GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 50,000 Max Cl/Cd: 37.65 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe100-il-50000.txt Download as CSV file: xf-goe100-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 100 (SOPWITH) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4079 0.10620 0.09964 -0.0150 1.0000 0.1463
-7.750 -0.4182 0.10524 0.09882 -0.0168 1.0000 0.1498
-7.500 -0.4158 0.10155 0.09523 -0.0171 1.0000 0.1526
-7.250 -0.4068 0.09765 0.09135 -0.0159 1.0000 0.1596
-7.000 -0.4156 0.09680 0.09062 -0.0206 1.0000 0.1640
-6.500 -0.4067 0.08998 0.08393 -0.0207 1.0000 0.1773
-6.000 -0.3997 0.08430 0.07835 -0.0236 1.0000 0.1921
-5.750 -0.3905 0.07954 0.07362 -0.0191 1.0000 0.2009
-5.500 -0.3857 0.07635 0.07048 -0.0194 1.0000 0.2104
-5.250 -0.3800 0.07336 0.06750 -0.0201 1.0000 0.2224
-5.000 -0.3731 0.07024 0.06441 -0.0199 1.0000 0.2362
-4.750 -0.3655 0.06704 0.06124 -0.0189 1.0000 0.2519
-4.500 -0.3577 0.06424 0.05843 -0.0192 1.0000 0.2763
-4.250 -0.3516 0.06111 0.05536 -0.0166 1.0000 0.3051
-4.000 -0.3464 0.05834 0.05264 -0.0142 1.0000 0.3453
-3.750 -0.3436 0.05517 0.04957 -0.0096 1.0000 0.3875
-3.500 -0.3415 0.05235 0.04683 -0.0051 1.0000 0.4405
-3.250 -0.3380 0.04905 0.04364 0.0000 1.0000 0.4829
-3.000 -0.3306 0.04583 0.04050 0.0042 1.0000 0.5182
-2.750 -0.1544 0.03723 0.02903 -0.0403 1.0000 0.1440
-2.500 -0.1244 0.03441 0.02565 -0.0410 1.0000 0.1467
-2.250 -0.0927 0.03161 0.02226 -0.0415 1.0000 0.1478
-2.000 -0.0617 0.02908 0.01924 -0.0418 1.0000 0.1553
-1.750 -0.0331 0.02730 0.01714 -0.0418 1.0000 0.1816
-1.500 -0.0048 0.02578 0.01536 -0.0418 1.0000 0.2101
-1.250 0.0241 0.02450 0.01378 -0.0415 1.0000 0.2296
-1.000 0.0533 0.02357 0.01260 -0.0414 1.0000 0.2583
-0.750 0.0829 0.02260 0.01160 -0.0413 1.0000 0.2905
-0.500 0.1124 0.02128 0.01070 -0.0414 1.0000 0.3791
-0.250 0.1328 0.01896 0.00979 -0.0389 1.0000 1.0000
0.000 0.1559 0.01929 0.00964 -0.0383 1.0000 1.0000
0.250 0.1782 0.01966 0.00966 -0.0379 1.0000 1.0000
0.500 0.2001 0.02007 0.00984 -0.0375 1.0000 1.0000
0.750 0.2216 0.02053 0.01012 -0.0371 1.0000 1.0000
1.000 0.2427 0.02104 0.01050 -0.0368 1.0000 1.0000
1.250 0.2632 0.02162 0.01099 -0.0366 1.0000 1.0000
1.500 0.2831 0.02229 0.01159 -0.0365 1.0000 1.0000
1.750 0.3021 0.02307 0.01232 -0.0365 1.0000 1.0000
2.000 0.3200 0.02399 0.01323 -0.0366 1.0000 1.0000
2.250 0.3837 0.02509 0.01435 -0.0453 0.9773 1.0000
2.500 0.4685 0.02556 0.01493 -0.0564 0.9430 1.0000
2.750 0.5396 0.02525 0.01479 -0.0637 0.9047 1.0000
3.000 0.6083 0.02429 0.01408 -0.0691 0.8657 1.0000
3.250 0.6656 0.02293 0.01300 -0.0712 0.8233 1.0000
3.500 0.7084 0.02163 0.01185 -0.0703 0.7703 1.0000
3.750 0.7425 0.02066 0.01082 -0.0677 0.7020 1.0000
4.000 0.7719 0.02050 0.01033 -0.0651 0.6265 1.0000
4.250 0.7972 0.02126 0.01064 -0.0631 0.5610 1.0000
4.500 0.8222 0.02235 0.01145 -0.0618 0.5111 1.0000
4.750 0.8466 0.02342 0.01233 -0.0607 0.4724 1.0000
5.000 0.8653 0.02411 0.01281 -0.0587 0.4311 1.0000
5.250 0.8872 0.02492 0.01364 -0.0574 0.4009 1.0000
5.500 0.9086 0.02564 0.01433 -0.0561 0.3736 1.0000
5.750 0.9277 0.02621 0.01485 -0.0545 0.3452 1.0000
6.000 0.9473 0.02679 0.01542 -0.0530 0.3203 1.0000
6.250 0.9703 0.02752 0.01631 -0.0521 0.3034 1.0000
6.500 0.9922 0.02816 0.01711 -0.0510 0.2872 1.0000
6.750 1.0061 0.02834 0.01745 -0.0487 0.2600 1.0000
7.000 1.0259 0.02879 0.01811 -0.0473 0.2444 1.0000
7.250 1.0426 0.02910 0.01867 -0.0454 0.2228 1.0000
7.500 1.0594 0.02950 0.01927 -0.0435 0.1986 1.0000
7.750 1.0758 0.03010 0.02003 -0.0416 0.1609 1.0000
8.000 1.0927 0.03141 0.02123 -0.0398 0.1017 1.0000
8.250 1.1066 0.03347 0.02302 -0.0379 0.0777 1.0000
8.500 1.1189 0.03562 0.02510 -0.0358 0.0691 1.0000
8.750 1.1304 0.03771 0.02733 -0.0336 0.0639 1.0000
9.000 1.1389 0.04003 0.02985 -0.0313 0.0609 1.0000
9.250 1.1496 0.04239 0.03237 -0.0289 0.0598 1.0000
9.500 1.1643 0.04488 0.03512 -0.0268 0.0592 1.0000
9.750 1.1819 0.04777 0.03831 -0.0251 0.0589 1.0000
10.000 1.1989 0.05123 0.04213 -0.0236 0.0590 1.0000
10.250 1.2110 0.05517 0.04645 -0.0219 0.0594 1.0000
10.500 1.2170 0.05941 0.05106 -0.0201 0.0599 1.0000
10.750 1.2158 0.06363 0.05572 -0.0180 0.0604 1.0000
11.000 1.2004 0.06737 0.05991 -0.0150 0.0611 1.0000
11.250 1.1788 0.07172 0.06464 -0.0129 0.0617 1.0000
11.500 1.1531 0.07681 0.07006 -0.0126 0.0622 1.0000
11.750 1.1242 0.08294 0.07646 -0.0144 0.0627 1.0000
12.000 1.0912 0.09081 0.08454 -0.0190 0.0631 1.0000
12.250 1.0509 0.10214 0.09602 -0.0277 0.0638 1.0000
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Polar data table (+)
Polar graphs
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