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GOE 522 AIRFOIL (goe522-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 522 AIRFOIL (goe522-il)
Reynolds number: 100,000
Max Cl/Cd: 37.59 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe522-il-100000-n5.txt
Download as CSV file: xf-goe522-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 522 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.2315   0.12613   0.12028  -0.0776   0.9745   0.0543
 -13.750  -0.4084   0.08833   0.08184  -0.0944   0.9715   0.0546
 -13.500  -0.4171   0.08236   0.07572  -0.0988   0.9675   0.0549
 -13.250  -0.4185   0.07740   0.07063  -0.1031   0.9644   0.0553
 -13.000  -0.4205   0.07331   0.06643  -0.1060   0.9600   0.0557
 -12.750  -0.4234   0.06954   0.06255  -0.1084   0.9539   0.0562
 -12.500  -0.4188   0.06580   0.05874  -0.1119   0.9496   0.0566
 -12.250  -0.4102   0.06207   0.05494  -0.1162   0.9463   0.0572
 -12.000  -0.4180   0.05888   0.05171  -0.1171   0.9372   0.0577
 -11.750  -0.4134   0.05528   0.04803  -0.1206   0.9319   0.0584
 -11.250  -0.4134   0.04870   0.04126  -0.1252   0.9166   0.0599
 -11.000  -0.4039   0.04530   0.03774  -0.1291   0.9114   0.0612
 -10.750  -0.4113   0.04259   0.03495  -0.1295   0.9009   0.0619
 -10.500  -0.4074   0.03965   0.03191  -0.1320   0.8932   0.0634
 -10.250  -0.4117   0.03743   0.02958  -0.1320   0.8839   0.0649
 -10.000  -0.4191   0.03580   0.02784  -0.1302   0.8740   0.0663
  -9.750  -0.4060   0.03416   0.02612  -0.1307   0.8696   0.0698
  -9.500  -0.4267   0.03358   0.02546  -0.1242   0.8560   0.0711
  -9.250  -0.4074   0.03230   0.02411  -0.1246   0.8514   0.0769
  -9.000  -0.4085   0.03162   0.02337  -0.1209   0.8420   0.0810
  -8.750  -0.3971   0.03079   0.02248  -0.1191   0.8347   0.0871
  -8.500  -0.3700   0.02978   0.02142  -0.1200   0.8307   0.0952
  -8.250  -0.3654   0.02931   0.02090  -0.1166   0.8215   0.1011
  -8.000  -0.3478   0.02868   0.02022  -0.1154   0.8144   0.1081
  -7.750  -0.3157   0.02794   0.01940  -0.1166   0.8105   0.1171
  -7.500  -0.3026   0.02753   0.01895  -0.1144   0.8025   0.1233
  -7.250  -0.2850   0.02712   0.01842  -0.1127   0.7945   0.1293
  -7.000  -0.2515   0.02644   0.01767  -0.1139   0.7901   0.1359
  -6.750  -0.2325   0.02605   0.01719  -0.1125   0.7824   0.1414
  -6.500  -0.2156   0.02563   0.01674  -0.1107   0.7737   0.1459
  -6.250  -0.1787   0.02503   0.01599  -0.1123   0.7691   0.1529
  -6.000  -0.1657   0.02469   0.01566  -0.1098   0.7598   0.1578
  -5.750  -0.1409   0.02425   0.01514  -0.1092   0.7520   0.1647
  -5.500  -0.1030   0.02357   0.01444  -0.1110   0.7470   0.1723
  -5.250  -0.0942   0.02339   0.01422  -0.1077   0.7355   0.1779
  -5.000  -0.0619   0.02284   0.01367  -0.1084   0.7284   0.1865
  -4.750  -0.0375   0.02249   0.01327  -0.1078   0.7198   0.1952
  -4.500  -0.0167   0.02218   0.01301  -0.1065   0.7101   0.2044
  -4.250   0.0233   0.02169   0.01250  -0.1086   0.7039   0.2199
  -4.000   0.0329   0.02163   0.01248  -0.1053   0.6914   0.2320
  -3.750   0.0697   0.02129   0.01210  -0.1067   0.6839   0.2521
  -3.500   0.0844   0.02126   0.01206  -0.1043   0.6723   0.2674
  -3.250   0.1170   0.02106   0.01179  -0.1050   0.6640   0.2868
  -3.000   0.1370   0.02104   0.01170  -0.1035   0.6539   0.3027
  -2.750   0.1643   0.02094   0.01154  -0.1032   0.6451   0.3185
  -2.500   0.1895   0.02087   0.01144  -0.1026   0.6362   0.3318
  -2.250   0.2121   0.02086   0.01130  -0.1015   0.6268   0.3455
  -2.000   0.2441   0.02074   0.01117  -0.1021   0.6196   0.3582
  -1.750   0.2613   0.02082   0.01116  -0.1001   0.6105   0.3694
  -1.500   0.2900   0.02076   0.01110  -0.1001   0.6037   0.3801
  -1.250   0.3165   0.02078   0.01099  -0.0998   0.5968   0.3910
  -1.000   0.3368   0.02082   0.01105  -0.0984   0.5892   0.3993
  -0.750   0.3664   0.02081   0.01094  -0.0985   0.5830   0.4098
  -0.500   0.3926   0.02085   0.01093  -0.0982   0.5769   0.4196
  -0.250   0.4124   0.02096   0.01106  -0.0967   0.5704   0.4301
   0.000   0.4391   0.02103   0.01107  -0.0964   0.5650   0.4421
   0.250   0.4731   0.02106   0.01103  -0.0974   0.5603   0.4546
   0.500   0.4909   0.02122   0.01120  -0.0957   0.5545   0.4659
   0.750   0.5114   0.02135   0.01137  -0.0943   0.5488   0.4779
   1.000   0.5381   0.02145   0.01142  -0.0941   0.5439   0.4908
   1.250   0.5726   0.02153   0.01144  -0.0952   0.5399   0.5039
   1.500   0.5924   0.02172   0.01165  -0.0939   0.5351   0.5155
   1.750   0.6102   0.02191   0.01190  -0.0921   0.5300   0.5277
   2.000   0.6336   0.02207   0.01206  -0.0914   0.5251   0.5422
   2.250   0.6631   0.02218   0.01212  -0.0916   0.5205   0.5597
   2.500   0.6873   0.02233   0.01229  -0.0909   0.5154   0.5762
   2.750   0.6975   0.02259   0.01263  -0.0879   0.5093   0.5921
   3.000   0.7177   0.02276   0.01279  -0.0865   0.5028   0.6112
   3.250   0.7511   0.02277   0.01272  -0.0874   0.4968   0.6337
   3.500   0.7555   0.02312   0.01321  -0.0834   0.4901   0.6542
   3.750   0.7698   0.02336   0.01354  -0.0811   0.4839   0.6797
   4.000   0.7929   0.02346   0.01371  -0.0802   0.4788   0.7115
   4.500   0.8328   0.02387   0.01442  -0.0774   0.4699   0.8075
   4.750   0.8700   0.02418   0.01495  -0.0798   0.4641   0.9068
   5.000   0.9004   0.02446   0.01516  -0.0808   0.4591   1.0000
   5.250   0.9278   0.02468   0.01522  -0.0809   0.4549   1.0000
   5.500   0.9362   0.02524   0.01579  -0.0782   0.4499   1.0000
   5.750   0.9440   0.02584   0.01641  -0.0755   0.4444   1.0000
   6.000   0.9599   0.02627   0.01679  -0.0739   0.4394   1.0000
   6.250   0.9833   0.02653   0.01694  -0.0734   0.4351   1.0000
   6.500   0.9942   0.02714   0.01755  -0.0713   0.4301   1.0000
   6.750   0.9981   0.02796   0.01842  -0.0683   0.4244   1.0000
   7.000   1.0117   0.02852   0.01895  -0.0666   0.4193   1.0000
   7.250   1.0341   0.02879   0.01912  -0.0660   0.4149   1.0000
   7.500   1.0389   0.02971   0.02009  -0.0634   0.4095   1.0000
   7.750   1.0419   0.03072   0.02116  -0.0607   0.4033   1.0000
   8.000   1.0564   0.03128   0.02168  -0.0593   0.3981   1.0000
   8.250   1.0738   0.03176   0.02209  -0.0582   0.3932   1.0000
   8.500   1.0672   0.03336   0.02382  -0.0549   0.3860   1.0000
   8.750   1.0777   0.03418   0.02461  -0.0533   0.3802   1.0000
   9.000   1.0957   0.03465   0.02500  -0.0524   0.3752   1.0000
   9.250   1.0861   0.03670   0.02719  -0.0494   0.3674   1.0000
   9.500   1.0970   0.03759   0.02805  -0.0480   0.3615   1.0000
   9.750   1.1063   0.03866   0.02910  -0.0467   0.3557   1.0000
  10.000   1.1012   0.04079   0.03131  -0.0445   0.3484   1.0000
  10.250   1.1163   0.04153   0.03200  -0.0437   0.3434   1.0000
  10.500   1.1182   0.04332   0.03383  -0.0422   0.3373   1.0000
  10.750   1.1164   0.04549   0.03605  -0.0407   0.3306   1.0000
  11.000   1.1340   0.04611   0.03661  -0.0401   0.3262   1.0000
  11.250   1.1338   0.04831   0.03885  -0.0389   0.3205   1.0000
  11.500   1.1314   0.05079   0.04140  -0.0377   0.3147   1.0000
  11.750   1.1468   0.05169   0.04225  -0.0372   0.3107   1.0000
  12.000   1.1668   0.05220   0.04269  -0.0368   0.3074   1.0000
  12.250   1.1481   0.05645   0.04711  -0.0356   0.3012   1.0000
  12.500   1.1534   0.05843   0.04910  -0.0350   0.2969   1.0000
  12.750   1.1727   0.05900   0.04962  -0.0347   0.2940   1.0000
  13.000   1.1945   0.05936   0.04992  -0.0344   0.2915   1.0000
  13.250   1.1575   0.06602   0.05683  -0.0336   0.2854   1.0000
  13.500   1.1560   0.06901   0.05988  -0.0334   0.2818   1.0000
  13.750   1.1702   0.07020   0.06107  -0.0331   0.2794   1.0000
  14.000   1.1920   0.07054   0.06138  -0.0329   0.2777   1.0000
  14.250   1.2181   0.07041   0.06121  -0.0326   0.2763   1.0000
  14.500   1.0587   0.09415   0.08550  -0.0352   0.2632   1.0000
  14.750   1.0782   0.09465   0.08600  -0.0351   0.2620   1.0000
  15.000   1.1026   0.09447   0.08582  -0.0347   0.2612   1.0000
  15.250   1.1289   0.09404   0.08537  -0.0344   0.2604   1.0000
  16.750   0.8743   0.15843   0.15053  -0.0544   0.2205   1.0000
  17.000   0.8847   0.16028   0.15240  -0.0551   0.2177   1.0000
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