GOE 587 AIRFOIL (goe587-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 587 AIRFOIL (goe587-il) Reynolds number: 500,000 Max Cl/Cd: 70.73 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe587-il-500000-n5.txt Download as CSV file: xf-goe587-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 587 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4405 0.09465 0.09242 -0.0147 1.0000 0.0062
-8.000 -0.4383 0.09161 0.08941 -0.0159 1.0000 0.0062
-7.750 -0.4387 0.08848 0.08632 -0.0169 1.0000 0.0062
-7.500 -0.4395 0.08541 0.08327 -0.0182 1.0000 0.0062
-7.250 -0.4388 0.08108 0.07897 -0.0202 1.0000 0.0063
-7.000 -0.4366 0.07692 0.07481 -0.0220 1.0000 0.0064
-6.750 -0.4314 0.07352 0.07142 -0.0228 1.0000 0.0066
-6.500 -0.4239 0.07002 0.06790 -0.0242 1.0000 0.0066
-6.250 -0.4158 0.06686 0.06473 -0.0250 1.0000 0.0068
-6.000 -0.4059 0.06344 0.06128 -0.0261 1.0000 0.0069
-5.750 -0.3889 0.05965 0.05744 -0.0284 0.9986 0.0070
-5.500 -0.3606 0.05486 0.05255 -0.0332 0.9929 0.0071
-5.250 -0.3315 0.04952 0.04706 -0.0374 0.9849 0.0069
-5.000 -0.3047 0.04531 0.04269 -0.0399 0.9748 0.0055
-4.750 -0.2762 0.04075 0.03796 -0.0426 0.9628 0.0050
-4.500 -0.2420 0.03541 0.03236 -0.0457 0.9506 0.0046
-4.250 -0.2051 0.02932 0.02590 -0.0484 0.9376 0.0043
-4.000 -0.1698 0.02116 0.01706 -0.0494 0.9230 0.0041
-3.750 -0.1388 0.01505 0.01011 -0.0494 0.9064 0.0044
-3.500 -0.1087 0.01318 0.00778 -0.0497 0.8876 0.0050
-3.250 -0.0810 0.01243 0.00676 -0.0495 0.8672 0.0060
-3.000 -0.0556 0.01097 0.00492 -0.0487 0.8476 0.0064
-2.750 -0.0311 0.01000 0.00369 -0.0478 0.8279 0.0072
-2.500 -0.0063 0.00953 0.00305 -0.0470 0.8069 0.0086
-2.250 0.0187 0.00929 0.00265 -0.0463 0.7862 0.0106
-2.000 0.0428 0.00881 0.00201 -0.0453 0.7672 0.0161
-1.750 0.0681 0.00867 0.00180 -0.0448 0.7503 0.0287
-1.500 0.0936 0.00861 0.00166 -0.0443 0.7344 0.0369
-1.000 0.1449 0.00847 0.00135 -0.0434 0.7049 0.0496
-0.750 0.1705 0.00839 0.00119 -0.0430 0.6902 0.0563
-0.500 0.1962 0.00832 0.00108 -0.0426 0.6750 0.0682
-0.250 0.2217 0.00823 0.00102 -0.0421 0.6577 0.0995
0.000 0.2470 0.00817 0.00095 -0.0417 0.6378 0.1305
0.250 0.2707 0.00809 0.00091 -0.0410 0.6048 0.1988
0.500 0.2845 0.00688 0.00083 -0.0388 0.5785 0.6557
0.750 0.2977 0.00639 0.00103 -0.0350 0.5573 0.9137
1.000 0.3243 0.00651 0.00110 -0.0345 0.5395 0.9434
1.250 0.3640 0.00669 0.00122 -0.0369 0.5252 0.9704
1.750 0.4375 0.00700 0.00136 -0.0410 0.4904 0.9816
2.000 0.4696 0.00714 0.00141 -0.0422 0.4679 0.9847
2.250 0.5020 0.00730 0.00148 -0.0434 0.4405 0.9879
2.500 0.5333 0.00754 0.00155 -0.0444 0.3952 0.9900
2.750 0.5614 0.00807 0.00174 -0.0450 0.3114 0.9925
3.000 0.5811 0.00951 0.00230 -0.0444 0.0997 0.9952
3.250 0.6087 0.00998 0.00258 -0.0447 0.0440 0.9968
3.500 0.6375 0.01021 0.00285 -0.0452 0.0397 0.9983
3.750 0.6661 0.01045 0.00315 -0.0456 0.0367 0.9998
4.000 0.6887 0.01066 0.00341 -0.0447 0.0328 1.0000
4.250 0.7089 0.01097 0.00375 -0.0433 0.0280 1.0000
4.500 0.7305 0.01112 0.00398 -0.0422 0.0225 1.0000
4.750 0.7509 0.01143 0.00423 -0.0408 0.0122 1.0000
5.000 0.7695 0.01198 0.00487 -0.0390 0.0085 1.0000
5.250 0.7890 0.01246 0.00544 -0.0374 0.0069 1.0000
5.500 0.8067 0.01315 0.00619 -0.0356 0.0054 1.0000
5.750 0.8251 0.01381 0.00697 -0.0338 0.0048 1.0000
6.000 0.8425 0.01464 0.00795 -0.0319 0.0043 1.0000
6.250 0.8597 0.01558 0.00900 -0.0300 0.0040 1.0000
6.500 0.8768 0.01666 0.01019 -0.0281 0.0037 1.0000
6.750 0.8937 0.01797 0.01165 -0.0263 0.0035 1.0000
7.000 0.9093 0.01999 0.01384 -0.0243 0.0033 1.0000
7.250 0.9300 0.02139 0.01549 -0.0229 0.0028 1.0000
7.500 0.9487 0.02385 0.01826 -0.0212 0.0025 1.0000
7.750 0.9645 0.02818 0.02304 -0.0187 0.0023 1.0000
8.000 0.9774 0.03233 0.02758 -0.0161 0.0022 1.0000
8.250 0.9859 0.03673 0.03238 -0.0132 0.0021 1.0000
8.500 0.9922 0.04064 0.03662 -0.0105 0.0020 1.0000
8.750 0.9924 0.04557 0.04191 -0.0073 0.0021 1.0000
9.000 0.9875 0.05071 0.04737 -0.0041 0.0022 1.0000
9.250 0.9807 0.05498 0.05189 -0.0014 0.0023 1.0000
9.500 0.9710 0.05871 0.05581 0.0011 0.0024 1.0000
9.750 0.9531 0.06205 0.05930 0.0044 0.0024 1.0000
10.000 0.9351 0.06548 0.06286 0.0058 0.0024 1.0000
10.250 0.9165 0.06958 0.06707 0.0054 0.0024 1.0000
10.500 0.8991 0.07434 0.07194 0.0031 0.0024 1.0000
10.750 0.8822 0.08003 0.07772 -0.0006 0.0025 1.0000
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Polar data table (+)
Polar graphs
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