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GOE 331 (PFALZ 60) AIRFOIL (goe331-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 331 (PFALZ 60) AIRFOIL (goe331-il)
Reynolds number: 500,000
Max Cl/Cd: 97.13 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe331-il-500000.txt
Download as CSV file: xf-goe331-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 331 (PFALZ 60) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0643   0.09055   0.08816  -0.0748   0.9249   0.0197
  -8.500  -0.0577   0.08813   0.08569  -0.0753   0.9067   0.0199
  -8.250  -0.0506   0.08566   0.08317  -0.0761   0.8899   0.0203
  -8.000  -0.0429   0.08315   0.08059  -0.0771   0.8753   0.0206
  -7.750  -0.0344   0.08060   0.07796  -0.0786   0.8627   0.0211
  -7.500  -0.0252   0.07804   0.07534  -0.0811   0.8510   0.0216
  -7.250  -0.0093   0.07498   0.07220  -0.0893   0.8407   0.0218
  -6.750   0.0264   0.06802   0.06510  -0.0992   0.8243   0.0219
  -6.500   0.0388   0.06533   0.06238  -0.0986   0.8170   0.0220
  -6.250   0.0544   0.06271   0.05970  -0.0999   0.8106   0.0222
  -6.000   0.0729   0.06004   0.05700  -0.1024   0.8039   0.0224
  -5.750   0.0936   0.05736   0.05425  -0.1054   0.7979   0.0227
  -5.500   0.1163   0.05463   0.05146  -0.1088   0.7920   0.0230
  -5.250   0.1406   0.05186   0.04864  -0.1122   0.7857   0.0236
  -5.000   0.1678   0.04902   0.04568  -0.1159   0.7802   0.0245
  -4.750   0.2156   0.04518   0.04154  -0.1242   0.7750   0.0251
  -4.500   0.2381   0.04218   0.03848  -0.1258   0.7692   0.0252
  -4.250   0.2577   0.03994   0.03619  -0.1264   0.7638   0.0254
  -4.000   0.2803   0.03790   0.03410  -0.1274   0.7582   0.0256
  -3.750   0.3053   0.03589   0.03203  -0.1286   0.7521   0.0259
  -3.500   0.3321   0.03394   0.02996  -0.1299   0.7468   0.0264
  -3.250   0.3601   0.03204   0.02792  -0.1311   0.7415   0.0272
  -3.000   0.3989   0.03002   0.02556  -0.1324   0.7353   0.0287
  -2.750   0.4256   0.02766   0.02300  -0.1330   0.7292   0.0289
  -2.500   0.4494   0.02598   0.02130  -0.1336   0.7229   0.0292
  -2.250   0.4749   0.02459   0.01984  -0.1340   0.7162   0.0296
  -2.000   0.5019   0.02331   0.01841  -0.1344   0.7098   0.0304
  -1.750   0.5301   0.02200   0.01698  -0.1345   0.7024   0.0316
  -1.500   0.5621   0.02057   0.01514  -0.1342   0.6958   0.0332
  -1.250   0.5877   0.01936   0.01393  -0.1346   0.6885   0.0337
  -1.000   0.6144   0.01846   0.01293  -0.1347   0.6808   0.0346
  -0.750   0.6425   0.01760   0.01193  -0.1346   0.6737   0.0362
  -0.500   0.6717   0.01664   0.01068  -0.1343   0.6657   0.0383
  -0.250   0.6983   0.01583   0.00983  -0.1344   0.6576   0.0393
   0.000   0.7258   0.01530   0.00916  -0.1342   0.6480   0.0419
   0.250   0.7533   0.01455   0.00826  -0.1341   0.6382   0.0450
   0.750   0.8069   0.01361   0.00713  -0.1337   0.6159   0.0536
   1.000   0.8336   0.01325   0.00665  -0.1335   0.6039   0.0611
   1.250   0.8597   0.01296   0.00627  -0.1332   0.5908   0.0707
   1.500   0.8853   0.01267   0.00593  -0.1330   0.5764   0.0834
   1.750   0.9104   0.01245   0.00566  -0.1327   0.5603   0.1003
   2.750   1.0107   0.01174   0.00428  -0.1288   0.4743   0.0481
   3.000   1.0330   0.01184   0.00420  -0.1277   0.4424   0.0454
   3.250   1.0543   0.01210   0.00428  -0.1266   0.4085   0.0449
   3.500   1.0757   0.01239   0.00443  -0.1255   0.3833   0.0465
   3.750   1.0983   0.01264   0.00457  -0.1247   0.3669   0.0462
   4.000   1.1215   0.01287   0.00473  -0.1239   0.3555   0.0461
   4.250   1.1452   0.01308   0.00489  -0.1233   0.3470   0.0467
   4.500   1.1683   0.01334   0.00509  -0.1225   0.3396   0.0482
   4.750   1.1915   0.01359   0.00531  -0.1218   0.3334   0.0504
   5.000   1.2155   0.01379   0.00553  -0.1212   0.3280   0.0630
   5.250   1.2355   0.01272   0.00601  -0.1201   0.3233   1.0000
   5.500   1.2573   0.01310   0.00632  -0.1192   0.3187   1.0000
   5.750   1.2814   0.01332   0.00655  -0.1187   0.3153   1.0000
   6.000   1.3045   0.01360   0.00681  -0.1180   0.3116   1.0000
   6.250   1.3266   0.01393   0.00711  -0.1171   0.3081   1.0000
   6.500   1.3472   0.01434   0.00748  -0.1160   0.3042   1.0000
   6.750   1.3691   0.01465   0.00780  -0.1151   0.3007   1.0000
   7.000   1.3907   0.01488   0.00807  -0.1142   0.2971   1.0000
   7.250   1.4112   0.01518   0.00837  -0.1131   0.2935   1.0000
   7.500   1.4308   0.01555   0.00874  -0.1119   0.2904   1.0000
   7.750   1.4496   0.01604   0.00920  -0.1105   0.2871   1.0000
   8.000   1.4703   0.01637   0.00957  -0.1095   0.2846   1.0000
   8.250   1.4910   0.01667   0.00994  -0.1086   0.2820   1.0000
   8.500   1.5112   0.01700   0.01032  -0.1075   0.2792   1.0000
   8.750   1.5307   0.01738   0.01072  -0.1064   0.2762   1.0000
   9.000   1.5489   0.01784   0.01118  -0.1052   0.2730   1.0000
   9.250   1.5670   0.01837   0.01172  -0.1039   0.2694   1.0000
   9.500   1.5863   0.01868   0.01213  -0.1029   0.2662   1.0000
   9.750   1.6048   0.01906   0.01256  -0.1018   0.2623   1.0000
  10.000   1.6220   0.01954   0.01307  -0.1005   0.2585   1.0000
  10.250   1.6372   0.02022   0.01373  -0.0990   0.2543   1.0000
  10.500   1.6560   0.02059   0.01422  -0.0981   0.2512   1.0000
  10.750   1.6736   0.02106   0.01476  -0.0970   0.2467   1.0000
  11.000   1.6884   0.02171   0.01542  -0.0956   0.2417   1.0000
  11.250   1.7038   0.02235   0.01613  -0.0944   0.2370   1.0000
  11.500   1.7209   0.02291   0.01677  -0.0934   0.2317   1.0000
  11.750   1.7340   0.02374   0.01761  -0.0921   0.2260   1.0000
  12.000   1.7496   0.02444   0.01839  -0.0910   0.2201   1.0000
  12.250   1.7629   0.02531   0.01930  -0.0898   0.2131   1.0000
  12.500   1.7758   0.02624   0.02028  -0.0887   0.2049   1.0000
  12.750   1.7851   0.02747   0.02150  -0.0872   0.1951   1.0000
  13.000   1.7942   0.02876   0.02280  -0.0859   0.1826   1.0000
  13.250   1.7986   0.03044   0.02443  -0.0842   0.1648   1.0000
  13.500   1.7936   0.03295   0.02680  -0.0819   0.1414   1.0000
  13.750   1.7851   0.03584   0.02958  -0.0795   0.1213   1.0000
  14.000   1.7753   0.03897   0.03263  -0.0773   0.1045   1.0000
  14.250   1.7614   0.04265   0.03621  -0.0751   0.0824   1.0000
  14.500   1.7389   0.04736   0.04077  -0.0730   0.0569   1.0000
  14.750   1.7195   0.05207   0.04543  -0.0715   0.0432   1.0000
  15.000   1.7053   0.05642   0.04982  -0.0704   0.0359   1.0000
  15.250   1.6934   0.06073   0.05420  -0.0698   0.0319   1.0000
  15.500   1.6836   0.06494   0.05850  -0.0695   0.0294   1.0000
  15.750   1.6707   0.06968   0.06334  -0.0694   0.0276   1.0000
  16.000   1.6617   0.07404   0.06782  -0.0695   0.0265   1.0000
  16.250   1.6514   0.07870   0.07260  -0.0698   0.0255   1.0000
  16.500   1.6390   0.08377   0.07779  -0.0703   0.0246   1.0000
  16.750   1.6239   0.08930   0.08344  -0.0711   0.0240   1.0000
  17.000   1.6066   0.09530   0.08957  -0.0722   0.0234   1.0000
  17.250   1.5873   0.10177   0.09617  -0.0736   0.0229   1.0000
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