GOE 448 AIRFOIL (goe448-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 448 AIRFOIL (goe448-il) Reynolds number: 500,000 Max Cl/Cd: 102.89 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe448-il-500000-n5.txt Download as CSV file: xf-goe448-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 448 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
------ -------- --------- --------- -------- -------- --------
-11.000 0.1684 0.10325 0.09957 -0.1301 0.7542 0.0131
-10.750 0.1766 0.10044 0.09675 -0.1315 0.7503 0.0136
-10.500 0.1767 0.09559 0.09190 -0.1336 0.7464 0.0149
-10.250 0.1894 0.09401 0.09030 -0.1347 0.7422 0.0152
-10.000 0.2015 0.09228 0.08853 -0.1359 0.7384 0.0155
-9.750 0.2122 0.09011 0.08635 -0.1372 0.7347 0.0159
-9.500 0.2217 0.08762 0.08386 -0.1387 0.7306 0.0164
-9.000 0.2320 0.08080 0.07699 -0.1424 0.7227 0.0185
-8.750 0.2459 0.07941 0.07559 -0.1435 0.7190 0.0188
-8.500 0.2585 0.07765 0.07383 -0.1447 0.7152 0.0193
-8.250 0.2689 0.07542 0.07159 -0.1462 0.7112 0.0199
-8.000 0.2770 0.07277 0.06891 -0.1479 0.7073 0.0207
-7.750 0.2756 0.06857 0.06471 -0.1505 0.7037 0.0223
-7.500 0.2907 0.06732 0.06346 -0.1517 0.6998 0.0226
-7.250 0.3065 0.06579 0.06192 -0.1535 0.6958 0.0231
-7.000 0.3216 0.06369 0.05980 -0.1560 0.6921 0.0237
-6.750 0.3368 0.06104 0.05710 -0.1594 0.6887 0.0245
-5.750 0.4748 0.01546 0.00967 -0.2285 0.6752 0.0369
-5.500 0.5027 0.01525 0.00939 -0.2287 0.6721 0.0377
-5.250 0.5309 0.01506 0.00916 -0.2290 0.6688 0.0385
-5.000 0.5588 0.01471 0.00871 -0.2293 0.6651 0.0395
-4.750 0.5867 0.01412 0.00795 -0.2298 0.6614 0.0410
-4.500 0.6145 0.01356 0.00718 -0.2302 0.6580 0.0428
-4.250 0.6421 0.01379 0.00744 -0.2301 0.6548 0.0438
-4.000 0.6698 0.01393 0.00760 -0.2301 0.6515 0.0447
-3.750 0.6974 0.01387 0.00748 -0.2302 0.6479 0.0462
-3.500 0.7251 0.01336 0.00677 -0.2305 0.6443 0.0490
-3.250 0.7521 0.01357 0.00697 -0.2304 0.6409 0.0498
-3.000 0.7794 0.01369 0.00707 -0.2304 0.6378 0.0510
-2.750 0.8071 0.01346 0.00673 -0.2306 0.6345 0.0537
-2.500 0.8344 0.01328 0.00644 -0.2306 0.6310 0.0557
-2.250 0.8610 0.01343 0.00657 -0.2305 0.6274 0.0567
-1.750 0.9148 0.01339 0.00638 -0.2305 0.6211 0.0602
-1.500 0.9420 0.01327 0.00610 -0.2305 0.6177 0.0619
-1.250 0.9684 0.01316 0.00599 -0.2305 0.6141 0.0628
-1.000 0.9944 0.01319 0.00601 -0.2303 0.6106 0.0639
-0.750 1.0204 0.01324 0.00602 -0.2302 0.6074 0.0655
-0.500 1.0468 0.01321 0.00597 -0.2301 0.6041 0.0673
-0.250 1.0727 0.01318 0.00586 -0.2299 0.6001 0.0685
0.000 1.0978 0.01317 0.00576 -0.2296 0.5956 0.0691
0.250 1.1224 0.01309 0.00561 -0.2292 0.5908 0.0697
0.500 1.1471 0.01295 0.00549 -0.2288 0.5851 0.0705
0.750 1.1709 0.01293 0.00546 -0.2283 0.5798 0.0714
1.000 1.1946 0.01296 0.00545 -0.2277 0.5758 0.0721
1.250 1.2197 0.01294 0.00544 -0.2275 0.5724 0.0727
1.500 1.2441 0.01295 0.00545 -0.2270 0.5685 0.0733
1.750 1.2666 0.01299 0.00548 -0.2262 0.5644 0.0738
2.000 1.2877 0.01306 0.00553 -0.2252 0.5604 0.0744
2.250 1.3102 0.01311 0.00559 -0.2244 0.5568 0.0749
2.500 1.3326 0.01318 0.00568 -0.2236 0.5529 0.0755
2.750 1.3545 0.01330 0.00580 -0.2227 0.5486 0.0762
3.000 1.3756 0.01349 0.00597 -0.2218 0.5441 0.0770
3.250 1.3982 0.01364 0.00614 -0.2211 0.5392 0.0775
3.500 1.4196 0.01382 0.00634 -0.2202 0.5336 0.0778
3.750 1.4400 0.01404 0.00654 -0.2192 0.5284 0.0786
4.000 1.4621 0.01421 0.00675 -0.2185 0.5239 0.0794
4.250 1.4836 0.01442 0.00700 -0.2178 0.5190 0.0802
4.500 1.5034 0.01471 0.00729 -0.2167 0.5140 0.0811
4.750 1.5230 0.01501 0.00760 -0.2156 0.5093 0.0819
5.000 1.5432 0.01530 0.00792 -0.2147 0.5037 0.0829
5.250 1.5611 0.01569 0.00831 -0.2133 0.4978 0.0839
5.500 1.5794 0.01607 0.00871 -0.2121 0.4926 0.0849
5.750 1.5985 0.01644 0.00911 -0.2111 0.4870 0.0864
6.250 1.6322 0.01741 0.01010 -0.2083 0.4753 0.0907
6.500 1.6470 0.01801 0.01071 -0.2066 0.4671 0.0939
6.750 1.6596 0.01873 0.01145 -0.2047 0.4569 0.0986
7.000 1.6692 0.01964 0.01243 -0.2024 0.4447 0.1749
7.250 1.6765 0.02072 0.01350 -0.1999 0.4313 0.2032
7.500 1.6869 0.02169 0.01453 -0.1979 0.4189 0.2562
8.000 1.7023 0.02333 0.01706 -0.1934 0.3949 1.0000
8.250 1.7068 0.02480 0.01848 -0.1908 0.3825 1.0000
8.500 1.7107 0.02637 0.02000 -0.1883 0.3691 1.0000
8.750 1.7156 0.02794 0.02153 -0.1859 0.3566 1.0000
9.000 1.7193 0.02963 0.02319 -0.1835 0.3451 1.0000
9.250 1.7209 0.03154 0.02507 -0.1810 0.3330 1.0000
9.500 1.7196 0.03375 0.02721 -0.1783 0.3182 1.0000
9.750 1.7188 0.03597 0.02938 -0.1757 0.3037 1.0000
10.000 1.7182 0.03824 0.03161 -0.1733 0.2890 1.0000
10.250 1.7154 0.04077 0.03408 -0.1707 0.2727 1.0000
10.500 1.7065 0.04392 0.03712 -0.1678 0.2483 1.0000
10.750 1.6798 0.04879 0.04175 -0.1635 0.2036 1.0000
11.000 1.6555 0.05364 0.04641 -0.1597 0.1697 1.0000
11.250 1.6457 0.05718 0.04988 -0.1573 0.1525 1.0000
11.500 1.6390 0.06051 0.05317 -0.1552 0.1373 1.0000
11.750 1.6197 0.06525 0.05775 -0.1524 0.1031 1.0000
12.000 1.5909 0.07117 0.06347 -0.1494 0.0634 1.0000
12.250 1.5659 0.07692 0.06909 -0.1468 0.0227 1.0000
12.500 1.5632 0.08019 0.07239 -0.1456 0.0171 1.0000
12.750 1.5665 0.08274 0.07501 -0.1447 0.0155 1.0000
13.000 1.5685 0.08547 0.07781 -0.1438 0.0145 1.0000
13.250 1.5705 0.08820 0.08061 -0.1429 0.0136 1.0000
13.500 1.5714 0.09112 0.08360 -0.1421 0.0129 1.0000
13.750 1.5748 0.09370 0.08626 -0.1414 0.0124 1.0000
14.000 1.5766 0.09654 0.08918 -0.1408 0.0119 1.0000
14.250 1.5787 0.09932 0.09204 -0.1402 0.0113 1.0000
14.500 1.5791 0.10235 0.09514 -0.1396 0.0108 1.0000
14.750 1.5790 0.10542 0.09829 -0.1391 0.0104 1.0000
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Polar data table (+)
Polar graphs
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