GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 500,000 Max Cl/Cd: 118.27 at α=1.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe499-il-500000-n5.txt Download as CSV file: xf-goe499-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 499 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2228 0.09602 0.09365 -0.0693 0.9752 0.0078
-9.250 -0.2128 0.09201 0.08964 -0.0724 0.9706 0.0082
-9.000 -0.2026 0.08644 0.08408 -0.0773 0.9672 0.0093
-8.750 -0.1899 0.08159 0.07922 -0.0824 0.9635 0.0099
-8.500 -0.1738 0.07799 0.07561 -0.0868 0.9585 0.0101
-8.250 -0.1530 0.07512 0.07272 -0.0913 0.9548 0.0108
-8.000 -0.1369 0.07119 0.06878 -0.0962 0.9484 0.0113
-7.750 -0.1234 0.06625 0.06381 -0.1023 0.9399 0.0126
-7.500 -0.1184 0.05655 0.05409 -0.1145 0.9259 0.0147
-7.250 -0.0973 0.05563 0.05314 -0.1163 0.9197 0.0152
-7.000 -0.0766 0.05334 0.05080 -0.1201 0.9132 0.0158
-6.750 -0.0569 0.04994 0.04736 -0.1253 0.9061 0.0168
-6.500 -0.0320 0.04294 0.04026 -0.1366 0.8980 0.0191
-6.250 0.0254 0.01922 0.01516 -0.1712 0.8884 0.0232
-6.000 0.0534 0.01805 0.01387 -0.1726 0.8850 0.0245
-5.750 0.0815 0.01736 0.01303 -0.1734 0.8815 0.0256
-5.500 0.1094 0.01643 0.01190 -0.1742 0.8766 0.0266
-5.250 0.1375 0.01569 0.01098 -0.1748 0.8718 0.0279
-5.000 0.1661 0.01474 0.00979 -0.1755 0.8675 0.0287
-4.750 0.1943 0.01388 0.00873 -0.1760 0.8628 0.0292
-4.500 0.2227 0.01309 0.00773 -0.1764 0.8585 0.0295
-4.250 0.2512 0.01241 0.00686 -0.1768 0.8545 0.0297
-4.000 0.2791 0.01184 0.00617 -0.1770 0.8497 0.0300
-3.750 0.3072 0.01136 0.00556 -0.1772 0.8454 0.0304
-3.250 0.3636 0.01036 0.00432 -0.1775 0.8370 0.0301
-3.000 0.3917 0.00995 0.00382 -0.1776 0.8324 0.0299
-2.750 0.4199 0.00960 0.00337 -0.1777 0.8284 0.0298
-2.500 0.4479 0.00930 0.00301 -0.1778 0.8236 0.0298
-2.250 0.4759 0.00903 0.00270 -0.1779 0.8188 0.0298
-2.000 0.5041 0.00882 0.00240 -0.1779 0.8143 0.0298
-1.750 0.5319 0.00862 0.00217 -0.1779 0.8086 0.0300
-1.500 0.5598 0.00847 0.00197 -0.1779 0.8032 0.0303
-1.250 0.5878 0.00835 0.00179 -0.1779 0.7987 0.0308
-1.000 0.6156 0.00825 0.00167 -0.1779 0.7936 0.0316
-0.750 0.6434 0.00818 0.00157 -0.1778 0.7885 0.0328
-0.500 0.6712 0.00812 0.00148 -0.1777 0.7839 0.0350
-0.250 0.6988 0.00805 0.00142 -0.1777 0.7780 0.0406
0.000 0.7263 0.00790 0.00138 -0.1776 0.7703 0.0836
0.250 0.7535 0.00781 0.00139 -0.1775 0.7609 0.1192
0.500 0.7807 0.00774 0.00143 -0.1774 0.7516 0.1588
0.750 0.8075 0.00770 0.00147 -0.1772 0.7403 0.1992
1.250 0.8597 0.00766 0.00161 -0.1765 0.7035 0.2970
1.500 0.8851 0.00762 0.00172 -0.1760 0.6789 0.3839
1.750 0.9095 0.00769 0.00187 -0.1753 0.6492 0.4716
2.000 0.9293 0.00811 0.00209 -0.1737 0.5862 0.5266
2.250 0.9464 0.00880 0.00247 -0.1717 0.5093 0.5781
2.500 0.9687 0.00906 0.00275 -0.1707 0.4753 0.6521
3.000 1.0112 0.00931 0.00322 -0.1681 0.4107 1.0000
3.250 1.0320 0.00990 0.00352 -0.1669 0.3519 1.0000
3.500 1.0375 0.01207 0.00454 -0.1634 0.1290 1.0000
3.750 1.0537 0.01330 0.00527 -0.1615 0.0252 1.0000
4.000 1.0776 0.01366 0.00565 -0.1608 0.0179 1.0000
4.250 1.1013 0.01404 0.00605 -0.1600 0.0151 1.0000
4.500 1.1238 0.01454 0.00663 -0.1590 0.0118 1.0000
4.750 1.1460 0.01506 0.00722 -0.1579 0.0108 1.0000
5.000 1.1682 0.01555 0.00776 -0.1568 0.0101 1.0000
5.250 1.1895 0.01612 0.00840 -0.1556 0.0093 1.0000
5.500 1.2107 0.01664 0.00895 -0.1545 0.0083 1.0000
5.750 1.2310 0.01723 0.00956 -0.1532 0.0076 1.0000
6.000 1.2463 0.01829 0.01069 -0.1510 0.0071 1.0000
6.250 1.2628 0.01917 0.01164 -0.1490 0.0068 1.0000
6.500 1.2793 0.02002 0.01259 -0.1471 0.0065 1.0000
6.750 1.2936 0.02099 0.01364 -0.1447 0.0062 1.0000
7.000 1.3064 0.02206 0.01479 -0.1421 0.0060 1.0000
7.250 1.3195 0.02319 0.01600 -0.1396 0.0057 1.0000
7.500 1.3344 0.02415 0.01703 -0.1375 0.0054 1.0000
7.750 1.3499 0.02500 0.01793 -0.1356 0.0050 1.0000
8.000 1.3651 0.02575 0.01871 -0.1338 0.0048 1.0000
8.250 1.3784 0.02713 0.02014 -0.1318 0.0045 1.0000
8.500 1.3943 0.02901 0.02215 -0.1300 0.0044 1.0000
8.750 1.4129 0.03068 0.02403 -0.1286 0.0042 1.0000
9.000 1.4356 0.03300 0.02658 -0.1278 0.0040 1.0000
9.250 1.4613 0.03617 0.03006 -0.1275 0.0038 1.0000
9.500 1.4815 0.03972 0.03395 -0.1264 0.0036 1.0000
9.750 1.4931 0.04332 0.03788 -0.1240 0.0036 1.0000
10.000 1.4964 0.04682 0.04170 -0.1206 0.0035 1.0000
10.250 1.4936 0.05035 0.04554 -0.1166 0.0035 1.0000
10.500 1.4868 0.05387 0.04933 -0.1124 0.0035 1.0000
10.750 1.4763 0.05753 0.05326 -0.1083 0.0036 1.0000
11.000 1.4629 0.06143 0.05742 -0.1045 0.0036 1.0000
11.250 1.4476 0.06562 0.06186 -0.1012 0.0036 1.0000
11.500 1.4312 0.07001 0.06647 -0.0986 0.0036 1.0000
11.750 1.4129 0.07477 0.07145 -0.0966 0.0036 1.0000
12.000 1.3938 0.07990 0.07679 -0.0955 0.0036 1.0000
12.250 1.3741 0.08544 0.08252 -0.0953 0.0036 1.0000
12.500 1.3534 0.09153 0.08880 -0.0960 0.0036 1.0000
12.750 1.3309 0.09836 0.09582 -0.0978 0.0037 1.0000
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Polar data table (+)
Polar graphs
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