GOE 445 AIRFOIL (goe445-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 445 AIRFOIL (goe445-il) Reynolds number: 200,000 Max Cl/Cd: 39 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe445-il-200000-n5.txt Download as CSV file: xf-goe445-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 445 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6235 0.08786 0.08442 -0.0082 1.0000 0.0165
-8.500 -0.6262 0.08236 0.07893 -0.0134 1.0000 0.0165
-8.250 -0.6332 0.07799 0.07451 -0.0156 1.0000 0.0165
-8.000 -0.6384 0.07394 0.07039 -0.0166 1.0000 0.0165
-7.750 -0.6405 0.06983 0.06617 -0.0174 1.0000 0.0165
-6.250 -0.6203 0.04290 0.03831 -0.0146 1.0000 0.0118
-6.000 -0.5988 0.03894 0.03391 -0.0120 1.0000 0.0082
-5.750 -0.5890 0.03473 0.02935 -0.0102 1.0000 0.0076
-5.500 -0.5748 0.03118 0.02540 -0.0082 1.0000 0.0073
-5.250 -0.5582 0.02800 0.02180 -0.0062 1.0000 0.0071
-5.000 -0.5396 0.02517 0.01855 -0.0041 1.0000 0.0070
-4.750 -0.5180 0.02334 0.01635 -0.0024 1.0000 0.0078
-4.500 -0.4970 0.02106 0.01363 -0.0007 1.0000 0.0090
-4.250 -0.4748 0.01893 0.01117 0.0009 1.0000 0.0092
-4.000 -0.4529 0.01708 0.00913 0.0024 1.0000 0.0094
-3.750 -0.4318 0.01558 0.00752 0.0040 1.0000 0.0100
-3.500 -0.4113 0.01439 0.00623 0.0056 1.0000 0.0109
-3.250 -0.3900 0.01362 0.00539 0.0069 1.0000 0.0138
-3.000 -0.3687 0.01285 0.00442 0.0084 1.0000 0.0157
-2.750 -0.3470 0.01214 0.00357 0.0097 1.0000 0.0208
-2.500 -0.3263 0.01125 0.00288 0.0111 1.0000 0.0794
-2.250 -0.3177 0.00904 0.00251 0.0137 1.0000 0.4895
-2.000 -0.3082 0.00793 0.00256 0.0181 1.0000 0.7398
-1.750 -0.2847 0.00773 0.00248 0.0195 1.0000 0.8215
-1.500 -0.2494 0.00772 0.00248 0.0184 1.0000 0.8815
-1.250 -0.2071 0.00777 0.00244 0.0155 1.0000 0.9172
-1.000 -0.1616 0.00784 0.00239 0.0117 1.0000 0.9454
-0.750 -0.1191 0.00789 0.00237 0.0085 1.0000 0.9667
-0.500 -0.0711 0.00794 0.00237 0.0040 1.0000 0.9838
-0.250 -0.0258 0.00797 0.00234 0.0000 1.0000 0.9965
0.000 0.0000 0.00797 0.00233 0.0000 1.0000 1.0000
0.250 0.0259 0.00797 0.00234 0.0000 0.9965 1.0000
0.500 0.0714 0.00794 0.00237 -0.0041 0.9836 1.0000
0.750 0.1190 0.00790 0.00237 -0.0085 0.9668 1.0000
1.000 0.1617 0.00784 0.00239 -0.0117 0.9453 1.0000
1.250 0.2071 0.00777 0.00244 -0.0155 0.9173 1.0000
1.500 0.2496 0.00772 0.00248 -0.0184 0.8815 1.0000
1.750 0.2851 0.00774 0.00248 -0.0196 0.8194 1.0000
2.000 0.3089 0.00792 0.00257 -0.0182 0.7454 1.0000
2.250 0.3181 0.00904 0.00251 -0.0138 0.4885 1.0000
2.500 0.3267 0.01127 0.00290 -0.0112 0.0760 1.0000
2.750 0.3474 0.01214 0.00357 -0.0098 0.0201 1.0000
3.000 0.3692 0.01286 0.00444 -0.0085 0.0156 1.0000
3.250 0.3906 0.01362 0.00539 -0.0070 0.0137 1.0000
3.500 0.4118 0.01442 0.00626 -0.0057 0.0107 1.0000
3.750 0.4323 0.01559 0.00753 -0.0041 0.0099 1.0000
4.000 0.4534 0.01707 0.00911 -0.0025 0.0095 1.0000
4.250 0.4754 0.01891 0.01116 -0.0010 0.0092 1.0000
4.500 0.4976 0.02098 0.01354 0.0005 0.0091 1.0000
4.750 0.5178 0.02363 0.01665 0.0024 0.0081 1.0000
5.000 0.5398 0.02521 0.01859 0.0041 0.0071 1.0000
5.250 0.5585 0.02800 0.02180 0.0061 0.0071 1.0000
5.500 0.5750 0.03119 0.02541 0.0082 0.0074 1.0000
5.750 0.5892 0.03462 0.02923 0.0101 0.0077 1.0000
6.000 0.5988 0.03890 0.03386 0.0120 0.0082 1.0000
6.250 0.6203 0.04290 0.03832 0.0146 0.0119 1.0000
13.000 0.5292 0.14635 0.14302 -0.0185 0.0160 1.0000
13.250 0.5293 0.14887 0.14554 -0.0203 0.0158 1.0000
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Polar data table (+)
Polar graphs
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