GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 595 AIRFOIL (goe595-il) Reynolds number: 50,000 Max Cl/Cd: 36.89 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe595-il-50000.txt Download as CSV file: xf-goe595-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 595 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3998 0.09799 0.09138 -0.0219 1.0000 0.2611
-7.750 -0.3956 0.09473 0.08819 -0.0204 1.0000 0.2714
-7.500 -0.4313 0.09511 0.08881 -0.0186 1.0000 0.2781
-7.250 -0.4263 0.09183 0.08558 -0.0163 1.0000 0.2922
-7.000 -0.4297 0.08930 0.08315 -0.0136 1.0000 0.3066
-6.750 -0.4339 0.08691 0.08085 -0.0108 1.0000 0.3211
-6.500 -0.4459 0.08505 0.07911 -0.0082 1.0000 0.3366
-6.250 -0.4278 0.08136 0.07541 -0.0044 1.0000 0.3618
-6.000 -0.4521 0.08035 0.07455 -0.0011 1.0000 0.3808
-5.750 -0.4411 0.07729 0.07153 0.0030 1.0000 0.4084
-4.500 -0.4207 0.04790 0.04055 -0.0304 1.0000 0.1586
-4.250 -0.4000 0.04322 0.03530 -0.0308 1.0000 0.1403
-4.000 -0.3778 0.03939 0.03070 -0.0306 1.0000 0.1298
-3.750 -0.3567 0.03655 0.02740 -0.0298 1.0000 0.1283
-3.500 -0.3342 0.03423 0.02453 -0.0290 1.0000 0.1300
-3.250 -0.3104 0.03213 0.02190 -0.0281 1.0000 0.1313
-3.000 -0.2857 0.03026 0.01953 -0.0271 1.0000 0.1330
-2.750 -0.2634 0.02869 0.01795 -0.0262 1.0000 0.1419
-2.500 -0.2397 0.02737 0.01639 -0.0252 1.0000 0.1515
-2.250 -0.2139 0.02613 0.01498 -0.0243 1.0000 0.1635
-2.000 -0.1896 0.02511 0.01397 -0.0234 1.0000 0.1894
-1.750 -0.1287 0.01988 0.01220 -0.0264 1.0000 1.0000
-1.500 -0.1099 0.02009 0.01179 -0.0251 1.0000 1.0000
-1.250 -0.0917 0.02034 0.01157 -0.0240 1.0000 1.0000
-1.000 -0.0735 0.02062 0.01150 -0.0230 1.0000 1.0000
-0.750 -0.0555 0.02094 0.01153 -0.0220 1.0000 1.0000
-0.500 -0.0375 0.02131 0.01161 -0.0212 1.0000 1.0000
-0.250 -0.0198 0.02172 0.01179 -0.0203 1.0000 1.0000
0.000 -0.0023 0.02218 0.01205 -0.0196 1.0000 1.0000
0.250 0.0150 0.02270 0.01239 -0.0188 1.0000 1.0000
0.500 0.0317 0.02327 0.01282 -0.0182 1.0000 1.0000
0.750 0.0480 0.02392 0.01332 -0.0176 1.0000 1.0000
1.000 0.0638 0.02463 0.01392 -0.0171 1.0000 1.0000
1.250 0.0972 0.02581 0.01498 -0.0202 0.9923 1.0000
1.500 0.1528 0.02735 0.01641 -0.0272 0.9732 1.0000
1.750 0.2026 0.02860 0.01757 -0.0329 0.9538 1.0000
2.000 0.2486 0.02968 0.01861 -0.0376 0.9340 1.0000
2.250 0.2990 0.03073 0.01965 -0.0428 0.9156 1.0000
2.500 0.3351 0.03152 0.02045 -0.0454 0.8951 1.0000
2.750 0.3777 0.03226 0.02122 -0.0487 0.8756 1.0000
3.000 0.4234 0.03273 0.02176 -0.0520 0.8546 1.0000
3.250 0.4698 0.03284 0.02195 -0.0548 0.8317 1.0000
3.500 0.5122 0.03284 0.02205 -0.0567 0.8097 1.0000
3.750 0.5567 0.03270 0.02208 -0.0588 0.7900 1.0000
4.000 0.6093 0.03220 0.02176 -0.0617 0.7729 1.0000
4.250 0.6420 0.03222 0.02196 -0.0619 0.7530 1.0000
4.500 0.6862 0.03172 0.02166 -0.0632 0.7341 1.0000
4.750 0.7380 0.03074 0.02091 -0.0650 0.7164 1.0000
5.000 0.7710 0.03054 0.02093 -0.0646 0.6947 1.0000
5.250 0.8182 0.02965 0.02027 -0.0655 0.6737 1.0000
5.500 0.8497 0.02957 0.02037 -0.0647 0.6496 1.0000
5.750 0.8897 0.02917 0.02020 -0.0648 0.6260 1.0000
6.000 0.9210 0.02933 0.02051 -0.0641 0.6018 1.0000
6.250 0.9544 0.02883 0.02009 -0.0628 0.5720 1.0000
6.500 0.9778 0.02846 0.01973 -0.0600 0.5374 1.0000
6.750 1.0004 0.02826 0.01958 -0.0574 0.5041 1.0000
7.000 1.0222 0.02811 0.01940 -0.0547 0.4706 1.0000
7.250 1.0317 0.02810 0.01944 -0.0504 0.4325 1.0000
7.500 1.0356 0.02807 0.01941 -0.0453 0.3894 1.0000
7.750 1.0295 0.02829 0.01959 -0.0388 0.3345 1.0000
8.000 1.0150 0.02949 0.02019 -0.0316 0.2577 1.0000
8.250 1.0088 0.03207 0.02202 -0.0266 0.1896 1.0000
8.500 1.0162 0.03418 0.02378 -0.0236 0.1568 1.0000
8.750 1.0324 0.03617 0.02571 -0.0216 0.1355 1.0000
9.000 1.0562 0.03843 0.02783 -0.0209 0.1200 1.0000
9.250 1.0922 0.04134 0.03085 -0.0214 0.1092 1.0000
9.500 1.1208 0.04452 0.03419 -0.0214 0.1011 1.0000
9.750 1.1460 0.04807 0.03812 -0.0208 0.0974 1.0000
10.000 1.1657 0.05180 0.04218 -0.0198 0.0949 1.0000
10.250 1.1806 0.05620 0.04677 -0.0188 0.0922 1.0000
10.500 1.1767 0.05958 0.05067 -0.0154 0.0914 1.0000
10.750 1.1701 0.06321 0.05473 -0.0122 0.0911 1.0000
11.000 1.1593 0.06704 0.05892 -0.0090 0.0911 1.0000
11.250 1.1477 0.07095 0.06309 -0.0061 0.0915 1.0000
11.500 1.1358 0.07516 0.06750 -0.0037 0.0921 1.0000
11.750 1.1203 0.07924 0.07183 -0.0017 0.0929 1.0000
12.000 1.0376 0.08459 0.07764 -0.0011 0.0971 1.0000
12.250 0.9944 0.09290 0.08605 -0.0048 0.1009 1.0000
12.500 0.9695 0.10076 0.09396 -0.0085 0.1033 1.0000
12.750 0.9549 0.10816 0.10137 -0.0117 0.1047 1.0000
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Polar data table (+)
Polar graphs
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