621 0.00093 -0.2270 0.7922 0.0720
0.000 0.9233 0.00628 0.00097 -0.2264 0.7719 0.0884
0.250 0.9453 0.00649 0.00104 -0.2251 0.7391 0.0987
0.500 0.9656 0.00679 0.00116 -0.2235 0.7012 0.1048
0.750 0.9866 0.00708 0.00132 -0.2221 0.6666 0.1124
1.000 1.0085 0.00736 0.00147 -0.2209 0.6371 0.1191
1.250 1.0310 0.00761 0.00166 -0.2199 0.6074 0.1462
1.500 1.0533 0.00789 0.00189 -0.2189 0.5719 0.2023
1.750 1.0692 0.00857 0.00223 -0.2166 0.4893 0.2239
2.000 1.0915 0.00899 0.00268 -0.2160 0.4269 0.4124
2.250 1.1169 0.00919 0.00296 -0.2158 0.4017 0.5092
2.500 1.1465 0.00911 0.00340 -0.2167 0.3742 0.8172
2.750 1.1636 0.00982 0.00381 -0.2147 0.2961 0.8580
3.000 1.1818 0.01043 0.00421 -0.2129 0.2417 0.8824
3.250 1.2029 0.01071 0.00446 -0.2116 0.2239 0.9090
3.500 1.2177 0.01080 0.00461 -0.2088 0.2115 0.9624
3.750 1.2393 0.01125 0.00493 -0.2077 0.1788 1.0000
4.000 1.2560 0.01218 0.00547 -0.2058 0.1061 1.0000
4.250 1.2762 0.01281 0.00591 -0.2044 0.0678 1.0000
4.500 1.2977 0.01326 0.00629 -0.2033 0.0527 1.0000
4.750 1.3197 0.01362 0.00664 -0.2023 0.0417 1.0000
5.000 1.3379 0.01434 0.00720 -0.2006 0.0152 1.0000
5.250 1.3586 0.01481 0.00765 -0.1993 0.0101 1.0000
5.500 1.3793 0.01524 0.00810 -0.1980 0.0079 1.0000
5.750 1.3997 0.01571 0.00859 -0.1967 0.0065 1.0000
6.000 1.4203 0.01615 0.00905 -0.1954 0.0055 1.0000
6.250 1.4397 0.01669 0.00962 -0.1939 0.0047 1.0000
6.500 1.4594 0.01719 0.01018 -0.1925 0.0043 1.0000
6.750 1.4785 0.01773 0.01076 -0.1910 0.0038 1.0000
7.000 1.4969 0.01837 0.01144 -0.1893 0.0035 1.0000
7.250 1.5145 0.01907 0.01221 -0.1876 0.0032 1.0000
7.500 1.5326 0.01970 0.01290 -0.1859 0.0029 1.0000
7.750 1.5505 0.02034 0.01361 -0.1843 0.0027 1.0000
8.000 1.5678 0.02106 0.01438 -0.1826 0.0025 1.0000
8.250 1.5836 0.02191 0.01530 -0.1806 0.0023 1.0000
8.500 1.5975 0.02298 0.01645 -0.1783 0.0022 1.0000
8.750 1.6131 0.02386 0.01743 -0.1764 0.0021 1.0000
9.000 1.6271 0.02492 0.01859 -0.1742 0.0020 1.0000
9.250 1.6409 0.02598 0.01977 -0.1720 0.0019 1.0000
9.500 1.6539 0.02715 0.02105 -0.1698 0.0018 1.0000
9.750 1.6657 0.02844 0.02246 -0.1674 0.0017 1.0000
10.000 1.6778 0.02969 0.02382 -0.1651 0.0017 1.0000
10.250 1.6904 0.03089 0.02512 -0.1631 0.0016 1.0000
10.500 1.7008 0.03234 0.02668 -0.1607 0.0015 1.0000
10.750 1.7114 0.03376 0.02821 -0.1585 0.0015 1.0000
11.000 1.7181 0.03567 0.03028 -0.1558 0.0014 1.0000
11.250 1.7227 0.03791 0.03270 -0.1529 0.0013 1.0000
11.500 1.7285 0.03995 0.03492 -0.1502 0.0013 1.0000
11.750 1.7339 0.04203 0.03719 -0.1477 0.0012 1.0000
12.000 1.7360 0.04461 0.03997 -0.1449 0.0012 1.0000
12.250 1.7382 0.04712 0.04271 -0.1423 0.0012 1.0000
12.500 1.7379 0.04996 0.04575 -0.1397 0.0011 1.0000
12.750 1.7354 0.05309 0.04910 -0.1371 0.0011 1.0000
13.000 1.7261 0.05729 0.05357 -0.1342 0.0011 1.0000
13.250 1.7183 0.06125 0.05775 -0.1319 0.0011 1.0000
13.500 1.7102 0.06538 0.06209 -0.1300 0.0010 1.0000
13.750 1.6935 0.07095 0.06793 -0.1282 0.0010 1.0000
14.000 1.6659 0.07867 0.07598 -0.1270 0.0010 1.0000
14.250 1.6542 0.08406 0.08157 -0.1270 0.0010 1.0000
14.500 1.6293 0.09215 0.08992 -0.1281 0.0010 1.0000
14.750 1.6112 0.09951 0.09748 -0.1300 0.0010 1.0000
15.000 1.5785 0.11067 0.10891 -0.1344 0.0010 1.0000
15.250 1.5499 0.12202 0.12050 -0.1403 0.0010 1.0000
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Polar data table (+)
Polar graphs
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