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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 200,000
Max Cl/Cd: 85.88 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe394-il-200000-n5.txt
Download as CSV file: xf-goe394-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2789   0.09714   0.09376  -0.0310   0.9154   0.0287
  -7.750  -0.2719   0.09434   0.09093  -0.0336   0.8927   0.0289
  -7.250  -0.2546   0.08682   0.08333  -0.0326   0.8668   0.0266
  -7.000  -0.2437   0.08331   0.07977  -0.0353   0.8555   0.0253
  -6.750  -0.2301   0.07971   0.07611  -0.0389   0.8464   0.0249
  -6.500  -0.2131   0.07634   0.07270  -0.0430   0.8386   0.0262
  -6.250  -0.1921   0.07236   0.06864  -0.0491   0.8320   0.0277
  -6.000  -0.1707   0.06832   0.06454  -0.0543   0.8265   0.0276
  -5.750  -0.1450   0.06388   0.06000  -0.0608   0.8213   0.0279
  -5.500  -0.1168   0.05946   0.05550  -0.0677   0.8170   0.0304
  -5.250  -0.0988   0.05858   0.05459  -0.0672   0.8132   0.0328
  -5.000  -0.0684   0.05449   0.05041  -0.0733   0.8089   0.0330
  -4.750  -0.0357   0.05034   0.04614  -0.0795   0.8052   0.0333
  -4.500  -0.0026   0.04690   0.04256  -0.0848   0.8014   0.0355
  -4.250   0.0352   0.04241   0.03787  -0.0915   0.7967   0.0363
  -4.000   0.0736   0.03779   0.03301  -0.0977   0.7910   0.0366
  -3.750   0.1144   0.03255   0.02740  -0.1040   0.7860   0.0384
  -3.500   0.1552   0.02611   0.02045  -0.1099   0.7811   0.0388
  -3.250   0.1937   0.01863   0.01186  -0.1147   0.7766   0.0394
  -3.000   0.2230   0.01671   0.00944  -0.1154   0.7722   0.0401
  -2.750   0.2513   0.01558   0.00802  -0.1156   0.7682   0.0418
  -2.500   0.2798   0.01487   0.00714  -0.1158   0.7634   0.0429
  -2.250   0.3079   0.01424   0.00631  -0.1157   0.7583   0.0436
  -2.000   0.3358   0.01376   0.00565  -0.1155   0.7541   0.0446
  -1.750   0.3641   0.01335   0.00515  -0.1155   0.7493   0.0459
  -1.500   0.3922   0.01302   0.00473  -0.1154   0.7449   0.0476
  -1.250   0.4201   0.01275   0.00436  -0.1152   0.7409   0.0498
  -1.000   0.4481   0.01255   0.00417  -0.1150   0.7366   0.0535
  -0.750   0.4761   0.01245   0.00412  -0.1149   0.7316   0.0607
  -0.500   0.5040   0.01250   0.00417  -0.1147   0.7268   0.0733
  -0.250   0.5318   0.01266   0.00424  -0.1144   0.7220   0.0864
   0.000   0.5597   0.01278   0.00430  -0.1142   0.7162   0.0958
   0.250   0.5872   0.01274   0.00425  -0.1140   0.7107   0.1009
   0.500   0.6148   0.01275   0.00424  -0.1138   0.7047   0.1072
   0.750   0.6423   0.01268   0.00414  -0.1136   0.6980   0.1101
   1.000   0.6696   0.01256   0.00407  -0.1134   0.6917   0.1149
   1.250   0.6971   0.01254   0.00408  -0.1132   0.6835   0.1220
   1.500   0.7243   0.01239   0.00399  -0.1130   0.6757   0.1267
   1.750   0.7517   0.01228   0.00393  -0.1127   0.6663   0.1284
   2.000   0.7790   0.01219   0.00390  -0.1125   0.6555   0.1302
   2.250   0.8062   0.01211   0.00387  -0.1123   0.6432   0.1322
   2.500   0.8334   0.01204   0.00385  -0.1120   0.6277   0.1344
   2.750   0.8604   0.01199   0.00380  -0.1116   0.6078   0.1366
   3.000   0.8870   0.01196   0.00374  -0.1112   0.5820   0.1399
   3.250   0.9125   0.01202   0.00368  -0.1105   0.5516   0.1453
   3.500   0.9373   0.01224   0.00374  -0.1099   0.5226   0.1521
   3.750   0.9622   0.01249   0.00391  -0.1092   0.4997   0.1642
   4.000   0.9874   0.01267   0.00416  -0.1088   0.4826   0.2186
   4.250   1.0134   0.01180   0.00446  -0.1086   0.4682   1.0000
   4.500   1.0389   0.01214   0.00471  -0.1081   0.4529   1.0000
   4.750   1.0643   0.01247   0.00498  -0.1077   0.4392   1.0000
   5.250   1.1152   0.01310   0.00558  -0.1068   0.4139   1.0000
   5.500   1.1406   0.01341   0.00590  -0.1064   0.4015   1.0000
   5.750   1.1655   0.01374   0.00623  -0.1059   0.3869   1.0000
   6.000   1.1904   0.01408   0.00660  -0.1054   0.3730   1.0000
   6.250   1.2151   0.01442   0.00697  -0.1049   0.3597   1.0000
   6.500   1.2397   0.01477   0.00736  -0.1043   0.3461   1.0000
   6.750   1.2636   0.01516   0.00778  -0.1037   0.3276   1.0000
   7.000   1.2849   0.01576   0.00826  -0.1029   0.2896   1.0000
   7.250   1.3017   0.01683   0.00894  -0.1016   0.2195   1.0000
   7.500   1.3153   0.01834   0.00996  -0.1000   0.1490   1.0000
   7.750   1.3326   0.01941   0.01087  -0.0988   0.1219   1.0000
   8.000   1.3508   0.02033   0.01174  -0.0976   0.1048   1.0000
   8.250   1.3698   0.02113   0.01257  -0.0965   0.0883   1.0000
   8.500   1.3862   0.02215   0.01348  -0.0951   0.0613   1.0000
   8.750   1.3979   0.02358   0.01470  -0.0932   0.0366   1.0000
   9.000   1.4102   0.02487   0.01599  -0.0913   0.0280   1.0000
   9.250   1.4223   0.02609   0.01728  -0.0893   0.0237   1.0000
   9.500   1.4329   0.02728   0.01855  -0.0872   0.0208   1.0000
   9.750   1.4384   0.02877   0.02012  -0.0845   0.0187   1.0000
  10.000   1.4458   0.03014   0.02167  -0.0822   0.0178   1.0000
  10.250   1.4521   0.03166   0.02334  -0.0801   0.0169   1.0000
  10.500   1.4573   0.03334   0.02516  -0.0781   0.0160   1.0000
  10.750   1.4619   0.03516   0.02710  -0.0763   0.0152   1.0000
  11.000   1.4655   0.03714   0.02920  -0.0746   0.0144   1.0000
  11.250   1.4661   0.03950   0.03166  -0.0731   0.0137   1.0000
  11.500   1.4618   0.04247   0.03474  -0.0715   0.0130   1.0000
  11.750   1.4633   0.04492   0.03732  -0.0702   0.0127   1.0000
  12.000   1.4646   0.04746   0.04001  -0.0690   0.0124   1.0000
  12.250   1.4651   0.05013   0.04283  -0.0679   0.0120   1.0000
  12.500   1.4649   0.05292   0.04577  -0.0669   0.0117   1.0000
  12.750   1.4642   0.05583   0.04886  -0.0659   0.0115   1.0000
  13.000   1.4630   0.05884   0.05202  -0.0651   0.0112   1.0000
  13.250   1.4613   0.06198   0.05531  -0.0644   0.0109   1.0000
  13.500   1.4591   0.06525   0.05872  -0.0638   0.0107   1.0000
  13.750   1.4561   0.06866   0.06228  -0.0635   0.0104   1.0000
  14.000   1.4524   0.07227   0.06603  -0.0635   0.0101   1.0000
  14.250   1.4484   0.07606   0.06996  -0.0638   0.0099   1.0000
  14.500   1.4433   0.08011   0.07413  -0.0643   0.0097   1.0000
  14.750   1.4375   0.08440   0.07855  -0.0650   0.0095   1.0000
  15.000   1.4302   0.08901   0.08329  -0.0658   0.0092   1.0000
  15.250   1.4211   0.09405   0.08846  -0.0668   0.0091   1.0000
  15.500   1.4129   0.09931   0.09394  -0.0686   0.0090   1.0000
  15.750   1.4037   0.10490   0.09974  -0.0707   0.0089   1.0000
  16.000   1.3937   0.11081   0.10585  -0.0731   0.0088   1.0000
  16.250   1.3826   0.11713   0.11238  -0.0760   0.0088   1.0000
  16.500   1.3707   0.12375   0.11920  -0.0792   0.0087   1.0000
  16.750   1.3582   0.13078   0.12642  -0.0829   0.0087   1.0000
  17.000   1.3452   0.13818   0.13401  -0.0871   0.0087   1.0000
  17.250   1.3319   0.14601   0.14202  -0.0917   0.0087   1.0000
  17.500   1.3182   0.15434   0.15053  -0.0969   0.0087   1.0000
  17.750   1.3039   0.16327   0.15962  -0.1026   0.0087   1.0000
  18.000   1.2893   0.17287   0.16938  -0.1089   0.0088   1.0000
  18.250   1.2740   0.18343   0.18007  -0.1158   0.0089   1.0000
  18.500   1.2571   0.19553   0.19230  -0.1237   0.0090   1.0000
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