GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 365 AIRFOIL (goe365-il) Reynolds number: 100,000 Max Cl/Cd: 55.09 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe365-il-100000-n5.txt Download as CSV file: xf-goe365-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 365 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 -0.2547 0.11770 0.11289 -0.0399 1.0000 0.0418
-10.000 -0.2579 0.11582 0.11109 -0.0389 1.0000 0.0433
-9.750 -0.2654 0.11431 0.10967 -0.0374 1.0000 0.0444
-9.500 -0.2563 0.11079 0.10618 -0.0439 0.9934 0.0465
-9.250 -0.2474 0.10718 0.10259 -0.0521 0.9844 0.0470
-9.000 -0.2378 0.10331 0.09873 -0.0593 0.9744 0.0473
-8.750 -0.2190 0.09803 0.09347 -0.0580 0.9701 0.0482
-8.500 -0.1992 0.09418 0.08960 -0.0592 0.9650 0.0496
-8.250 -0.1847 0.09074 0.08616 -0.0620 0.9564 0.0516
-8.000 -0.1718 0.08708 0.08250 -0.0672 0.9476 0.0551
-7.750 -0.1676 0.08288 0.07825 -0.0808 0.9307 0.0575
-7.500 -0.1535 0.07754 0.07286 -0.0874 0.9227 0.0584
-7.250 -0.1323 0.07417 0.06954 -0.0849 0.9206 0.0603
-7.000 -0.1190 0.07108 0.06642 -0.0867 0.9110 0.0622
-6.750 -0.0987 0.06710 0.06235 -0.0919 0.9049 0.0651
-6.500 -0.0875 0.06404 0.05875 -0.1016 0.8907 0.0703
-6.000 -0.0566 0.05676 0.05169 -0.1004 0.8789 0.0756
-5.750 -0.0380 0.05576 0.04992 -0.1050 0.8696 0.0849
-5.500 -0.0244 0.05057 0.04497 -0.1047 0.8633 0.0866
-5.250 -0.0031 0.04765 0.04203 -0.1053 0.8585 0.0889
-5.000 0.0160 0.04231 0.03569 -0.1051 0.8498 0.0583
-4.750 0.0380 0.03948 0.03287 -0.1053 0.8445 0.0563
-4.500 0.0603 0.03675 0.02991 -0.1054 0.8394 0.0540
-4.250 0.0776 0.03451 0.02736 -0.1041 0.8318 0.0522
-4.000 0.1035 0.03228 0.02475 -0.1040 0.8269 0.0518
-3.750 0.1242 0.03080 0.02298 -0.1029 0.8200 0.0530
-3.500 0.1485 0.02913 0.02095 -0.1022 0.8139 0.0527
-3.000 0.1982 0.02632 0.01750 -0.1007 0.8014 0.0519
-2.750 0.2268 0.02516 0.01606 -0.1005 0.7962 0.0526
-2.500 0.2523 0.02433 0.01499 -0.0999 0.7900 0.0543
-2.250 0.2779 0.02349 0.01395 -0.0991 0.7835 0.0548
-2.000 0.3090 0.02254 0.01281 -0.0993 0.7789 0.0550
-1.750 0.3318 0.02195 0.01211 -0.0982 0.7717 0.0553
-1.500 0.3598 0.02129 0.01133 -0.0979 0.7658 0.0558
-1.250 0.3885 0.02071 0.01066 -0.0977 0.7604 0.0567
-1.000 0.4112 0.02033 0.01026 -0.0966 0.7529 0.0585
-0.750 0.4397 0.01968 0.00964 -0.0965 0.7474 0.0606
-0.500 0.4612 0.01940 0.00937 -0.0952 0.7398 0.0618
-0.250 0.4872 0.01906 0.00898 -0.0945 0.7332 0.0633
0.000 0.5124 0.01883 0.00870 -0.0938 0.7263 0.0651
0.250 0.5366 0.01868 0.00847 -0.0929 0.7185 0.0674
0.500 0.5650 0.01847 0.00817 -0.0927 0.7119 0.0720
0.750 0.5879 0.01838 0.00808 -0.0916 0.7030 0.0798
1.000 0.6175 0.01816 0.00784 -0.0917 0.6959 0.0955
1.500 0.7142 0.01604 0.00780 -0.0999 0.6746 1.0000
1.750 0.7358 0.01604 0.00764 -0.0983 0.6613 1.0000
2.000 0.7562 0.01605 0.00752 -0.0966 0.6468 1.0000
2.250 0.7761 0.01610 0.00746 -0.0947 0.6318 1.0000
2.500 0.7965 0.01616 0.00743 -0.0931 0.6174 1.0000
2.750 0.8171 0.01626 0.00744 -0.0915 0.6035 1.0000
3.000 0.8375 0.01638 0.00749 -0.0900 0.5893 1.0000
3.250 0.8583 0.01651 0.00754 -0.0885 0.5746 1.0000
3.500 0.8793 0.01665 0.00758 -0.0870 0.5598 1.0000
3.750 0.9002 0.01681 0.00764 -0.0856 0.5442 1.0000
4.000 0.9209 0.01701 0.00775 -0.0841 0.5288 1.0000
4.250 0.9414 0.01725 0.00789 -0.0827 0.5135 1.0000
4.500 0.9614 0.01752 0.00807 -0.0812 0.4981 1.0000
4.750 0.9809 0.01782 0.00830 -0.0796 0.4828 1.0000
5.000 0.9999 0.01815 0.00855 -0.0780 0.4672 1.0000
5.250 1.0183 0.01851 0.00883 -0.0763 0.4515 1.0000
5.500 1.0360 0.01890 0.00915 -0.0746 0.4359 1.0000
5.750 1.0529 0.01932 0.00950 -0.0727 0.4198 1.0000
6.000 1.0689 0.01977 0.00988 -0.0707 0.4036 1.0000
6.250 1.0842 0.02024 0.01028 -0.0687 0.3875 1.0000
6.500 1.0984 0.02073 0.01073 -0.0664 0.3715 1.0000
6.750 1.1118 0.02123 0.01119 -0.0641 0.3568 1.0000
7.000 1.1245 0.02177 0.01168 -0.0617 0.3422 1.0000
7.250 1.1377 0.02234 0.01222 -0.0595 0.3291 1.0000
7.500 1.1504 0.02294 0.01280 -0.0572 0.3163 1.0000
7.750 1.1635 0.02358 0.01340 -0.0551 0.3055 1.0000
8.000 1.1773 0.02423 0.01404 -0.0532 0.2957 1.0000
8.250 1.1912 0.02490 0.01471 -0.0514 0.2867 1.0000
8.500 1.2045 0.02562 0.01543 -0.0496 0.2788 1.0000
8.750 1.2191 0.02633 0.01618 -0.0480 0.2711 1.0000
9.000 1.2323 0.02710 0.01693 -0.0463 0.2643 1.0000
9.250 1.2469 0.02785 0.01774 -0.0448 0.2579 1.0000
9.500 1.2605 0.02865 0.01858 -0.0432 0.2517 1.0000
9.750 1.2744 0.02948 0.01943 -0.0418 0.2464 1.0000
10.000 1.2888 0.03030 0.02036 -0.0405 0.2409 1.0000
10.250 1.3019 0.03118 0.02127 -0.0390 0.2358 1.0000
10.500 1.3159 0.03206 0.02221 -0.0378 0.2311 1.0000
10.750 1.3289 0.03299 0.02329 -0.0364 0.2261 1.0000
11.000 1.3418 0.03395 0.02431 -0.0352 0.2217 1.0000
11.250 1.3562 0.03488 0.02528 -0.0340 0.2180 1.0000
11.500 1.3689 0.03592 0.02651 -0.0329 0.2139 1.0000
11.750 1.3810 0.03698 0.02772 -0.0317 0.2099 1.0000
12.000 1.3925 0.03807 0.02886 -0.0305 0.2057 1.0000
12.250 1.3999 0.03937 0.03031 -0.0291 0.2006 1.0000
12.500 1.4041 0.04085 0.03194 -0.0276 0.1947 1.0000
12.750 1.4077 0.04235 0.03344 -0.0261 0.1886 1.0000
13.000 1.4074 0.04425 0.03558 -0.0248 0.1818 1.0000
13.250 1.4086 0.04607 0.03748 -0.0236 0.1759 1.0000
13.500 1.4095 0.04809 0.03968 -0.0226 0.1700 1.0000
13.750 1.4090 0.05028 0.04204 -0.0217 0.1640 1.0000
14.000 1.4097 0.05242 0.04420 -0.0209 0.1594 1.0000
14.250 1.4077 0.05505 0.04712 -0.0204 0.1526 1.0000
14.500 1.4039 0.05786 0.05004 -0.0200 0.1467 1.0000
14.750 1.4006 0.06088 0.05327 -0.0199 0.1397 1.0000
15.000 1.3959 0.06415 0.05671 -0.0200 0.1336 1.0000
15.250 1.3909 0.06767 0.06044 -0.0203 0.1265 1.0000
15.500 1.3826 0.07175 0.06466 -0.0209 0.1191 1.0000
15.750 1.3707 0.07651 0.06954 -0.0220 0.1096 1.0000
16.000 1.3563 0.08185 0.07496 -0.0234 0.1009 1.0000
16.250 1.3406 0.08758 0.08076 -0.0252 0.0952 1.0000
16.500 1.3222 0.09398 0.08723 -0.0274 0.0904 1.0000
16.750 1.3034 0.10065 0.09398 -0.0299 0.0865 1.0000
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