GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 50,000 Max Cl/Cd: 26.12 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe285-il-50000.txt Download as CSV file: xf-goe285-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3668 0.10963 0.10250 -0.0236 1.0000 0.2343
-8.250 -0.3309 0.10321 0.09604 -0.0215 1.0000 0.2418
-8.000 -0.3480 0.10246 0.09543 -0.0219 1.0000 0.2510
-7.750 -0.3323 0.09813 0.09114 -0.0208 1.0000 0.2575
-7.500 -0.3433 0.09681 0.08995 -0.0199 1.0000 0.2678
-7.250 -0.3337 0.09326 0.08646 -0.0185 1.0000 0.2762
-7.000 -0.3579 0.09277 0.08617 -0.0162 1.0000 0.2860
-6.750 -0.3413 0.08908 0.08251 -0.0143 1.0000 0.2985
-6.500 -0.3914 0.08994 0.08365 -0.0129 1.0000 0.3053
-6.250 -0.3741 0.08639 0.08013 -0.0091 1.0000 0.3213
-6.000 -0.3671 0.08359 0.07741 -0.0059 1.0000 0.3354
-5.750 -0.3735 0.08158 0.07552 -0.0027 1.0000 0.3491
-5.250 -0.3945 0.07822 0.07239 0.0041 1.0000 0.3813
-5.000 -0.3982 0.07636 0.07063 0.0080 1.0000 0.4007
-4.750 -0.4035 0.07471 0.06907 0.0121 1.0000 0.4236
-4.500 -0.4119 0.07305 0.06751 0.0166 1.0000 0.4514
-4.250 -0.4185 0.07160 0.06617 0.0219 1.0000 0.4852
-3.750 -0.1957 0.06032 0.05455 0.0227 1.0000 0.7794
-3.500 -0.1558 0.05688 0.05109 0.0200 1.0000 0.8341
-3.250 -0.3140 0.04724 0.03948 -0.0291 1.0000 0.1966
-3.000 -0.2850 0.04394 0.03545 -0.0314 1.0000 0.1810
-2.750 -0.2631 0.04165 0.03298 -0.0319 1.0000 0.1774
-2.500 -0.2391 0.03964 0.03061 -0.0325 1.0000 0.1743
-2.250 -0.2156 0.03814 0.02874 -0.0330 1.0000 0.1755
-2.000 -0.1921 0.03699 0.02718 -0.0334 1.0000 0.1793
-1.750 -0.1484 0.03553 0.02538 -0.0372 0.9939 0.1854
-1.500 -0.0921 0.03440 0.02391 -0.0430 0.9817 0.2014
-1.250 -0.0399 0.03338 0.02284 -0.0480 0.9687 0.2268
-1.000 0.0104 0.03266 0.02211 -0.0524 0.9553 0.2663
-0.750 0.0633 0.03201 0.02157 -0.0571 0.9414 0.3129
-0.500 0.1141 0.03126 0.02112 -0.0613 0.9273 0.3733
-0.250 0.1633 0.02869 0.02062 -0.0633 0.9132 1.0000
0.000 0.2129 0.02920 0.02048 -0.0671 0.8960 1.0000
0.250 0.2623 0.02957 0.02049 -0.0709 0.8785 1.0000
0.500 0.3032 0.02985 0.02053 -0.0731 0.8582 1.0000
0.750 0.3471 0.02993 0.02041 -0.0753 0.8373 1.0000
1.000 0.3959 0.02975 0.02006 -0.0779 0.8179 1.0000
1.250 0.4389 0.02955 0.01972 -0.0793 0.7992 1.0000
1.500 0.4780 0.02940 0.01945 -0.0801 0.7813 1.0000
1.750 0.5139 0.02929 0.01924 -0.0803 0.7636 1.0000
2.000 0.5475 0.02921 0.01908 -0.0801 0.7461 1.0000
2.250 0.5793 0.02917 0.01895 -0.0796 0.7289 1.0000
2.500 0.6098 0.02915 0.01887 -0.0789 0.7117 1.0000
2.750 0.6393 0.02918 0.01882 -0.0780 0.6946 1.0000
3.000 0.6676 0.02928 0.01886 -0.0771 0.6776 1.0000
3.250 0.6949 0.02948 0.01900 -0.0760 0.6608 1.0000
3.500 0.7213 0.02976 0.01922 -0.0750 0.6440 1.0000
3.750 0.7467 0.03015 0.01955 -0.0738 0.6274 1.0000
4.000 0.7708 0.03069 0.02005 -0.0727 0.6112 1.0000
4.250 0.7937 0.03139 0.02073 -0.0716 0.5959 1.0000
4.500 0.8164 0.03221 0.02153 -0.0706 0.5822 1.0000
4.750 0.8481 0.03247 0.02171 -0.0702 0.5716 1.0000
5.000 0.8612 0.03411 0.02345 -0.0688 0.5583 1.0000
5.250 0.8757 0.03573 0.02514 -0.0676 0.5470 1.0000
5.500 0.9066 0.03612 0.02548 -0.0673 0.5388 1.0000
5.750 0.9094 0.03875 0.02828 -0.0655 0.5279 1.0000
6.000 0.9431 0.03904 0.02854 -0.0655 0.5217 1.0000
6.250 0.9278 0.04350 0.03322 -0.0633 0.5127 1.0000
6.500 0.9475 0.04510 0.03489 -0.0628 0.5072 1.0000
6.750 0.9289 0.05031 0.04023 -0.0612 0.5012 1.0000
7.000 0.8487 0.06169 0.05162 -0.0600 0.4956 1.0000
7.250 0.8236 0.06821 0.05815 -0.0605 0.4931 1.0000
7.500 0.7864 0.07598 0.06591 -0.0618 0.4967 1.0000
7.750 0.7769 0.08113 0.07109 -0.0628 0.5007 1.0000
8.000 0.7794 0.08525 0.07527 -0.0636 0.5030 1.0000
11.750 1.3487 0.05328 0.04506 -0.0278 0.2594 1.0000
12.000 1.2999 0.05900 0.05108 -0.0232 0.2562 1.0000
12.250 1.2264 0.07012 0.06240 -0.0227 0.2614 1.0000
12.500 1.3123 0.05797 0.04963 -0.0162 0.2005 1.0000
12.750 1.2834 0.06296 0.05480 -0.0146 0.1929 1.0000
13.000 1.2758 0.06579 0.05762 -0.0133 0.1806 1.0000
13.250 1.2350 0.07376 0.06584 -0.0144 0.1788 1.0000
13.500 1.1558 0.08971 0.08205 -0.0207 0.1857 1.0000
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Polar data table (+)
Polar graphs
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