GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 500,000 Max Cl/Cd: 157.25 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe804-il-500000-n5.txt Download as CSV file: xf-goe804-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.0620 0.08597 0.08342 -0.1069 0.9505 0.0086
-8.000 -0.0519 0.08284 0.08029 -0.1090 0.9476 0.0082
-7.750 -0.0388 0.07996 0.07740 -0.1114 0.9457 0.0086
-7.500 -0.0240 0.07677 0.07421 -0.1148 0.9441 0.0098
-7.250 -0.0082 0.07357 0.07101 -0.1182 0.9426 0.0091
-7.000 -0.0072 0.07064 0.06810 -0.1201 0.9349 0.0104
-6.750 0.0106 0.06711 0.06458 -0.1247 0.9322 0.0104
-6.250 0.0547 0.05860 0.05603 -0.1359 0.9288 0.0075
-6.000 0.0872 0.05437 0.05177 -0.1445 0.9276 0.0073
-5.750 0.0956 0.05173 0.04912 -0.1461 0.9216 0.0071
-5.250 0.2637 0.01492 0.01053 -0.2069 0.9175 0.0072
-5.000 0.3022 0.01306 0.00820 -0.2102 0.9168 0.0081
-4.750 0.3370 0.01212 0.00705 -0.2123 0.9160 0.0087
-4.500 0.3722 0.01127 0.00598 -0.2143 0.9150 0.0096
-4.250 0.4077 0.01054 0.00505 -0.2163 0.9139 0.0107
-4.000 0.4427 0.01007 0.00450 -0.2181 0.9127 0.0127
-3.750 0.4682 0.00970 0.00402 -0.2178 0.9090 0.0145
-3.500 0.4977 0.00936 0.00362 -0.2183 0.9058 0.0178
-3.250 0.5295 0.00902 0.00324 -0.2193 0.9034 0.0248
-3.000 0.5609 0.00885 0.00308 -0.2202 0.9012 0.0367
-2.750 0.5930 0.00876 0.00296 -0.2212 0.8992 0.0452
-2.500 0.6215 0.00875 0.00287 -0.2213 0.8957 0.0497
-2.250 0.6485 0.00856 0.00268 -0.2213 0.8906 0.0554
-2.000 0.6784 0.00844 0.00252 -0.2218 0.8869 0.0598
-1.750 0.7104 0.00831 0.00233 -0.2228 0.8844 0.0627
-1.500 0.7391 0.00821 0.00223 -0.2231 0.8813 0.0665
-1.250 0.7654 0.00815 0.00219 -0.2228 0.8771 0.0695
-1.000 0.7939 0.00809 0.00211 -0.2230 0.8731 0.0732
-0.750 0.8250 0.00800 0.00204 -0.2238 0.8697 0.0815
-0.500 0.8510 0.00797 0.00204 -0.2235 0.8645 0.0922
-0.250 0.8783 0.00794 0.00201 -0.2234 0.8585 0.1034
0.000 0.9077 0.00786 0.00196 -0.2238 0.8529 0.1162
0.250 0.9335 0.00782 0.00197 -0.2234 0.8452 0.1313
0.500 0.9614 0.00772 0.00199 -0.2235 0.8355 0.1853
0.750 0.9883 0.00766 0.00198 -0.2233 0.8220 0.2224
1.000 1.0199 0.00731 0.00212 -0.2246 0.8091 0.4716
1.250 1.0485 0.00684 0.00239 -0.2250 0.7965 0.8100
1.500 1.0707 0.00686 0.00246 -0.2235 0.7802 0.8709
1.750 1.0929 0.00695 0.00250 -0.2222 0.7560 0.8966
2.000 1.1117 0.00716 0.00256 -0.2200 0.7212 0.9199
2.250 1.1249 0.00742 0.00266 -0.2166 0.6792 1.0000
2.500 1.1440 0.00788 0.00291 -0.2148 0.6396 1.0000
2.750 1.1646 0.00828 0.00317 -0.2133 0.6088 1.0000
3.000 1.1816 0.00885 0.00352 -0.2111 0.5592 1.0000
3.250 1.1936 0.00970 0.00399 -0.2080 0.4802 1.0000
3.500 1.2092 0.01046 0.00446 -0.2057 0.4265 1.0000
3.750 1.2285 0.01102 0.00487 -0.2042 0.3907 1.0000
4.000 1.2466 0.01165 0.00531 -0.2024 0.3428 1.0000
4.500 1.2726 0.01376 0.00660 -0.1972 0.1924 1.0000
4.750 1.2857 0.01491 0.00731 -0.1947 0.1104 1.0000
5.000 1.3025 0.01574 0.00794 -0.1928 0.0685 1.0000
5.250 1.3209 0.01643 0.00853 -0.1912 0.0483 1.0000
5.500 1.3375 0.01730 0.00924 -0.1893 0.0183 1.0000
5.750 1.3560 0.01800 0.00996 -0.1876 0.0125 1.0000
6.000 1.3748 0.01866 0.01066 -0.1860 0.0098 1.0000
6.250 1.3930 0.01937 0.01143 -0.1843 0.0084 1.0000
6.500 1.4113 0.02007 0.01221 -0.1827 0.0074 1.0000
6.750 1.4282 0.02093 0.01313 -0.1808 0.0065 1.0000
7.000 1.4460 0.02167 0.01395 -0.1792 0.0058 1.0000
7.250 1.4626 0.02252 0.01487 -0.1773 0.0052 1.0000
7.500 1.4772 0.02358 0.01600 -0.1751 0.0049 1.0000
7.750 1.4909 0.02473 0.01726 -0.1728 0.0046 1.0000
8.000 1.5042 0.02593 0.01860 -0.1705 0.0043 1.0000
8.250 1.5172 0.02717 0.01995 -0.1681 0.0041 1.0000
8.500 1.5307 0.02840 0.02128 -0.1660 0.0038 1.0000
8.750 1.5446 0.02949 0.02245 -0.1640 0.0035 1.0000
9.000 1.5550 0.03114 0.02421 -0.1615 0.0033 1.0000
9.250 1.5672 0.03269 0.02595 -0.1592 0.0031 1.0000
9.500 1.5782 0.03454 0.02798 -0.1568 0.0030 1.0000
9.750 1.5891 0.03651 0.03018 -0.1545 0.0029 1.0000
10.000 1.5997 0.03857 0.03245 -0.1522 0.0027 1.0000
10.250 1.6094 0.04065 0.03475 -0.1499 0.0026 1.0000
10.500 1.6174 0.04303 0.03736 -0.1474 0.0025 1.0000
10.750 1.6235 0.04528 0.03982 -0.1449 0.0024 1.0000
11.000 1.6274 0.04785 0.04260 -0.1423 0.0024 1.0000
11.250 1.6281 0.05071 0.04569 -0.1396 0.0023 1.0000
11.500 1.6246 0.05432 0.04957 -0.1366 0.0023 1.0000
11.750 1.6155 0.05870 0.05427 -0.1334 0.0022 1.0000
12.000 1.6044 0.06330 0.05920 -0.1305 0.0022 1.0000
12.250 1.5872 0.06899 0.06529 -0.1277 0.0022 1.0000
12.500 1.5702 0.07447 0.07106 -0.1257 0.0022 1.0000
12.750 1.5540 0.07996 0.07681 -0.1246 0.0022 1.0000
13.000 1.5262 0.08803 0.08524 -0.1243 0.0022 1.0000
13.250 1.5157 0.09307 0.09040 -0.1251 0.0022 1.0000
13.500 1.4842 0.10330 0.10103 -0.1277 0.0021 1.0000
13.750 1.4678 0.11064 0.10852 -0.1309 0.0022 1.0000
14.000 1.4573 0.11714 0.11509 -0.1343 0.0022 1.0000
14.250 1.4296 0.12956 0.12779 -0.1418 0.0022 1.0000
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Polar data table (+)
Polar graphs
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