GOE 444 AIRFOIL (goe444-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 444 AIRFOIL (goe444-il) Reynolds number: 100,000 Max Cl/Cd: 24.79 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe444-il-100000-n5.txt Download as CSV file: xf-goe444-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 444 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6377 0.08864 0.08396 -0.0038 1.0000 0.0386
-8.000 -0.6413 0.08433 0.07968 -0.0069 1.0000 0.0390
-7.750 -0.6433 0.08010 0.07545 -0.0091 1.0000 0.0396
-7.500 -0.6429 0.07578 0.07109 -0.0112 1.0000 0.0405
-7.250 -0.6412 0.07137 0.06661 -0.0131 1.0000 0.0416
-7.000 -0.6408 0.06881 0.06354 -0.0161 1.0000 0.0458
-6.500 -0.5796 0.04500 0.04029 -0.0169 1.0000 0.0521
-6.000 -0.5977 0.04874 0.04286 -0.0142 1.0000 0.0251
-5.750 -0.5849 0.04482 0.03867 -0.0132 1.0000 0.0237
-5.500 -0.5698 0.04095 0.03438 -0.0119 1.0000 0.0216
-5.250 -0.5465 0.03843 0.03112 -0.0094 1.0000 0.0182
-5.000 -0.5300 0.03470 0.02709 -0.0080 1.0000 0.0174
-4.750 -0.5121 0.03140 0.02342 -0.0065 1.0000 0.0167
-4.500 -0.4917 0.02858 0.02018 -0.0049 1.0000 0.0161
-4.250 -0.4695 0.02601 0.01718 -0.0033 1.0000 0.0157
-4.000 -0.4458 0.02365 0.01444 -0.0017 1.0000 0.0156
-3.750 -0.4213 0.02151 0.01199 -0.0003 1.0000 0.0159
-3.500 -0.3972 0.01980 0.01005 0.0011 1.0000 0.0170
-3.250 -0.3758 0.01812 0.00823 0.0027 1.0000 0.0195
-3.000 -0.3554 0.01680 0.00682 0.0043 1.0000 0.0216
-2.750 -0.3341 0.01579 0.00559 0.0059 1.0000 0.0255
-2.500 -0.3122 0.01489 0.00456 0.0074 1.0000 0.0365
-2.250 -0.2996 0.01205 0.00357 0.0095 1.0000 0.4212
-2.000 -0.2037 0.01110 0.00393 -0.0006 1.0000 0.9679
-1.750 -0.1549 0.01102 0.00351 -0.0052 1.0000 0.9856
-1.500 -0.1088 0.01090 0.00308 -0.0095 1.0000 0.9993
-1.250 -0.0896 0.01077 0.00283 -0.0082 1.0000 1.0000
-1.000 -0.0721 0.01066 0.00264 -0.0066 1.0000 1.0000
-0.750 -0.0543 0.01058 0.00249 -0.0049 1.0000 1.0000
-0.500 -0.0364 0.01053 0.00237 -0.0033 1.0000 1.0000
-0.250 -0.0183 0.01049 0.00231 -0.0016 1.0000 1.0000
0.000 0.0000 0.01048 0.00229 0.0000 1.0000 1.0000
0.250 0.0183 0.01050 0.00231 0.0016 1.0000 1.0000
0.500 0.0364 0.01053 0.00238 0.0033 1.0000 1.0000
0.750 0.0543 0.01058 0.00249 0.0049 1.0000 1.0000
1.000 0.0720 0.01066 0.00264 0.0066 1.0000 1.0000
1.250 0.0895 0.01077 0.00283 0.0083 1.0000 1.0000
1.500 0.1088 0.01090 0.00308 0.0095 0.9992 1.0000
1.750 0.1551 0.01103 0.00353 0.0052 0.9854 1.0000
2.000 0.2036 0.01110 0.00393 0.0006 0.9678 1.0000
2.250 0.3002 0.01211 0.00358 -0.0096 0.4107 1.0000
2.500 0.3129 0.01493 0.00459 -0.0075 0.0361 1.0000
2.750 0.3349 0.01581 0.00562 -0.0061 0.0249 1.0000
3.000 0.3561 0.01683 0.00685 -0.0045 0.0215 1.0000
3.250 0.3765 0.01812 0.00823 -0.0028 0.0195 1.0000
3.500 0.3979 0.01981 0.01006 -0.0013 0.0169 1.0000
3.750 0.4220 0.02154 0.01203 0.0001 0.0159 1.0000
4.000 0.4464 0.02365 0.01444 0.0016 0.0157 1.0000
4.250 0.4699 0.02596 0.01714 0.0031 0.0158 1.0000
4.500 0.4921 0.02854 0.02014 0.0048 0.0161 1.0000
4.750 0.5124 0.03143 0.02345 0.0064 0.0167 1.0000
5.000 0.5303 0.03474 0.02714 0.0080 0.0174 1.0000
5.250 0.5468 0.03838 0.03107 0.0093 0.0182 1.0000
5.750 0.5505 0.02958 0.02391 0.0149 0.0237 1.0000
6.000 0.5601 0.03387 0.02843 0.0159 0.0255 1.0000
7.000 0.6370 0.06705 0.06213 0.0149 0.0435 1.0000
7.500 0.6425 0.07568 0.07100 0.0114 0.0406 1.0000
7.750 0.6429 0.08000 0.07535 0.0093 0.0396 1.0000
8.000 0.6408 0.08427 0.07963 0.0070 0.0391 1.0000
8.250 0.6373 0.08860 0.08390 0.0040 0.0386 1.0000
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Polar data table (+)
Polar graphs
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