GOE 443 AIRFOIL (goe443-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 443 AIRFOIL (goe443-il) Reynolds number: 100,000 Max Cl/Cd: 20.34 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe443-il-100000.txt Download as CSV file: xf-goe443-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 443 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6625 0.09271 0.08795 0.0003 1.0000 0.0645
-8.000 -0.6693 0.08865 0.08385 -0.0054 1.0000 0.0650
-7.750 -0.6745 0.08536 0.08038 -0.0094 1.0000 0.0654
-7.500 -0.6583 0.07932 0.07460 -0.0041 1.0000 0.0703
-7.250 -0.6555 0.07521 0.07044 -0.0067 1.0000 0.0752
-7.000 -0.6566 0.07196 0.06679 -0.0118 1.0000 0.0782
-6.750 -0.5993 0.05633 0.05182 -0.0102 1.0000 0.0955
-6.500 -0.5994 0.05225 0.04740 -0.0129 1.0000 0.1043
-6.250 -0.6320 0.05883 0.05345 -0.0127 1.0000 0.1062
-6.000 -0.6208 0.05527 0.04972 -0.0128 1.0000 0.1193
-5.750 -0.5722 0.03808 0.03317 -0.0118 1.0000 0.1383
-5.500 -0.5938 0.04784 0.04231 -0.0112 1.0000 0.1515
-4.250 -0.4683 0.02904 0.02033 -0.0063 1.0000 0.0646
-4.000 -0.4436 0.02534 0.01631 -0.0051 1.0000 0.0568
-3.750 -0.4161 0.02370 0.01405 -0.0033 1.0000 0.0530
-3.500 -0.3926 0.02130 0.01162 -0.0027 1.0000 0.0618
-3.250 -0.3660 0.01938 0.00947 -0.0014 1.0000 0.0631
-3.000 -0.3403 0.01783 0.00776 -0.0001 1.0000 0.0654
-2.750 -0.3190 0.01597 0.00609 0.0015 1.0000 0.0734
-2.500 -0.2985 0.01468 0.00489 0.0030 1.0000 0.1003
-2.250 -0.1739 0.01092 0.00387 -0.0122 1.0000 1.0000
-2.000 -0.1561 0.01068 0.00344 -0.0108 1.0000 1.0000
-1.750 -0.1377 0.01049 0.00309 -0.0095 1.0000 1.0000
-1.500 -0.1187 0.01035 0.00280 -0.0081 1.0000 1.0000
-1.250 -0.0993 0.01023 0.00257 -0.0068 1.0000 1.0000
-1.000 -0.0796 0.01014 0.00239 -0.0055 1.0000 1.0000
-0.750 -0.0597 0.01008 0.00222 -0.0041 1.0000 1.0000
-0.500 -0.0398 0.01003 0.00212 -0.0028 1.0000 1.0000
-0.250 -0.0198 0.01001 0.00206 -0.0014 1.0000 1.0000
0.000 0.0000 0.01000 0.00204 0.0000 1.0000 1.0000
0.250 0.0199 0.01001 0.00206 0.0014 1.0000 1.0000
0.500 0.0398 0.01003 0.00212 0.0028 1.0000 1.0000
0.750 0.0598 0.01008 0.00222 0.0041 1.0000 1.0000
1.000 0.0796 0.01014 0.00239 0.0055 1.0000 1.0000
1.250 0.0993 0.01023 0.00257 0.0068 1.0000 1.0000
1.500 0.1188 0.01034 0.00280 0.0081 1.0000 1.0000
1.750 0.1378 0.01049 0.00308 0.0095 1.0000 1.0000
2.000 0.1563 0.01068 0.00344 0.0108 1.0000 1.0000
2.250 0.1742 0.01091 0.00387 0.0121 1.0000 1.0000
2.500 0.2982 0.01466 0.00487 -0.0030 0.1011 1.0000
2.750 0.3188 0.01596 0.00608 -0.0014 0.0735 1.0000
3.000 0.3400 0.01782 0.00775 0.0001 0.0655 1.0000
3.250 0.3658 0.01936 0.00945 0.0014 0.0631 1.0000
3.500 0.3923 0.02128 0.01160 0.0027 0.0618 1.0000
3.750 0.4159 0.02366 0.01400 0.0033 0.0531 1.0000
4.000 0.4434 0.02531 0.01627 0.0051 0.0568 1.0000
4.250 0.4682 0.02898 0.02027 0.0064 0.0646 1.0000
6.250 0.6323 0.05893 0.05353 0.0127 0.1062 1.0000
6.500 0.6406 0.06235 0.05723 0.0116 0.0944 1.0000
6.750 0.6459 0.06679 0.06188 0.0095 0.0865 1.0000
7.000 0.6576 0.07213 0.06693 0.0119 0.0783 1.0000
7.250 0.6559 0.07527 0.07049 0.0066 0.0752 1.0000
7.500 0.6590 0.07932 0.07460 0.0041 0.0700 1.0000
7.750 0.6755 0.08543 0.08045 0.0094 0.0655 1.0000
8.000 0.6702 0.08870 0.08390 0.0053 0.0650 1.0000
8.250 0.6626 0.09279 0.08803 -0.0006 0.0644 1.0000
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Polar data table (+)
Polar graphs
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