GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 499 AIRFOIL (goe499-il) Reynolds number: 100,000 Max Cl/Cd: 69.63 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe499-il-100000-n5.txt Download as CSV file: xf-goe499-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3447 0.13401 0.12915 -0.0386 1.0000 0.0335
-10.000 -0.3479 0.13186 0.12706 -0.0375 1.0000 0.0335
-9.750 -0.3507 0.12974 0.12498 -0.0364 1.0000 0.0335
-9.500 -0.3384 0.12235 0.11760 -0.0338 1.0000 0.0347
-9.250 -0.3370 0.11976 0.11504 -0.0319 1.0000 0.0357
-9.000 -0.3378 0.11782 0.11314 -0.0301 1.0000 0.0371
-8.750 -0.3305 0.11514 0.11046 -0.0312 0.9983 0.0401
-8.500 -0.3186 0.11196 0.10729 -0.0353 0.9948 0.0438
-8.250 -0.3147 0.11068 0.10605 -0.0423 0.9885 0.0458
-8.000 -0.3069 0.10793 0.10331 -0.0466 0.9832 0.0461
-7.750 -0.2972 0.10463 0.10002 -0.0507 0.9778 0.0463
-7.500 -0.2866 0.10097 0.09637 -0.0546 0.9721 0.0463
-7.250 -0.2734 0.09523 0.09062 -0.0508 0.9722 0.0483
-7.000 -0.2583 0.09243 0.08779 -0.0512 0.9689 0.0526
-6.750 -0.2476 0.09014 0.08554 -0.0601 0.9599 0.0591
-6.250 -0.2156 0.08167 0.07702 -0.0671 0.9528 0.0618
-6.000 -0.2075 0.07898 0.07433 -0.0670 0.9468 0.0632
-5.750 -0.1898 0.07598 0.07130 -0.0699 0.9426 0.0675
-5.250 -0.1466 0.06598 0.06117 -0.0836 0.9325 0.0541
-5.000 -0.1070 0.05829 0.05333 -0.0972 0.9283 0.0494
-4.750 -0.0734 0.05483 0.04975 -0.1034 0.9260 0.0532
-4.500 -0.0293 0.04843 0.04312 -0.1151 0.9229 0.0529
-4.250 0.0332 0.03847 0.03258 -0.1322 0.9206 0.0510
-4.000 0.0841 0.03273 0.02614 -0.1420 0.9189 0.0524
-3.750 0.1264 0.02946 0.02225 -0.1474 0.9171 0.0548
-3.500 0.1668 0.02674 0.01888 -0.1514 0.9156 0.0540
-3.250 0.2044 0.02495 0.01657 -0.1541 0.9139 0.0535
-3.000 0.2408 0.02366 0.01489 -0.1563 0.9123 0.0534
-2.750 0.2747 0.02272 0.01370 -0.1577 0.9098 0.0535
-2.500 0.3006 0.02209 0.01290 -0.1575 0.9039 0.0539
-2.250 0.3383 0.02130 0.01193 -0.1593 0.9000 0.0547
-2.000 0.3813 0.02050 0.01097 -0.1621 0.8971 0.0563
-1.750 0.4080 0.02008 0.01045 -0.1618 0.8887 0.0582
-1.500 0.4478 0.01944 0.00972 -0.1639 0.8849 0.0620
-1.250 0.4787 0.01906 0.00934 -0.1644 0.8795 0.0694
-1.000 0.5083 0.01875 0.00912 -0.1648 0.8743 0.0907
-0.750 0.5430 0.01832 0.00900 -0.1662 0.8712 0.1793
-0.500 0.5728 0.01822 0.00900 -0.1666 0.8667 0.2370
-0.250 0.5996 0.01818 0.00901 -0.1664 0.8608 0.2757
0.000 0.6336 0.01794 0.00881 -0.1675 0.8573 0.3064
0.250 0.6610 0.01777 0.00890 -0.1674 0.8515 0.3731
0.500 0.6898 0.01750 0.00899 -0.1675 0.8460 0.4920
0.750 0.7229 0.01702 0.00884 -0.1682 0.8425 0.6174
1.000 0.7405 0.01651 0.00884 -0.1657 0.8340 1.0000
1.250 0.7739 0.01642 0.00865 -0.1665 0.8294 1.0000
1.500 0.7987 0.01656 0.00877 -0.1658 0.8213 1.0000
1.750 0.8308 0.01647 0.00865 -0.1662 0.8157 1.0000
2.000 0.8558 0.01657 0.00876 -0.1655 0.8068 1.0000
2.250 0.8886 0.01643 0.00863 -0.1660 0.8006 1.0000
2.500 0.9125 0.01656 0.00882 -0.1651 0.7902 1.0000
2.750 0.9408 0.01655 0.00887 -0.1649 0.7815 1.0000
3.000 0.9702 0.01649 0.00888 -0.1648 0.7723 1.0000
3.250 0.9954 0.01652 0.00902 -0.1639 0.7594 1.0000
3.500 1.0217 0.01651 0.00911 -0.1632 0.7455 1.0000
3.750 1.0490 0.01644 0.00915 -0.1626 0.7295 1.0000
4.000 1.0727 0.01612 0.00882 -0.1607 0.6891 1.0000
4.250 1.1008 0.01581 0.00822 -0.1591 0.6154 1.0000
4.500 1.1234 0.01626 0.00819 -0.1572 0.5388 1.0000
4.750 1.1341 0.01751 0.00872 -0.1537 0.4372 1.0000
5.000 1.1339 0.01976 0.00968 -0.1491 0.2322 1.0000
5.250 1.1342 0.02298 0.01155 -0.1453 0.0411 1.0000
5.500 1.1508 0.02411 0.01275 -0.1433 0.0318 1.0000
5.750 1.1672 0.02519 0.01398 -0.1413 0.0287 1.0000
6.000 1.1827 0.02626 0.01526 -0.1391 0.0269 1.0000
6.250 1.1959 0.02746 0.01664 -0.1367 0.0252 1.0000
6.500 1.2058 0.02876 0.01808 -0.1338 0.0231 1.0000
6.750 1.2114 0.03037 0.01980 -0.1304 0.0214 1.0000
7.000 1.2161 0.03234 0.02185 -0.1270 0.0206 1.0000
7.250 1.2283 0.03425 0.02385 -0.1246 0.0201 1.0000
7.500 1.2486 0.03605 0.02573 -0.1233 0.0197 1.0000
7.750 1.2763 0.03810 0.02790 -0.1230 0.0193 1.0000
8.000 1.3049 0.04012 0.03012 -0.1228 0.0182 1.0000
8.250 1.3338 0.04240 0.03266 -0.1228 0.0170 1.0000
8.500 1.3620 0.04525 0.03581 -0.1225 0.0166 1.0000
8.750 1.3850 0.04834 0.03925 -0.1215 0.0165 1.0000
9.000 1.4025 0.05159 0.04289 -0.1198 0.0165 1.0000
9.250 1.4143 0.05498 0.04675 -0.1175 0.0165 1.0000
9.500 1.4209 0.05846 0.05064 -0.1147 0.0166 1.0000
9.750 1.4225 0.06197 0.05454 -0.1116 0.0168 1.0000
10.000 1.4183 0.06537 0.05828 -0.1079 0.0170 1.0000
10.250 1.4099 0.06880 0.06204 -0.1040 0.0171 1.0000
10.500 1.3990 0.07231 0.06584 -0.1005 0.0172 1.0000
10.750 1.3856 0.07603 0.06986 -0.0973 0.0173 1.0000
11.000 1.3704 0.08004 0.07414 -0.0948 0.0173 1.0000
11.250 1.3536 0.08435 0.07872 -0.0928 0.0173 1.0000
11.500 1.3358 0.08904 0.08365 -0.0917 0.0174 1.0000
11.750 1.3172 0.09410 0.08895 -0.0914 0.0175 1.0000
12.000 1.2977 0.09965 0.09471 -0.0920 0.0176 1.0000
12.250 1.2779 0.10570 0.10097 -0.0936 0.0177 1.0000
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Polar data table (+)
Polar graphs
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