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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 50,000
Max Cl/Cd: 40.39 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe394-il-50000.txt
Download as CSV file: xf-goe394-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3216   0.11625   0.10945  -0.0190   1.0000   0.1119
  -8.500  -0.3222   0.11600   0.10930  -0.0217   1.0000   0.1137
  -8.250  -0.3277   0.11694   0.11039  -0.0250   1.0000   0.1143
  -8.000  -0.3047   0.10801   0.10143  -0.0228   1.0000   0.1171
  -7.750  -0.2959   0.10464   0.09808  -0.0229   1.0000   0.1204
  -7.500  -0.2926   0.10253   0.09606  -0.0236   1.0000   0.1238
  -7.250  -0.2947   0.10202   0.09569  -0.0256   1.0000   0.1267
  -7.000  -0.3030   0.10330   0.09713  -0.0286   1.0000   0.1279
  -6.750  -0.2980   0.09775   0.09166  -0.0245   1.0000   0.1303
  -6.500  -0.3002   0.09535   0.08934  -0.0216   1.0000   0.1336
  -6.250  -0.3082   0.09425   0.08832  -0.0196   1.0000   0.1363
  -6.000  -0.3158   0.09352   0.08765  -0.0188   1.0000   0.1393
  -5.750  -0.3191   0.09443   0.08860  -0.0229   1.0000   0.1421
  -5.500  -0.3186   0.09114   0.08537  -0.0216   1.0000   0.1437
  -5.250  -0.3179   0.08763   0.08190  -0.0181   1.0000   0.1466
  -5.000  -0.3139   0.08531   0.07960  -0.0178   1.0000   0.1510
  -4.750  -0.2931   0.08517   0.07937  -0.0278   1.0000   0.1577
  -4.500  -0.2950   0.08064   0.07491  -0.0225   1.0000   0.1602
  -4.250  -0.2867   0.07801   0.07227  -0.0221   1.0000   0.1678
  -4.000  -0.2703   0.07538   0.06961  -0.0257   1.0000   0.1754
  -3.750  -0.2433   0.07368   0.06778  -0.0324   1.0000   0.1879
  -3.500  -0.2405   0.06988   0.06406  -0.0287   1.0000   0.1923
  -3.000  -0.1923   0.06495   0.05897  -0.0367   1.0000   0.2184
  -2.750  -0.1726   0.06228   0.05624  -0.0385   1.0000   0.2335
  -2.500  -0.1570   0.05951   0.05349  -0.0385   1.0000   0.2507
  -2.250  -0.1326   0.05732   0.05123  -0.0412   1.0000   0.2785
  -2.000  -0.1110   0.05506   0.04895  -0.0427   1.0000   0.3079
  -1.750  -0.0942   0.05257   0.04648  -0.0424   1.0000   0.3395
  -1.500  -0.0787   0.05032   0.04425  -0.0417   1.0000   0.3847
  -0.750  -0.0559   0.04262   0.03689  -0.0308   1.0000   0.5806
  -0.500  -0.0435   0.03976   0.03412  -0.0283   1.0000   0.6390
  -0.250  -0.0055   0.03750   0.03180  -0.0323   0.9973   0.6810
   0.000   0.2618   0.03922   0.03067  -0.0929   0.9760   0.2311
   0.250   0.3270   0.03747   0.02829  -0.1004   0.9641   0.2154
   0.500   0.3851   0.03629   0.02673  -0.1065   0.9514   0.2286
   0.750   0.4405   0.03548   0.02557  -0.1120   0.9379   0.2603
   1.000   0.4907   0.03511   0.02493  -0.1164   0.9230   0.2937
   1.250   0.5361   0.03503   0.02466  -0.1197   0.9071   0.3137
   1.500   0.5784   0.03509   0.02461  -0.1224   0.8906   0.3286
   1.750   0.6185   0.03522   0.02474  -0.1246   0.8740   0.3478
   2.000   0.6575   0.03536   0.02493  -0.1265   0.8575   0.3658
   2.250   0.6953   0.03545   0.02523  -0.1281   0.8416   0.3964
   2.500   0.7283   0.03455   0.02560  -0.1288   0.8260   1.0000
   2.750   0.7647   0.03527   0.02586  -0.1296   0.8103   1.0000
   3.000   0.7962   0.03600   0.02635  -0.1298   0.7949   1.0000
   3.250   0.8250   0.03675   0.02698  -0.1296   0.7797   1.0000
   3.500   0.8515   0.03759   0.02779  -0.1293   0.7650   1.0000
   3.750   0.8770   0.03846   0.02863  -0.1287   0.7506   1.0000
   4.000   0.9013   0.03940   0.02958  -0.1281   0.7368   1.0000
   4.250   0.9262   0.04029   0.03050  -0.1274   0.7236   1.0000
   4.500   0.9620   0.04038   0.03067  -0.1271   0.7135   1.0000
   4.750   0.9797   0.04172   0.03207  -0.1261   0.6994   1.0000
   5.000   0.9962   0.04318   0.03362  -0.1250   0.6855   1.0000
   5.250   1.0116   0.04477   0.03530  -0.1239   0.6718   1.0000
   5.500   1.0272   0.04635   0.03701  -0.1229   0.6585   1.0000
   5.750   1.0449   0.04770   0.03848  -0.1218   0.6454   1.0000
   6.000   1.0692   0.04807   0.03899  -0.1202   0.6309   1.0000
   6.250   1.1080   0.04605   0.03714  -0.1175   0.6134   1.0000
   6.500   1.1575   0.04208   0.03339  -0.1138   0.5960   1.0000
   6.750   1.1944   0.04002   0.03151  -0.1111   0.5802   1.0000
   7.000   1.2141   0.04019   0.03193  -0.1089   0.5614   1.0000
   7.250   1.2476   0.03853   0.03048  -0.1062   0.5423   1.0000
   7.500   1.2881   0.03595   0.02801  -0.1032   0.5198   1.0000
   7.750   1.3183   0.03474   0.02686  -0.1002   0.4895   1.0000
   8.000   1.3428   0.03401   0.02612  -0.0967   0.4477   1.0000
   8.250   1.3569   0.03373   0.02569  -0.0924   0.3943   1.0000
   8.500   1.3640   0.03377   0.02544  -0.0880   0.3380   1.0000
   8.750   1.3645   0.03476   0.02616  -0.0837   0.2840   1.0000
   9.000   1.3617   0.03661   0.02759  -0.0796   0.2333   1.0000
   9.250   1.3591   0.03935   0.02982  -0.0759   0.1878   1.0000
   9.500   1.3672   0.04265   0.03257  -0.0732   0.1519   1.0000
  10.000   1.4108   0.04948   0.03925  -0.0706   0.1139   1.0000
  10.250   1.4304   0.05334   0.04344  -0.0693   0.1062   1.0000
  10.500   1.4502   0.05706   0.04732  -0.0683   0.1000   1.0000
  10.750   1.4593   0.06129   0.05187  -0.0666   0.0961   1.0000
  11.000   1.4554   0.06500   0.05612  -0.0639   0.0938   1.0000
  11.250   1.4490   0.06896   0.06053  -0.0613   0.0923   1.0000
  11.500   1.4377   0.07308   0.06503  -0.0587   0.0916   1.0000
  11.750   1.4199   0.07723   0.06951  -0.0560   0.0917   1.0000
  12.000   1.3979   0.08173   0.07431  -0.0542   0.0921   1.0000
  12.250   1.3730   0.08680   0.07965  -0.0535   0.0927   1.0000
  12.500   1.3462   0.09257   0.08565  -0.0540   0.0935   1.0000
  12.750   1.3185   0.09909   0.09237  -0.0556   0.0945   1.0000
  13.000   1.2916   0.10633   0.09976  -0.0582   0.0955   1.0000
  13.250   1.2679   0.11407   0.10761  -0.0615   0.0966   1.0000
  13.500   1.2493   0.12202   0.11562  -0.0648   0.0974   1.0000
  13.750   1.1306   0.15888   0.15236  -0.0948   0.1230   1.0000
  14.000   1.1350   0.16484   0.15833  -0.0959   0.1249   1.0000
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