GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 200,000 Max Cl/Cd: 107.01 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe804-il-200000-n5.txt Download as CSV file: xf-goe804-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1652 0.10128 0.09758 -0.0815 0.9556 0.0188
-7.750 -0.1722 0.10014 0.09649 -0.0791 0.9489 0.0189
-7.500 -0.1680 0.09616 0.09256 -0.0803 0.9459 0.0191
-7.250 -0.1542 0.09162 0.08800 -0.0801 0.9449 0.0197
-7.000 -0.1420 0.08846 0.08484 -0.0815 0.9431 0.0203
-6.750 -0.1426 0.08663 0.08303 -0.0803 0.9386 0.0206
-6.500 -0.1398 0.08448 0.08091 -0.0800 0.9335 0.0210
-6.250 -0.1264 0.08138 0.07781 -0.0828 0.9305 0.0215
-6.000 -0.1078 0.07791 0.07433 -0.0870 0.9284 0.0221
-5.750 -0.1055 0.07576 0.07221 -0.0870 0.9224 0.0224
-5.500 -0.0917 0.07269 0.06913 -0.0902 0.9181 0.0228
-5.250 -0.0679 0.06878 0.06520 -0.0961 0.9154 0.0233
-5.000 -0.0327 0.06283 0.05918 -0.1063 0.9135 0.0170
-4.750 -0.0136 0.05912 0.05544 -0.1113 0.9066 0.0179
-4.500 0.0167 0.05479 0.05105 -0.1175 0.9034 0.0171
-4.250 0.0640 0.04893 0.04505 -0.1285 0.9016 0.0162
-4.000 0.1287 0.04113 0.03698 -0.1437 0.9009 0.0152
-3.750 0.2027 0.03293 0.02832 -0.1594 0.9013 0.0155
-3.500 0.3006 0.02197 0.01594 -0.1790 0.9053 0.0181
-3.250 0.3496 0.01931 0.01260 -0.1844 0.9057 0.0210
-3.000 0.3852 0.01847 0.01150 -0.1863 0.9043 0.0252
-2.750 0.4207 0.01773 0.01057 -0.1881 0.9031 0.0313
-2.500 0.4550 0.01730 0.00998 -0.1895 0.9018 0.0404
-2.250 0.4889 0.01701 0.00957 -0.1909 0.9006 0.0518
-2.000 0.5226 0.01679 0.00924 -0.1922 0.8996 0.0618
-1.750 0.5573 0.01650 0.00894 -0.1938 0.8987 0.0706
-1.500 0.5834 0.01640 0.00878 -0.1936 0.8953 0.0757
-1.250 0.6072 0.01641 0.00880 -0.1930 0.8908 0.0814
-1.000 0.6393 0.01618 0.00853 -0.1940 0.8887 0.0866
-0.750 0.6743 0.01585 0.00819 -0.1956 0.8870 0.0922
-0.500 0.7117 0.01545 0.00777 -0.1975 0.8855 0.1016
-0.250 0.7518 0.01496 0.00731 -0.2000 0.8841 0.1186
0.250 0.8064 0.01466 0.00725 -0.2000 0.8738 0.1884
0.500 0.8484 0.01389 0.00715 -0.2034 0.8720 0.4490
0.750 0.8734 0.01283 0.00701 -0.2021 0.8698 0.8944
1.000 0.8847 0.01284 0.00705 -0.1984 0.8609 1.0000
1.250 0.9184 0.01270 0.00688 -0.1995 0.8576 1.0000
1.500 0.9549 0.01253 0.00669 -0.2012 0.8553 1.0000
1.750 0.9733 0.01270 0.00688 -0.1993 0.8464 1.0000
2.000 1.0094 0.01243 0.00662 -0.2008 0.8415 1.0000
2.250 1.0299 0.01251 0.00673 -0.1991 0.8314 1.0000
2.500 1.0592 0.01234 0.00659 -0.1992 0.8215 1.0000
2.750 1.0876 0.01217 0.00647 -0.1990 0.8084 1.0000
3.000 1.1153 0.01207 0.00640 -0.1988 0.7942 1.0000
3.250 1.1440 0.01199 0.00638 -0.1987 0.7783 1.0000
3.500 1.1766 0.01186 0.00629 -0.1995 0.7588 1.0000
3.750 1.2155 0.01169 0.00610 -0.2015 0.7312 1.0000
4.000 1.2520 0.01170 0.00598 -0.2029 0.6887 1.0000
4.250 1.2790 0.01205 0.00616 -0.2025 0.6445 1.0000
4.500 1.2991 0.01262 0.00653 -0.2007 0.5950 1.0000
4.750 1.3055 0.01372 0.00716 -0.1963 0.4971 1.0000
5.000 1.3013 0.01528 0.00808 -0.1901 0.4029 1.0000
5.250 1.2986 0.01707 0.00915 -0.1846 0.2781 1.0000
5.500 1.3043 0.01865 0.01024 -0.1810 0.2031 1.0000
5.750 1.3127 0.02020 0.01128 -0.1779 0.1153 1.0000
6.000 1.3228 0.02172 0.01245 -0.1751 0.0570 1.0000
6.250 1.3357 0.02306 0.01364 -0.1727 0.0257 1.0000
6.500 1.3506 0.02423 0.01486 -0.1704 0.0182 1.0000
6.750 1.3647 0.02545 0.01620 -0.1681 0.0155 1.0000
7.000 1.3788 0.02667 0.01758 -0.1658 0.0137 1.0000
7.250 1.3924 0.02792 0.01894 -0.1636 0.0120 1.0000
7.500 1.4032 0.02949 0.02063 -0.1610 0.0111 1.0000
7.750 1.4150 0.03103 0.02233 -0.1585 0.0104 1.0000
8.000 1.4266 0.03270 0.02414 -0.1560 0.0098 1.0000
8.250 1.4388 0.03435 0.02586 -0.1539 0.0091 1.0000
8.500 1.4518 0.03621 0.02785 -0.1518 0.0084 1.0000
8.750 1.4676 0.03817 0.03004 -0.1500 0.0078 1.0000
9.000 1.4853 0.04035 0.03242 -0.1485 0.0074 1.0000
9.250 1.5039 0.04268 0.03496 -0.1472 0.0071 1.0000
9.500 1.5212 0.04523 0.03774 -0.1458 0.0068 1.0000
9.750 1.5365 0.04808 0.04086 -0.1443 0.0067 1.0000
10.000 1.5457 0.05145 0.04461 -0.1419 0.0064 1.0000
10.250 1.5473 0.05509 0.04882 -0.1384 0.0061 1.0000
10.500 1.5451 0.05898 0.05315 -0.1349 0.0059 1.0000
10.750 1.5381 0.06297 0.05758 -0.1313 0.0056 1.0000
11.000 1.5276 0.06741 0.06239 -0.1278 0.0056 1.0000
11.250 1.5133 0.07219 0.06754 -0.1246 0.0055 1.0000
11.500 1.4971 0.07724 0.07293 -0.1219 0.0056 1.0000
11.750 1.4792 0.08260 0.07859 -0.1200 0.0055 1.0000
12.000 1.4594 0.08851 0.08480 -0.1188 0.0056 1.0000
12.250 1.4390 0.09468 0.09124 -0.1187 0.0056 1.0000
12.500 1.4182 0.10137 0.09819 -0.1197 0.0056 1.0000
12.750 1.3989 0.10837 0.10540 -0.1219 0.0057 1.0000
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Polar data table (+)
Polar graphs
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