GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 456 AIRFOIL (goe456-il) Reynolds number: 1,000,000 Max Cl/Cd: 134.25 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe456-il-1000000-n5.txt Download as CSV file: xf-goe456-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 456 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3209 0.12966 0.12799 -0.0326 1.0000 0.0023
-11.000 -0.3182 0.12639 0.12474 -0.0328 1.0000 0.0023
-10.750 -0.3144 0.12402 0.12238 -0.0328 1.0000 0.0026
-10.500 -0.3093 0.12108 0.11945 -0.0336 0.9999 0.0026
-10.250 -0.2971 0.11725 0.11562 -0.0365 0.9990 0.0026
-10.000 -0.2847 0.11315 0.11152 -0.0397 0.9973 0.0025
-9.750 -0.2739 0.10987 0.10825 -0.0420 0.9931 0.0027
-9.500 -0.2625 0.10628 0.10466 -0.0447 0.9892 0.0029
-9.250 -0.2514 0.10270 0.10108 -0.0474 0.9836 0.0028
-9.000 -0.2383 0.09893 0.09731 -0.0506 0.9788 0.0028
-8.750 -0.2247 0.09522 0.09360 -0.0540 0.9727 0.0030
-8.500 -0.2077 0.09119 0.08956 -0.0585 0.9678 0.0033
-8.250 -0.1887 0.08702 0.08538 -0.0637 0.9614 0.0030
-8.000 -0.1626 0.08188 0.08022 -0.0714 0.9559 0.0039
-7.750 -0.1366 0.07691 0.07522 -0.0792 0.9455 0.0040
-7.500 -0.1135 0.07214 0.07040 -0.0862 0.9301 0.0040
-7.250 -0.1018 0.06870 0.06688 -0.0896 0.9098 0.0040
-7.000 -0.0952 0.06619 0.06429 -0.0913 0.8926 0.0032
-5.500 -0.0077 0.04286 0.04058 -0.1140 0.8246 0.0038
-5.250 0.0160 0.03766 0.03524 -0.1190 0.8168 0.0035
-5.000 0.0425 0.03148 0.02888 -0.1237 0.8088 0.0033
-4.750 0.0686 0.02182 0.01871 -0.1279 0.8020 0.0030
-4.500 0.0908 0.01460 0.01057 -0.1281 0.7944 0.0027
-4.250 0.1152 0.01174 0.00714 -0.1275 0.7869 0.0028
-4.000 0.1409 0.01045 0.00553 -0.1271 0.7784 0.0029
-3.750 0.1671 0.00961 0.00447 -0.1267 0.7703 0.0031
-3.500 0.1934 0.00900 0.00367 -0.1264 0.7615 0.0035
-3.250 0.2201 0.00861 0.00313 -0.1261 0.7514 0.0039
-3.000 0.2465 0.00814 0.00251 -0.1257 0.7402 0.0043
-2.750 0.2730 0.00795 0.00226 -0.1255 0.7279 0.0052
-2.500 0.2995 0.00775 0.00195 -0.1252 0.7147 0.0061
-2.250 0.3260 0.00759 0.00167 -0.1249 0.7013 0.0068
-2.000 0.3525 0.00738 0.00134 -0.1245 0.6876 0.0096
-1.750 0.3789 0.00732 0.00118 -0.1242 0.6737 0.0130
-1.500 0.4053 0.00722 0.00105 -0.1239 0.6605 0.0283
-1.000 0.4578 0.00692 0.00092 -0.1235 0.6380 0.1310
-0.750 0.4844 0.00694 0.00090 -0.1233 0.6262 0.1454
-0.500 0.5107 0.00700 0.00089 -0.1230 0.6113 0.1540
-0.250 0.5370 0.00705 0.00088 -0.1227 0.5968 0.1606
0.000 0.5636 0.00710 0.00088 -0.1225 0.5856 0.1694
0.250 0.5901 0.00714 0.00089 -0.1223 0.5760 0.1782
0.500 0.6171 0.00715 0.00090 -0.1222 0.5671 0.1889
0.750 0.6438 0.00718 0.00093 -0.1220 0.5589 0.2043
1.000 0.6703 0.00721 0.00098 -0.1218 0.5492 0.2259
1.250 0.6966 0.00724 0.00103 -0.1216 0.5368 0.2540
1.500 0.7228 0.00728 0.00110 -0.1214 0.5235 0.2868
1.750 0.7490 0.00731 0.00117 -0.1212 0.5122 0.3211
2.000 0.7752 0.00731 0.00126 -0.1210 0.5039 0.3662
2.250 0.7993 0.00687 0.00143 -0.1206 0.4961 0.6395
2.750 0.8592 0.00640 0.00166 -0.1218 0.4770 1.0000
3.000 0.8842 0.00659 0.00178 -0.1213 0.4539 1.0000
3.250 0.9041 0.00720 0.00203 -0.1200 0.3786 1.0000
3.500 0.9186 0.00831 0.00254 -0.1178 0.2597 1.0000
3.750 0.9386 0.00897 0.00292 -0.1166 0.2000 1.0000
4.000 0.9588 0.00961 0.00327 -0.1154 0.1452 1.0000
4.250 0.9711 0.01099 0.00409 -0.1128 0.0138 1.0000
4.500 0.9952 0.01126 0.00438 -0.1122 0.0087 1.0000
4.750 1.0190 0.01157 0.00473 -0.1115 0.0064 1.0000
5.000 1.0425 0.01189 0.00507 -0.1108 0.0051 1.0000
5.250 1.0649 0.01230 0.00552 -0.1098 0.0041 1.0000
5.500 1.0878 0.01265 0.00591 -0.1090 0.0034 1.0000
5.750 1.1100 0.01306 0.00634 -0.1081 0.0030 1.0000
6.000 1.1296 0.01370 0.00707 -0.1067 0.0025 1.0000
6.250 1.1499 0.01426 0.00771 -0.1054 0.0024 1.0000
6.500 1.1685 0.01495 0.00849 -0.1037 0.0021 1.0000
6.750 1.1847 0.01580 0.00944 -0.1017 0.0020 1.0000
7.000 1.1988 0.01676 0.01051 -0.0993 0.0019 1.0000
7.250 1.2153 0.01749 0.01130 -0.0975 0.0017 1.0000
7.500 1.2291 0.01837 0.01227 -0.0952 0.0016 1.0000
7.750 1.2480 0.01873 0.01264 -0.0939 0.0015 1.0000
8.000 1.2548 0.01990 0.01394 -0.0904 0.0014 1.0000
8.250 1.2591 0.02151 0.01568 -0.0865 0.0013 1.0000
8.500 1.2693 0.02293 0.01722 -0.0837 0.0013 1.0000
8.750 1.2876 0.02565 0.02011 -0.0821 0.0010 1.0000
9.000 1.3294 0.03065 0.02538 -0.0842 0.0009 1.0000
9.250 1.3496 0.03436 0.02937 -0.0827 0.0008 1.0000
9.500 1.3624 0.03799 0.03329 -0.0803 0.0008 1.0000
9.750 1.3685 0.04170 0.03729 -0.0770 0.0008 1.0000
10.000 1.3695 0.04516 0.04102 -0.0733 0.0008 1.0000
10.250 1.3652 0.04837 0.04448 -0.0691 0.0009 1.0000
10.500 1.3547 0.05110 0.04741 -0.0642 0.0009 1.0000
10.750 1.3414 0.05390 0.05041 -0.0596 0.0009 1.0000
11.000 1.3273 0.05680 0.05349 -0.0558 0.0009 1.0000
11.250 1.3109 0.06016 0.05704 -0.0526 0.0009 1.0000
11.500 1.2944 0.06376 0.06080 -0.0501 0.0010 1.0000
11.750 1.2767 0.06773 0.06494 -0.0485 0.0010 1.0000
12.000 1.2589 0.07202 0.06938 -0.0476 0.0010 1.0000
12.250 1.2397 0.07682 0.07434 -0.0477 0.0010 1.0000
12.500 1.2206 0.08202 0.07968 -0.0485 0.0010 1.0000
12.750 1.2012 0.08775 0.08555 -0.0503 0.0010 1.0000
13.000 1.1818 0.09404 0.09197 -0.0529 0.0010 1.0000
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Polar data table (+)
Polar graphs
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