GOE 804 (EA 8) AIRFOIL (goe804-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 804 (EA 8) AIRFOIL (goe804-il) Reynolds number: 200,000 Max Cl/Cd: 107.09 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe804-il-200000.txt Download as CSV file: xf-goe804-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4130 0.11755 0.11433 -0.0165 1.0000 0.0298
-7.500 -0.4220 0.11648 0.11331 -0.0155 1.0000 0.0299
-7.250 -0.4342 0.11567 0.11256 -0.0139 1.0000 0.0300
-7.000 -0.4398 0.11400 0.11092 -0.0137 1.0000 0.0300
-6.750 -0.4403 0.11171 0.10865 -0.0151 1.0000 0.0301
-6.500 -0.4336 0.10869 0.10565 -0.0180 0.9994 0.0301
-6.250 -0.4225 0.10165 0.09862 -0.0143 0.9970 0.0311
-6.000 -0.3999 0.09770 0.09464 -0.0169 0.9928 0.0327
-5.750 -0.3803 0.09416 0.09109 -0.0216 0.9879 0.0350
-5.500 -0.3547 0.09001 0.08692 -0.0290 0.9828 0.0371
-5.250 -0.3121 0.08568 0.08253 -0.0454 0.9758 0.0393
-5.000 -0.2622 0.08055 0.07727 -0.0607 0.9708 0.0398
-4.750 -0.2418 0.07422 0.07093 -0.0660 0.9661 0.0403
-4.500 -0.2312 0.07034 0.06706 -0.0647 0.9632 0.0414
-4.250 -0.2030 0.06685 0.06354 -0.0683 0.9608 0.0429
-4.000 -0.1803 0.06349 0.06014 -0.0718 0.9553 0.0449
-3.750 -0.0904 0.05769 0.05390 -0.0937 0.9524 0.0518
-3.500 -0.0586 0.05137 0.04756 -0.0996 0.9508 0.0537
-3.250 -0.0239 0.04845 0.04458 -0.1036 0.9489 0.0564
-3.000 0.0611 0.04299 0.03838 -0.1195 0.9487 0.0660
-2.750 0.0941 0.03963 0.03514 -0.1232 0.9478 0.0688
-2.500 0.1364 0.03698 0.03217 -0.1281 0.9444 0.0811
-2.250 0.2152 0.03055 0.02493 -0.1394 0.9481 0.0620
-2.000 0.2693 0.02733 0.02101 -0.1452 0.9481 0.0628
-1.750 0.3172 0.02554 0.01858 -0.1491 0.9476 0.0656
-1.500 0.3425 0.02461 0.01764 -0.1494 0.9419 0.0729
-1.250 0.3802 0.02402 0.01669 -0.1513 0.9391 0.0788
-1.000 0.4194 0.02335 0.01601 -0.1539 0.9370 0.0885
-0.750 0.4622 0.02274 0.01529 -0.1569 0.9352 0.0958
-0.500 0.4888 0.02252 0.01507 -0.1568 0.9284 0.1036
-0.250 0.5276 0.02199 0.01457 -0.1591 0.9250 0.1103
0.000 0.5709 0.02153 0.01416 -0.1622 0.9226 0.1222
0.250 0.6042 0.02117 0.01391 -0.1634 0.9166 0.1371
0.500 0.6437 0.02069 0.01366 -0.1658 0.9120 0.1839
0.750 0.6731 0.01876 0.01358 -0.1656 0.9095 1.0000
1.000 0.7056 0.01876 0.01346 -0.1664 0.9038 1.0000
1.250 0.7393 0.01868 0.01331 -0.1674 0.8980 1.0000
1.500 0.7806 0.01843 0.01303 -0.1698 0.8953 1.0000
1.750 0.8104 0.01836 0.01294 -0.1700 0.8879 1.0000
2.000 0.8493 0.01802 0.01260 -0.1718 0.8833 1.0000
2.250 0.8914 0.01762 0.01224 -0.1742 0.8809 1.0000
2.500 0.9191 0.01750 0.01216 -0.1739 0.8726 1.0000
2.750 0.9687 0.01637 0.01108 -0.1771 0.8683 1.0000
3.000 1.0264 0.01491 0.00972 -0.1817 0.8655 1.0000
3.250 1.0520 0.01461 0.00950 -0.1807 0.8545 1.0000
3.500 1.0859 0.01400 0.00898 -0.1811 0.8442 1.0000
3.750 1.1235 0.01333 0.00841 -0.1822 0.8339 1.0000
4.000 1.1508 0.01294 0.00815 -0.1814 0.8184 1.0000
4.250 1.1837 0.01239 0.00767 -0.1815 0.7963 1.0000
4.500 1.2142 0.01200 0.00732 -0.1811 0.7607 1.0000
4.750 1.2615 0.01178 0.00657 -0.1836 0.6490 1.0000
5.000 1.2697 0.01302 0.00705 -0.1792 0.5177 1.0000
5.500 1.2709 0.01622 0.00887 -0.1689 0.2878 1.0000
5.750 1.2748 0.01801 0.01002 -0.1649 0.1901 1.0000
6.000 1.2811 0.01996 0.01131 -0.1614 0.1002 1.0000
6.250 1.2947 0.02131 0.01250 -0.1589 0.0732 1.0000
6.500 1.3053 0.02293 0.01406 -0.1559 0.0584 1.0000
6.750 1.3196 0.02425 0.01546 -0.1534 0.0496 1.0000
7.000 1.3316 0.02640 0.01760 -0.1508 0.0441 1.0000
7.250 1.3514 0.02756 0.01889 -0.1492 0.0399 1.0000
7.500 1.3699 0.02887 0.02019 -0.1478 0.0357 1.0000
7.750 1.4025 0.03163 0.02303 -0.1487 0.0328 1.0000
8.000 1.4371 0.03381 0.02546 -0.1497 0.0308 1.0000
8.250 1.4651 0.03582 0.02766 -0.1496 0.0287 1.0000
8.500 1.4851 0.03740 0.02933 -0.1486 0.0266 1.0000
8.750 1.5163 0.04149 0.03367 -0.1495 0.0254 1.0000
9.000 1.5389 0.04643 0.03907 -0.1486 0.0251 1.0000
9.250 1.5526 0.05038 0.04347 -0.1463 0.0252 1.0000
9.500 1.5626 0.05332 0.04684 -0.1430 0.0257 1.0000
9.750 1.5424 0.06268 0.05743 -0.1345 0.0303 1.0000
10.000 1.5325 0.06811 0.06322 -0.1300 0.0316 1.0000
10.250 1.4800 0.08276 0.07902 -0.1189 0.0539 1.0000
10.500 1.4542 0.08647 0.08297 -0.1140 0.0533 1.0000
10.750 1.4289 0.09073 0.08744 -0.1104 0.0528 1.0000
11.000 1.4024 0.09575 0.09266 -0.1081 0.0527 1.0000
11.250 1.3750 0.10161 0.09871 -0.1073 0.0531 1.0000
11.500 1.3473 0.10820 0.10546 -0.1081 0.0535 1.0000
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Polar data table (+)
Polar graphs
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