GOE 447 AIRFOIL (goe447-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 447 AIRFOIL (goe447-il) Reynolds number: 1,000,000 Max Cl/Cd: 126.35 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe447-il-1000000-n5.txt Download as CSV file: xf-goe447-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 447 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0140 0.08956 0.08652 -0.1079 0.7330 0.0176
-9.250 -0.1511 0.02244 0.01841 -0.1747 0.7257 0.0223
-9.000 -0.1278 0.02005 0.01574 -0.1763 0.7220 0.0224
-8.750 -0.1054 0.01783 0.01322 -0.1774 0.7182 0.0227
-8.500 -0.0801 0.01678 0.01202 -0.1778 0.7146 0.0229
-8.250 -0.0540 0.01604 0.01115 -0.1781 0.7113 0.0231
-8.000 -0.0271 0.01535 0.01036 -0.1784 0.7084 0.0232
-7.750 -0.0001 0.01476 0.00967 -0.1786 0.7052 0.0234
-7.500 0.0271 0.01422 0.00902 -0.1788 0.7018 0.0236
-7.250 0.0543 0.01373 0.00843 -0.1790 0.6984 0.0237
-7.000 0.0815 0.01329 0.00788 -0.1791 0.6948 0.0239
-6.750 0.1093 0.01286 0.00737 -0.1793 0.6911 0.0241
-6.500 0.1370 0.01246 0.00688 -0.1795 0.6864 0.0243
-6.250 0.1645 0.01212 0.00643 -0.1795 0.6816 0.0245
-6.000 0.1922 0.01179 0.00601 -0.1796 0.6776 0.0247
-5.750 0.2204 0.01147 0.00563 -0.1798 0.6742 0.0249
-5.500 0.2486 0.01118 0.00527 -0.1800 0.6710 0.0251
-5.250 0.2767 0.01092 0.00494 -0.1801 0.6673 0.0254
-5.000 0.3045 0.01071 0.00464 -0.1801 0.6633 0.0256
-4.750 0.3328 0.01049 0.00437 -0.1803 0.6597 0.0258
-4.500 0.3613 0.01029 0.00412 -0.1804 0.6561 0.0260
-4.250 0.3896 0.01012 0.00390 -0.1806 0.6526 0.0261
-4.000 0.4176 0.00995 0.00368 -0.1806 0.6488 0.0263
-3.750 0.4455 0.00973 0.00340 -0.1807 0.6454 0.0268
-3.500 0.4741 0.00954 0.00320 -0.1809 0.6422 0.0273
-3.250 0.5025 0.00941 0.00304 -0.1811 0.6380 0.0279
-3.000 0.5304 0.00931 0.00291 -0.1811 0.6333 0.0284
-2.750 0.5582 0.00923 0.00279 -0.1811 0.6291 0.0289
-2.500 0.5868 0.00913 0.00267 -0.1813 0.6262 0.0293
-2.250 0.6153 0.00904 0.00257 -0.1815 0.6231 0.0298
-2.000 0.6436 0.00897 0.00248 -0.1816 0.6198 0.0303
-1.750 0.6716 0.00891 0.00240 -0.1816 0.6164 0.0310
-1.250 0.7278 0.00880 0.00227 -0.1818 0.6102 0.0335
-1.000 0.7561 0.00875 0.00222 -0.1820 0.6066 0.0352
-0.750 0.7840 0.00870 0.00219 -0.1820 0.6024 0.0394
-0.500 0.8114 0.00868 0.00221 -0.1820 0.5981 0.0530
-0.250 0.8392 0.00870 0.00225 -0.1821 0.5940 0.0602
0.000 0.8670 0.00873 0.00230 -0.1821 0.5883 0.0640
0.250 0.8936 0.00881 0.00233 -0.1819 0.5810 0.0665
0.500 0.9210 0.00884 0.00236 -0.1819 0.5741 0.0683
0.750 0.9478 0.00889 0.00240 -0.1818 0.5670 0.0708
1.000 0.9747 0.00893 0.00244 -0.1817 0.5615 0.0724
1.250 1.0018 0.00898 0.00248 -0.1816 0.5547 0.0742
1.500 1.0277 0.00908 0.00254 -0.1814 0.5473 0.0759
1.750 1.0542 0.00915 0.00260 -0.1812 0.5385 0.0767
2.000 1.0794 0.00924 0.00265 -0.1808 0.5280 0.0784
2.250 1.1036 0.00938 0.00275 -0.1802 0.5137 0.0808
2.500 1.1264 0.00959 0.00289 -0.1794 0.4946 0.0825
2.750 1.1483 0.00985 0.00305 -0.1783 0.4755 0.0840
3.000 1.1706 0.01008 0.00322 -0.1774 0.4613 0.0855
3.250 1.1930 0.01031 0.00339 -0.1765 0.4495 0.0867
3.750 1.2388 0.01068 0.00372 -0.1749 0.4329 0.0919
4.000 1.2616 0.01085 0.00389 -0.1741 0.4251 0.0972
4.250 1.2825 0.01105 0.00410 -0.1729 0.4176 0.1139
4.500 1.3049 0.01105 0.00434 -0.1721 0.4125 0.2499
4.750 1.3252 0.01119 0.00456 -0.1709 0.4074 0.2932
5.000 1.3453 0.01140 0.00484 -0.1696 0.4008 0.3528
5.500 1.3861 0.01097 0.00555 -0.1674 0.3872 1.0000
5.750 1.4074 0.01122 0.00579 -0.1664 0.3825 1.0000
6.000 1.4287 0.01148 0.00603 -0.1655 0.3765 1.0000
6.250 1.4470 0.01186 0.00637 -0.1640 0.3687 1.0000
6.500 1.4674 0.01216 0.00666 -0.1629 0.3610 1.0000
6.750 1.4849 0.01259 0.00705 -0.1613 0.3522 1.0000
7.000 1.5049 0.01292 0.00738 -0.1602 0.3456 1.0000
7.250 1.5204 0.01347 0.00787 -0.1584 0.3331 1.0000
7.500 1.5322 0.01421 0.00851 -0.1561 0.3119 1.0000
7.750 1.5384 0.01526 0.00941 -0.1530 0.2850 1.0000
8.000 1.5413 0.01657 0.01056 -0.1496 0.2558 1.0000
8.250 1.5418 0.01809 0.01193 -0.1460 0.2266 1.0000
8.500 1.5458 0.01950 0.01322 -0.1431 0.2043 1.0000
8.750 1.5548 0.02065 0.01431 -0.1409 0.1913 1.0000
9.000 1.5654 0.02173 0.01536 -0.1391 0.1818 1.0000
9.250 1.5763 0.02283 0.01643 -0.1373 0.1736 1.0000
9.500 1.5878 0.02390 0.01750 -0.1357 0.1666 1.0000
9.750 1.6001 0.02493 0.01852 -0.1343 0.1613 1.0000
10.000 1.6110 0.02607 0.01966 -0.1327 0.1563 1.0000
10.250 1.6241 0.02708 0.02068 -0.1314 0.1521 1.0000
10.500 1.6356 0.02823 0.02185 -0.1300 0.1468 1.0000
10.750 1.6435 0.02964 0.02324 -0.1283 0.1391 1.0000
11.000 1.6511 0.03112 0.02469 -0.1266 0.1291 1.0000
11.500 1.6344 0.03679 0.03009 -0.1205 0.0777 1.0000
11.750 1.6376 0.03879 0.03209 -0.1187 0.0703 1.0000
12.000 1.6391 0.04098 0.03427 -0.1169 0.0606 1.0000
12.250 1.6230 0.04484 0.03798 -0.1138 0.0325 1.0000
12.500 1.6230 0.04730 0.04043 -0.1121 0.0246 1.0000
12.750 1.6267 0.04947 0.04263 -0.1108 0.0211 1.0000
13.000 1.6317 0.05153 0.04471 -0.1096 0.0188 1.0000
13.250 1.6370 0.05361 0.04683 -0.1085 0.0174 1.0000
13.500 1.6419 0.05572 0.04898 -0.1074 0.0162 1.0000
13.750 1.6468 0.05788 0.05118 -0.1064 0.0154 1.0000
14.000 1.6523 0.05996 0.05331 -0.1055 0.0147 1.0000
14.250 1.6562 0.06228 0.05568 -0.1046 0.0140 1.0000
14.500 1.6599 0.06462 0.05806 -0.1037 0.0133 1.0000
14.750 1.6620 0.06718 0.06068 -0.1028 0.0127 1.0000
15.000 1.6665 0.06947 0.06302 -0.1020 0.0123 1.0000
15.250 1.6694 0.07196 0.06558 -0.1013 0.0120 1.0000
15.500 1.6724 0.07446 0.06814 -0.1006 0.0116 1.0000
15.750 1.6740 0.07717 0.07090 -0.0999 0.0112 1.0000
16.000 1.6755 0.07991 0.07370 -0.0993 0.0109 1.0000
16.250 1.6759 0.08281 0.07666 -0.0988 0.0106 1.0000
16.500 1.6750 0.08588 0.07979 -0.0983 0.0103 1.0000
16.750 1.6747 0.08886 0.08284 -0.0978 0.0100 1.0000
17.000 1.6747 0.09189 0.08594 -0.0975 0.0098 1.0000
17.250 1.6753 0.09483 0.08895 -0.0972 0.0096 1.0000
17.500 1.6744 0.09801 0.09221 -0.0971 0.0094 1.0000
17.750 1.6739 0.10115 0.09542 -0.0970 0.0092 1.0000
18.000 1.6728 0.10438 0.09871 -0.0969 0.0090 1.0000
18.250 1.6708 0.10775 0.10216 -0.0970 0.0088 1.0000
18.500 1.6692 0.11106 0.10553 -0.0971 0.0085 1.0000
18.750 1.6666 0.11457 0.10911 -0.0974 0.0083 1.0000
19.000 1.6635 0.11817 0.11278 -0.0978 0.0082 1.0000
19.250 1.6606 0.12176 0.11643 -0.0983 0.0080 1.0000
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