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GOE 723 AIRFOIL (goe723-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 723 AIRFOIL (goe723-il)
Reynolds number: 200,000
Max Cl/Cd: 82.25 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe723-il-200000.txt
Download as CSV file: xf-goe723-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 723 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3095   0.09266   0.08916  -0.0400   1.0000   0.0688
  -8.250  -0.3186   0.09115   0.08774  -0.0380   1.0000   0.0706
  -7.750  -0.3286   0.08116   0.07789  -0.0543   0.9848   0.0762
  -7.500  -0.2989   0.07897   0.07567  -0.0536   0.9822   0.0777
  -7.250  -0.2731   0.07600   0.07269  -0.0568   0.9743   0.0804
  -7.000  -0.2512   0.06428   0.06089  -0.0821   0.9583   0.0888
  -6.750  -0.2273   0.06340   0.06002  -0.0792   0.9510   0.0903
  -6.500  -0.1985   0.05277   0.04908  -0.1002   0.9393   0.1020
  -6.250  -0.1676   0.05194   0.04835  -0.0988   0.9338   0.1037
  -6.000  -0.1327   0.05040   0.04680  -0.1008   0.9291   0.1090
  -5.750  -0.1061   0.04488   0.04108  -0.1089   0.9169   0.1194
  -5.500  -0.0791   0.04054   0.03644  -0.1151   0.9054   0.1325
  -5.250  -0.0650   0.02566   0.01966  -0.1199   0.8919   0.0721
  -5.000  -0.0366   0.02349   0.01666  -0.1195   0.8816   0.0639
  -4.750  -0.0123   0.02137   0.01434  -0.1191   0.8705   0.0626
  -4.500   0.0168   0.02016   0.01285  -0.1192   0.8620   0.0628
  -4.250   0.0411   0.01918   0.01167  -0.1184   0.8509   0.0628
  -4.000   0.0678   0.01818   0.01048  -0.1179   0.8416   0.0625
  -3.750   0.0942   0.01733   0.00949  -0.1173   0.8322   0.0623
  -3.500   0.1200   0.01665   0.00870  -0.1167   0.8232   0.0624
  -3.250   0.1468   0.01603   0.00799  -0.1161   0.8147   0.0628
  -3.000   0.1721   0.01554   0.00744  -0.1154   0.8059   0.0634
  -2.750   0.1986   0.01511   0.00694  -0.1148   0.7978   0.0640
  -2.500   0.2223   0.01451   0.00637  -0.1139   0.7895   0.0662
  -2.250   0.2479   0.01414   0.00599  -0.1133   0.7818   0.0693
  -2.000   0.2733   0.01390   0.00570  -0.1126   0.7740   0.0720
  -1.750   0.2994   0.01370   0.00542  -0.1120   0.7662   0.0748
  -1.500   0.3257   0.01343   0.00512  -0.1114   0.7594   0.0818
  -1.250   0.3502   0.01304   0.00491  -0.1106   0.7514   0.1188
  -1.000   0.3747   0.01237   0.00498  -0.1101   0.7453   0.3374
  -0.750   0.3981   0.01233   0.00513  -0.1091   0.7370   0.4066
  -0.500   0.4246   0.01231   0.00514  -0.1085   0.7303   0.4505
  -0.250   0.4490   0.01231   0.00521  -0.1076   0.7223   0.4859
   0.000   0.4747   0.01226   0.00521  -0.1069   0.7146   0.5240
   0.250   0.4993   0.01223   0.00527  -0.1060   0.7070   0.5648
   0.500   0.5239   0.01211   0.00529  -0.1050   0.6994   0.6117
   0.750   0.5488   0.01189   0.00529  -0.1041   0.6933   0.6806
   1.000   0.6344   0.01125   0.00519  -0.1164   0.6847   1.0000
   1.250   0.6627   0.01139   0.00516  -0.1163   0.6787   1.0000
   1.500   0.6873   0.01155   0.00528  -0.1156   0.6710   1.0000
   1.750   0.7143   0.01168   0.00531  -0.1152   0.6643   1.0000
   2.000   0.7402   0.01185   0.00542  -0.1147   0.6577   1.0000
   2.250   0.7658   0.01199   0.00552  -0.1141   0.6503   1.0000
   2.500   0.7935   0.01215   0.00557  -0.1139   0.6443   1.0000
   2.750   0.8173   0.01230   0.00575  -0.1129   0.6362   1.0000
   3.000   0.8445   0.01244   0.00581  -0.1126   0.6297   1.0000
   3.250   0.8686   0.01260   0.00599  -0.1117   0.6213   1.0000
   3.500   0.8952   0.01268   0.00598  -0.1112   0.6127   1.0000
   3.750   0.9183   0.01277   0.00609  -0.1100   0.6018   1.0000
   4.000   0.9436   0.01286   0.00613  -0.1093   0.5924   1.0000
   4.250   0.9677   0.01294   0.00619  -0.1083   0.5816   1.0000
   4.500   0.9911   0.01305   0.00631  -0.1072   0.5706   1.0000
   4.750   1.0155   0.01316   0.00637  -0.1063   0.5600   1.0000
   5.000   1.0388   0.01326   0.00647  -0.1052   0.5483   1.0000
   5.250   1.0613   0.01339   0.00664  -0.1039   0.5361   1.0000
   5.500   1.0843   0.01354   0.00678  -0.1028   0.5241   1.0000
   5.750   1.1068   0.01368   0.00692  -0.1016   0.5111   1.0000
   6.000   1.1287   0.01385   0.00706  -0.1002   0.4972   1.0000
   6.250   1.1496   0.01403   0.00724  -0.0987   0.4818   1.0000
   6.500   1.1699   0.01423   0.00747  -0.0971   0.4651   1.0000
   6.750   1.1893   0.01446   0.00771  -0.0954   0.4463   1.0000
   7.000   1.2078   0.01473   0.00798  -0.0935   0.4252   1.0000
   7.250   1.2239   0.01509   0.00827  -0.0912   0.3993   1.0000
   7.500   1.2361   0.01562   0.00866  -0.0883   0.3634   1.0000
   7.750   1.2401   0.01651   0.00927  -0.0841   0.3102   1.0000
   8.000   1.2287   0.01818   0.01032  -0.0777   0.2081   1.0000
   8.250   1.2098   0.02026   0.01178  -0.0705   0.1332   1.0000
   8.500   1.2062   0.02176   0.01313  -0.0659   0.1159   1.0000
   8.750   1.2097   0.02295   0.01434  -0.0626   0.1072   1.0000
   9.000   1.2106   0.02436   0.01574  -0.0592   0.1016   1.0000
   9.250   1.2181   0.02548   0.01694  -0.0568   0.0968   1.0000
   9.500   1.2229   0.02685   0.01834  -0.0543   0.0929   1.0000
   9.750   1.2228   0.02868   0.02013  -0.0516   0.0895   1.0000
  10.000   1.2332   0.02983   0.02138  -0.0500   0.0867   1.0000
  10.250   1.2421   0.03114   0.02275  -0.0483   0.0836   1.0000
  10.500   1.2499   0.03258   0.02421  -0.0467   0.0808   1.0000
  10.750   1.2557   0.03428   0.02588  -0.0449   0.0781   1.0000
  11.000   1.2658   0.03567   0.02734  -0.0435   0.0757   1.0000
  11.250   1.2764   0.03700   0.02876  -0.0422   0.0732   1.0000
  11.500   1.2866   0.03841   0.03019  -0.0409   0.0707   1.0000
  11.750   1.2968   0.03987   0.03163  -0.0396   0.0682   1.0000
  12.000   1.3114   0.04126   0.03303  -0.0382   0.0657   1.0000
  12.250   1.3215   0.04271   0.03461  -0.0371   0.0634   1.0000
  12.500   1.3320   0.04420   0.03618  -0.0360   0.0611   1.0000
  12.750   1.3442   0.04563   0.03760  -0.0349   0.0588   1.0000
  13.000   1.3657   0.04708   0.03903  -0.0337   0.0559   1.0000
  13.250   1.3718   0.04886   0.04101  -0.0326   0.0542   1.0000
  13.500   1.3816   0.05056   0.04283  -0.0315   0.0522   1.0000
  13.750   1.3919   0.05226   0.04459  -0.0306   0.0503   1.0000
  14.000   1.4212   0.05401   0.04625  -0.0299   0.0476   1.0000
  14.250   1.4170   0.05635   0.04886  -0.0286   0.0466   1.0000
  14.500   1.4164   0.05879   0.05151  -0.0276   0.0453   1.0000
  14.750   1.4188   0.06117   0.05405  -0.0268   0.0439   1.0000
  15.000   1.4237   0.06344   0.05643  -0.0261   0.0427   1.0000
  15.250   1.4292   0.06573   0.05880  -0.0255   0.0417   1.0000
  15.500   1.4470   0.06852   0.06159  -0.0247   0.0402   1.0000
  15.750   1.4316   0.07220   0.06556  -0.0242   0.0398   1.0000
  16.000   1.4162   0.07621   0.06987  -0.0242   0.0392   1.0000
  16.250   1.4015   0.08068   0.07461  -0.0244   0.0388   1.0000
  16.500   1.3861   0.08544   0.07962  -0.0251   0.0383   1.0000
  16.750   1.3698   0.09059   0.08502  -0.0261   0.0379   1.0000
  17.000   1.3521   0.09615   0.09081  -0.0277   0.0376   1.0000
  17.250   1.3333   0.10210   0.09699  -0.0299   0.0372   1.0000
  17.500   1.3105   0.10911   0.10424  -0.0328   0.0371   1.0000
  17.750   1.2856   0.11685   0.11221  -0.0366   0.0370   1.0000
  18.000   1.2503   0.12720   0.12282  -0.0424   0.0374   1.0000
  18.250   1.2094   0.13976   0.13565  -0.0502   0.0380   1.0000
  18.500   1.1671   0.15408   0.15017  -0.0595   0.0391   1.0000
  18.750   1.1259   0.16989   0.16609  -0.0696   0.0399   1.0000
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