GOE 435 AIRFOIL (goe435-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 435 AIRFOIL (goe435-il) Reynolds number: 200,000 Max Cl/Cd: 50.23 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe435-il-200000-n5.txt Download as CSV file: xf-goe435-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 435 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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.4273 0.09710 0.09093 -0.0739 0.8463 0.0813
-14.750 -0.4214 0.09468 0.08845 -0.0748 0.8350 0.0820
-14.500 -0.4178 0.09197 0.08566 -0.0757 0.8245 0.0826
-14.250 -0.4161 0.08896 0.08262 -0.0770 0.8163 0.0834
-14.000 -0.4261 0.08418 0.07777 -0.0792 0.8088 0.0843
-13.750 -0.4618 0.07581 0.06921 -0.0832 0.8029 0.0850
-13.500 -0.5037 0.06696 0.06010 -0.0876 0.7974 0.0856
-13.250 -0.5282 0.06069 0.05365 -0.0909 0.7913 0.0864
-13.000 -0.5434 0.05580 0.04861 -0.0935 0.7848 0.0875
-12.750 -0.5539 0.05167 0.04436 -0.0957 0.7789 0.0888
-12.500 -0.5632 0.04789 0.04046 -0.0976 0.7734 0.0906
-12.250 -0.5736 0.04414 0.03663 -0.0996 0.7686 0.0936
-12.000 -0.5856 0.04012 0.03269 -0.1022 0.7635 0.0995
-11.750 -0.5928 0.03645 0.02924 -0.1058 0.7581 0.1251
-11.500 -0.5781 0.03518 0.02778 -0.1063 0.7531 0.1357
-11.250 -0.5656 0.03366 0.02615 -0.1074 0.7483 0.1401
-11.000 -0.5511 0.03236 0.02467 -0.1083 0.7438 0.1439
-10.750 -0.5359 0.03108 0.02331 -0.1095 0.7393 0.1466
-10.500 -0.5208 0.02981 0.02200 -0.1107 0.7342 0.1490
-10.250 -0.5053 0.02866 0.02075 -0.1118 0.7289 0.1517
-10.000 -0.4918 0.02766 0.01960 -0.1125 0.7236 0.1543
-9.750 -0.4756 0.02678 0.01854 -0.1133 0.7188 0.1562
-9.500 -0.4554 0.02602 0.01775 -0.1144 0.7139 0.1579
-9.250 -0.4336 0.02535 0.01707 -0.1155 0.7085 0.1597
-9.000 -0.4105 0.02481 0.01649 -0.1163 0.7033 0.1615
-8.750 -0.3866 0.02436 0.01596 -0.1169 0.6982 0.1633
-8.500 -0.3621 0.02396 0.01544 -0.1174 0.6935 0.1650
-8.250 -0.3369 0.02360 0.01499 -0.1178 0.6887 0.1667
-8.000 -0.3115 0.02325 0.01457 -0.1183 0.6830 0.1682
-7.750 -0.2855 0.02294 0.01417 -0.1187 0.6772 0.1692
-7.500 -0.2596 0.02255 0.01377 -0.1188 0.6718 0.1704
-7.250 -0.2334 0.02220 0.01338 -0.1189 0.6668 0.1716
-7.000 -0.2073 0.02188 0.01308 -0.1191 0.6605 0.1728
-6.750 -0.1808 0.02157 0.01278 -0.1193 0.6535 0.1741
-6.500 -0.1539 0.02129 0.01245 -0.1195 0.6472 0.1756
-6.250 -0.1266 0.02104 0.01213 -0.1197 0.6415 0.1772
-6.000 -0.0995 0.02080 0.01189 -0.1199 0.6344 0.1787
-5.750 -0.0721 0.02056 0.01160 -0.1201 0.6276 0.1799
-5.500 -0.0444 0.02033 0.01129 -0.1203 0.6218 0.1809
-5.250 -0.0169 0.02013 0.01106 -0.1205 0.6149 0.1817
-5.000 0.0108 0.01993 0.01082 -0.1206 0.6080 0.1826
-4.750 0.0389 0.01977 0.01056 -0.1208 0.6020 0.1836
-4.500 0.0659 0.01949 0.01032 -0.1209 0.5957 0.1851
-4.250 0.0932 0.01924 0.01009 -0.1210 0.5889 0.1866
-4.000 0.1208 0.01903 0.00986 -0.1212 0.5829 0.1878
-3.750 0.1487 0.01886 0.00966 -0.1214 0.5776 0.1893
-3.500 0.1767 0.01872 0.00952 -0.1216 0.5722 0.1910
-3.250 0.2049 0.01859 0.00936 -0.1218 0.5673 0.1927
-3.000 0.2333 0.01848 0.00920 -0.1220 0.5628 0.1943
-2.750 0.2616 0.01839 0.00906 -0.1222 0.5583 0.1958
-2.500 0.2897 0.01831 0.00898 -0.1224 0.5527 0.1969
-2.250 0.3177 0.01824 0.00887 -0.1225 0.5468 0.1979
-2.000 0.3458 0.01819 0.00874 -0.1226 0.5412 0.1989
-1.750 0.3738 0.01811 0.00865 -0.1228 0.5357 0.2002
-1.500 0.4016 0.01802 0.00858 -0.1230 0.5297 0.2018
-1.250 0.4297 0.01796 0.00851 -0.1232 0.5244 0.2035
-1.000 0.4583 0.01793 0.00843 -0.1235 0.5202 0.2053
-0.750 0.4872 0.01793 0.00839 -0.1238 0.5165 0.2075
-0.500 0.5154 0.01791 0.00841 -0.1240 0.5126 0.2099
-0.250 0.5436 0.01791 0.00842 -0.1242 0.5086 0.2129
0.250 0.6004 0.01787 0.00839 -0.1247 0.5003 0.2234
0.500 0.6294 0.01784 0.00836 -0.1251 0.4966 0.2350
0.750 0.6582 0.01766 0.00844 -0.1258 0.4930 0.2795
1.000 0.6855 0.01772 0.00874 -0.1259 0.4889 0.3321
1.250 0.7126 0.01787 0.00893 -0.1258 0.4845 0.3517
1.500 0.7397 0.01804 0.00906 -0.1257 0.4801 0.3639
1.750 0.7671 0.01823 0.00923 -0.1256 0.4761 0.3725
2.000 0.7948 0.01845 0.00937 -0.1256 0.4722 0.3811
2.250 0.8198 0.01860 0.00959 -0.1252 0.4678 0.3869
2.500 0.8447 0.01877 0.00982 -0.1247 0.4629 0.3926
2.750 0.8697 0.01896 0.01000 -0.1243 0.4579 0.3992
3.000 0.8952 0.01917 0.01013 -0.1239 0.4534 0.4047
3.250 0.9195 0.01935 0.01033 -0.1234 0.4489 0.4086
3.500 0.9419 0.01952 0.01059 -0.1227 0.4432 0.4124
3.750 0.9640 0.01971 0.01081 -0.1218 0.4374 0.4162
4.000 0.9857 0.01993 0.01098 -0.1209 0.4321 0.4199
4.250 1.0045 0.02016 0.01125 -0.1195 0.4264 0.4240
4.500 1.0221 0.02042 0.01153 -0.1180 0.4199 0.4276
4.750 1.0400 0.02074 0.01180 -0.1167 0.4135 0.4302
5.000 1.0589 0.02108 0.01221 -0.1156 0.4063 0.4333
5.250 1.0766 0.02149 0.01265 -0.1144 0.3984 0.4366
5.500 1.0938 0.02195 0.01313 -0.1132 0.3910 0.4403
5.750 1.1102 0.02249 0.01369 -0.1120 0.3824 0.4442
6.000 1.1248 0.02313 0.01429 -0.1106 0.3744 0.4483
6.250 1.1394 0.02383 0.01498 -0.1094 0.3655 0.4524
6.500 1.1518 0.02466 0.01575 -0.1079 0.3575 0.4559
6.750 1.1655 0.02546 0.01659 -0.1068 0.3493 0.4598
7.250 1.1904 0.02735 0.01849 -0.1044 0.3355 0.4666
7.500 1.2022 0.02840 0.01953 -0.1033 0.3290 0.4701
7.750 1.2133 0.02952 0.02063 -0.1021 0.3234 0.4741
8.000 1.2266 0.03057 0.02170 -0.1012 0.3177 0.4788
8.250 1.2381 0.03174 0.02287 -0.1002 0.3124 0.4836
8.500 1.2494 0.03290 0.02403 -0.0992 0.3079 0.4894
8.750 1.2630 0.03399 0.02520 -0.0985 0.3038 0.4962
9.000 1.2759 0.03515 0.02641 -0.0977 0.2995 0.5031
9.500 1.2981 0.03769 0.02898 -0.0960 0.2912 0.5172
9.750 1.3105 0.03893 0.03028 -0.0954 0.2874 0.5257
10.000 1.3221 0.04027 0.03171 -0.0947 0.2833 0.5349
10.250 1.3327 0.04168 0.03319 -0.0940 0.2794 0.5457
10.500 1.3433 0.04308 0.03461 -0.0933 0.2758 0.5587
10.750 1.3548 0.04439 0.03593 -0.0926 0.2725 0.5736
11.000 1.3653 0.04594 0.03763 -0.0921 0.2693 0.5911
11.250 1.3758 0.04748 0.03930 -0.0916 0.2659 0.6116
11.500 1.3856 0.04906 0.04098 -0.0910 0.2626 0.6337
11.750 1.3947 0.05068 0.04268 -0.0904 0.2595 0.6572
12.000 1.4054 0.05213 0.04416 -0.0898 0.2568 0.6820
12.250 1.4155 0.05369 0.04581 -0.0892 0.2542 0.7062
12.500 1.4237 0.05553 0.04778 -0.0887 0.2515 0.7282
12.750 1.4321 0.05732 0.04967 -0.0882 0.2489 0.7486
13.000 1.4404 0.05912 0.05154 -0.0877 0.2463 0.7682
13.250 1.4485 0.06090 0.05337 -0.0872 0.2439 0.7879
13.500 1.4579 0.06248 0.05499 -0.0867 0.2416 0.8095
13.750 1.4678 0.06389 0.05645 -0.0859 0.2393 0.8384
14.000 1.4657 0.06586 0.05866 -0.0846 0.2369 1.0000
14.250 1.4709 0.06825 0.06113 -0.0845 0.2341 1.0000
14.500 1.4753 0.07073 0.06365 -0.0845 0.2314 1.0000
14.750 1.4817 0.07295 0.06589 -0.0844 0.2288 1.0000
15.000 1.4903 0.07488 0.06779 -0.0843 0.2266 1.0000
15.250 1.5021 0.07637 0.06922 -0.0841 0.2245 1.0000
15.500 1.5024 0.07943 0.07241 -0.0843 0.2222 1.0000
15.750 1.5038 0.08234 0.07541 -0.0844 0.2198 1.0000
16.000 1.5058 0.08518 0.07832 -0.0846 0.2175 1.0000
16.250 1.5097 0.08775 0.08094 -0.0847 0.2154 1.0000
16.500 1.5154 0.09009 0.08330 -0.0849 0.2135 1.0000
16.750 1.5247 0.09192 0.08512 -0.0849 0.2118 1.0000
17.000 1.5383 0.09316 0.08631 -0.0849 0.2102 1.0000
17.250 1.5331 0.09697 0.09027 -0.0854 0.2082 1.0000
17.500 1.5271 0.10092 0.09435 -0.0860 0.2060 1.0000
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Polar data table (+)
Polar graphs
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