GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 1,000,000 Max Cl/Cd: 211.36 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe804-il-1000000.txt Download as CSV file: xf-goe804-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.1135 0.08333 0.08152 -0.0998 0.9696 0.0118
-8.000 -0.1027 0.08028 0.07847 -0.1022 0.9663 0.0119
-7.750 -0.0884 0.07649 0.07469 -0.1064 0.9642 0.0120
-7.500 -0.0726 0.07269 0.07088 -0.1107 0.9626 0.0120
-7.250 -0.0585 0.06840 0.06660 -0.1146 0.9615 0.0127
-7.000 -0.0345 0.06524 0.06342 -0.1199 0.9608 0.0131
-6.250 0.1044 0.01777 0.01484 -0.1931 0.9481 0.0119
-6.000 0.1494 0.01166 0.00773 -0.2009 0.9477 0.0130
-5.750 0.1729 0.01112 0.00708 -0.2003 0.9447 0.0136
-5.500 0.2019 0.01058 0.00643 -0.2009 0.9429 0.0144
-5.250 0.2332 0.00998 0.00570 -0.2019 0.9414 0.0155
-5.000 0.2646 0.00974 0.00539 -0.2027 0.9399 0.0164
-4.750 0.2993 0.00868 0.00415 -0.2046 0.9387 0.0185
-4.500 0.3318 0.00836 0.00378 -0.2058 0.9374 0.0202
-4.250 0.3646 0.00806 0.00342 -0.2069 0.9359 0.0220
-4.000 0.3976 0.00759 0.00288 -0.2082 0.9338 0.0252
-3.750 0.4233 0.00750 0.00280 -0.2077 0.9295 0.0283
-3.500 0.4540 0.00724 0.00249 -0.2083 0.9262 0.0317
-3.250 0.4853 0.00712 0.00239 -0.2090 0.9233 0.0366
-3.000 0.5161 0.00717 0.00242 -0.2096 0.9205 0.0396
-2.750 0.5435 0.00690 0.00215 -0.2096 0.9174 0.0447
-2.500 0.5718 0.00682 0.00206 -0.2097 0.9143 0.0484
-2.250 0.6009 0.00678 0.00201 -0.2100 0.9113 0.0513
-2.000 0.6323 0.00660 0.00179 -0.2108 0.9086 0.0542
-1.750 0.6613 0.00646 0.00165 -0.2112 0.9056 0.0585
-1.500 0.6886 0.00637 0.00156 -0.2110 0.9015 0.0610
-1.250 0.7173 0.00629 0.00146 -0.2112 0.8974 0.0639
-1.000 0.7483 0.00621 0.00135 -0.2119 0.8936 0.0666
-0.750 0.7749 0.00613 0.00132 -0.2116 0.8894 0.0753
-0.500 0.8024 0.00606 0.00129 -0.2115 0.8839 0.0915
-0.250 0.8314 0.00599 0.00124 -0.2117 0.8777 0.1101
0.000 0.8578 0.00592 0.00123 -0.2114 0.8714 0.1274
0.250 0.8874 0.00581 0.00125 -0.2118 0.8658 0.1929
0.500 0.9144 0.00568 0.00128 -0.2117 0.8585 0.2606
0.750 0.9477 0.00516 0.00143 -0.2135 0.8521 0.5858
1.000 0.9745 0.00482 0.00165 -0.2133 0.8429 0.8407
1.250 0.9988 0.00484 0.00171 -0.2123 0.8313 0.8782
1.500 1.0221 0.00487 0.00175 -0.2111 0.8171 0.9012
1.750 1.0441 0.00494 0.00177 -0.2096 0.7933 0.9192
2.000 1.0628 0.00515 0.00182 -0.2074 0.7527 0.9329
2.250 1.0763 0.00557 0.00197 -0.2041 0.6937 0.9487
2.500 1.0891 0.00604 0.00219 -0.2007 0.6342 1.0000
2.750 1.1072 0.00664 0.00248 -0.1987 0.5713 1.0000
3.000 1.1204 0.00764 0.00293 -0.1959 0.4585 1.0000
3.250 1.1398 0.00832 0.00330 -0.1943 0.3984 1.0000
3.500 1.1578 0.00916 0.00371 -0.1926 0.3087 1.0000
3.750 1.1755 0.01007 0.00421 -0.1908 0.2292 1.0000
4.000 1.1986 0.01051 0.00452 -0.1900 0.2017 1.0000
4.250 1.2201 0.01110 0.00486 -0.1889 0.1508 1.0000
4.500 1.2393 0.01192 0.00537 -0.1874 0.0966 1.0000
4.750 1.2608 0.01250 0.00579 -0.1864 0.0650 1.0000
5.000 1.2843 0.01288 0.00613 -0.1856 0.0559 1.0000
5.250 1.3075 0.01327 0.00650 -0.1848 0.0490 1.0000
5.500 1.3311 0.01360 0.00684 -0.1841 0.0419 1.0000
5.750 1.3531 0.01410 0.00725 -0.1830 0.0294 1.0000
6.000 1.3748 0.01462 0.00774 -0.1819 0.0220 1.0000
6.250 1.3954 0.01529 0.00841 -0.1805 0.0174 1.0000
6.500 1.4176 0.01568 0.00884 -0.1796 0.0161 1.0000
6.750 1.4385 0.01617 0.00934 -0.1783 0.0144 1.0000
7.000 1.4561 0.01704 0.01028 -0.1763 0.0125 1.0000
7.250 1.4753 0.01765 0.01096 -0.1747 0.0119 1.0000
7.500 1.4946 0.01819 0.01155 -0.1732 0.0112 1.0000
7.750 1.5132 0.01880 0.01223 -0.1715 0.0105 1.0000
8.000 1.5314 0.01945 0.01292 -0.1699 0.0099 1.0000
8.250 1.5489 0.02016 0.01367 -0.1681 0.0093 1.0000
8.500 1.5570 0.02190 0.01556 -0.1646 0.0084 1.0000
8.750 1.5744 0.02260 0.01634 -0.1628 0.0081 1.0000
9.000 1.5912 0.02337 0.01718 -0.1610 0.0079 1.0000
9.250 1.6067 0.02426 0.01815 -0.1590 0.0075 1.0000
9.500 1.6212 0.02528 0.01926 -0.1569 0.0072 1.0000
9.750 1.6356 0.02631 0.02039 -0.1547 0.0069 1.0000
10.000 1.6493 0.02740 0.02156 -0.1526 0.0066 1.0000
10.250 1.6620 0.02861 0.02287 -0.1503 0.0065 1.0000
10.500 1.6745 0.02977 0.02411 -0.1482 0.0062 1.0000
10.750 1.6847 0.03123 0.02567 -0.1457 0.0060 1.0000
11.000 1.6900 0.03352 0.02813 -0.1426 0.0057 1.0000
11.250 1.6857 0.03802 0.03300 -0.1384 0.0055 1.0000
11.500 1.6945 0.03938 0.03450 -0.1360 0.0054 1.0000
11.750 1.7021 0.04096 0.03621 -0.1336 0.0053 1.0000
12.000 1.7097 0.04243 0.03782 -0.1313 0.0051 1.0000
12.250 1.7133 0.04456 0.04011 -0.1287 0.0050 1.0000
12.500 1.7161 0.04672 0.04242 -0.1262 0.0048 1.0000
12.750 1.7150 0.04948 0.04536 -0.1235 0.0047 1.0000
13.000 1.7101 0.05278 0.04889 -0.1208 0.0047 1.0000
13.250 1.7073 0.05573 0.05200 -0.1186 0.0045 1.0000
13.500 1.6941 0.06033 0.05684 -0.1160 0.0045 1.0000
13.750 1.6885 0.06380 0.06047 -0.1144 0.0044 1.0000
14.000 1.6743 0.06875 0.06564 -0.1130 0.0043 1.0000
14.250 1.6570 0.07454 0.07165 -0.1122 0.0044 1.0000
14.500 1.6391 0.08074 0.07807 -0.1123 0.0043 1.0000
14.750 1.6236 0.08694 0.08445 -0.1133 0.0043 1.0000
15.000 1.5990 0.09542 0.09317 -0.1158 0.0043 1.0000
15.250 1.5714 0.10536 0.10335 -0.1200 0.0043 1.0000
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Polar data table (+)
Polar graphs
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