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GOE 625 AIRFOIL (goe625-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 625 AIRFOIL (goe625-il)
Reynolds number: 200,000
Max Cl/Cd: 58.08 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe625-il-200000.txt
Download as CSV file: xf-goe625-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 625 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0201   0.09365   0.08974  -0.1119   0.9203   0.1145
 -10.000  -0.1787   0.05859   0.05443  -0.1375   0.9058   0.0947
  -9.750  -0.1943   0.05442   0.05015  -0.1378   0.8981   0.0951
  -9.500  -0.0980   0.06631   0.06226  -0.1297   0.8952   0.1040
  -9.250  -0.0917   0.06376   0.05970  -0.1295   0.8865   0.1031
  -9.000  -0.1047   0.05859   0.05443  -0.1317   0.8791   0.1021
  -8.750  -0.2133   0.04207   0.03710  -0.1349   0.8651   0.0996
  -8.500  -0.2276   0.03616   0.03046  -0.1335   0.8594   0.1019
  -8.250  -0.2327   0.03284   0.02648  -0.1306   0.8497   0.1038
  -8.000  -0.2069   0.03187   0.02558  -0.1305   0.8442   0.1055
  -7.750  -0.1762   0.03167   0.02544  -0.1307   0.8400   0.1072
  -7.500  -0.1587   0.03088   0.02457  -0.1294   0.8313   0.1091
  -7.250  -0.1389   0.02930   0.02267  -0.1285   0.8252   0.1114
  -7.000  -0.1167   0.02763   0.02052  -0.1280   0.8205   0.1135
  -6.750  -0.0979   0.02653   0.01936  -0.1268   0.8114   0.1152
  -6.500  -0.0704   0.02587   0.01869  -0.1266   0.8050   0.1169
  -6.250  -0.0438   0.02523   0.01797  -0.1263   0.7984   0.1187
  -6.000  -0.0203   0.02448   0.01710  -0.1255   0.7894   0.1206
  -5.750   0.0076   0.02355   0.01592  -0.1254   0.7830   0.1229
  -5.500   0.0307   0.02284   0.01499  -0.1244   0.7734   0.1245
  -5.250   0.0580   0.02184   0.01386  -0.1242   0.7656   0.1262
  -5.000   0.0840   0.02130   0.01333  -0.1238   0.7562   0.1282
  -4.750   0.1114   0.02081   0.01277  -0.1235   0.7468   0.1304
  -4.500   0.1377   0.02030   0.01217  -0.1230   0.7362   0.1326
  -4.250   0.1657   0.01974   0.01143  -0.1228   0.7259   0.1349
  -4.000   0.1911   0.01935   0.01089  -0.1220   0.7127   0.1372
  -3.750   0.2178   0.01872   0.01024  -0.1217   0.7001   0.1400
  -3.250   0.2703   0.01807   0.00943  -0.1207   0.6698   0.1464
  -3.000   0.2958   0.01783   0.00902  -0.1200   0.6529   0.1502
  -2.750   0.3209   0.01745   0.00859  -0.1194   0.6363   0.1543
  -2.500   0.3462   0.01732   0.00840  -0.1188   0.6206   0.1597
  -2.250   0.3721   0.01730   0.00817  -0.1182   0.6066   0.1665
  -2.000   0.3971   0.01703   0.00791  -0.1177   0.5939   0.1745
  -1.750   0.4224   0.01693   0.00774  -0.1172   0.5820   0.1850
  -1.500   0.4487   0.01687   0.00760  -0.1169   0.5728   0.1969
  -1.250   0.4736   0.01675   0.00753  -0.1165   0.5634   0.2089
  -1.000   0.5007   0.01681   0.00745  -0.1163   0.5558   0.2211
  -0.750   0.5260   0.01673   0.00744  -0.1160   0.5483   0.2330
  -0.500   0.5521   0.01671   0.00740  -0.1157   0.5416   0.2446
  -0.250   0.5803   0.01678   0.00739  -0.1159   0.5362   0.2575
   0.000   0.6059   0.01674   0.00746  -0.1156   0.5309   0.2720
   0.250   0.6319   0.01673   0.00753  -0.1154   0.5258   0.2918
   0.500   0.6584   0.01666   0.00761  -0.1153   0.5214   0.3300
   1.000   0.6972   0.01559   0.00816  -0.1117   0.5138   0.7866
   1.250   0.7480   0.01576   0.00855  -0.1152   0.5087   0.9644
   1.500   0.8212   0.01613   0.00876  -0.1246   0.5037   1.0000
   1.750   0.8442   0.01637   0.00886  -0.1239   0.5005   1.0000
   2.000   0.8697   0.01671   0.00905  -0.1236   0.4974   1.0000
   2.250   0.8885   0.01693   0.00927  -0.1221   0.4942   1.0000
   2.500   0.9090   0.01717   0.00948  -0.1209   0.4907   1.0000
   2.750   0.9312   0.01742   0.00967  -0.1200   0.4872   1.0000
   3.000   0.9551   0.01767   0.00981  -0.1194   0.4834   1.0000
   3.250   0.9833   0.01805   0.01001  -0.1197   0.4791   1.0000
   3.500   1.0013   0.01828   0.01028  -0.1180   0.4750   1.0000
   3.750   1.0221   0.01852   0.01052  -0.1168   0.4707   1.0000
   4.000   1.0461   0.01879   0.01074  -0.1163   0.4671   1.0000
   4.250   1.0723   0.01908   0.01095  -0.1162   0.4639   1.0000
   4.500   1.1015   0.01949   0.01123  -0.1167   0.4607   1.0000
   4.750   1.1239   0.01987   0.01163  -0.1160   0.4577   1.0000
   5.000   1.1443   0.02020   0.01201  -0.1149   0.4546   1.0000
   5.250   1.1667   0.02053   0.01236  -0.1142   0.4513   1.0000
   5.500   1.1910   0.02085   0.01265  -0.1138   0.4481   1.0000
   5.750   1.2179   0.02116   0.01289  -0.1139   0.4448   1.0000
   6.000   1.2489   0.02162   0.01323  -0.1148   0.4415   1.0000
   6.250   1.2672   0.02202   0.01372  -0.1134   0.4383   1.0000
   6.500   1.2849   0.02239   0.01416  -0.1119   0.4348   1.0000
   6.750   1.3059   0.02274   0.01454  -0.1110   0.4312   1.0000
   7.000   1.3302   0.02306   0.01484  -0.1107   0.4279   1.0000
   7.250   1.3590   0.02340   0.01509  -0.1112   0.4247   1.0000
   7.500   1.3869   0.02394   0.01559  -0.1117   0.4213   1.0000
   7.750   1.3971   0.02436   0.01616  -0.1089   0.4177   1.0000
   8.000   1.4123   0.02476   0.01662  -0.1071   0.4136   1.0000
   8.250   1.4331   0.02505   0.01691  -0.1062   0.4097   1.0000
   8.500   1.4614   0.02531   0.01709  -0.1066   0.4061   1.0000
   8.750   1.4859   0.02582   0.01758  -0.1065   0.4023   1.0000
   9.000   1.4883   0.02634   0.01826  -0.1026   0.3983   1.0000
   9.250   1.4972   0.02676   0.01875  -0.0997   0.3942   1.0000
   9.500   1.5161   0.02706   0.01903  -0.0986   0.3903   1.0000
   9.750   1.5478   0.02729   0.01916  -0.0997   0.3865   1.0000
  10.000   1.5500   0.02798   0.01997  -0.0960   0.3824   1.0000
  10.250   1.5487   0.02870   0.02083  -0.0919   0.3777   1.0000
  10.500   1.5613   0.02912   0.02126  -0.0900   0.3732   1.0000
  10.750   1.5868   0.02925   0.02130  -0.0900   0.3691   1.0000
  11.000   1.5876   0.03016   0.02232  -0.0867   0.3644   1.0000
  11.250   1.5846   0.03117   0.02345  -0.0831   0.3591   1.0000
  11.500   1.5972   0.03166   0.02393  -0.0815   0.3544   1.0000
  11.750   1.6258   0.03174   0.02388  -0.0820   0.3503   1.0000
  12.000   1.6094   0.03357   0.02596  -0.0773   0.3451   1.0000
  12.250   1.6131   0.03469   0.02715  -0.0752   0.3401   1.0000
  12.500   1.6284   0.03527   0.02770  -0.0742   0.3361   1.0000
  12.750   1.6406   0.03615   0.02859  -0.0731   0.3319   1.0000
  13.000   1.6315   0.03822   0.03083  -0.0701   0.3267   1.0000
  13.250   1.6383   0.03941   0.03206  -0.0687   0.3223   1.0000
  13.500   1.6577   0.03986   0.03245  -0.0683   0.3186   1.0000
  13.750   1.6566   0.04175   0.03445  -0.0664   0.3143   1.0000
  14.000   1.6508   0.04404   0.03687  -0.0644   0.3097   1.0000
  14.250   1.6584   0.04537   0.03823  -0.0634   0.3057   1.0000
  14.500   1.6806   0.04564   0.03842  -0.0632   0.3023   1.0000
  14.750   1.6726   0.04836   0.04128  -0.0615   0.2982   1.0000
  15.000   1.6651   0.05118   0.04424  -0.0600   0.2940   1.0000
  15.250   1.6711   0.05287   0.04596  -0.0592   0.2903   1.0000
  15.500   1.6925   0.05315   0.04617  -0.0590   0.2870   1.0000
  15.750   1.6901   0.05570   0.04883  -0.0580   0.2835   1.0000
  16.000   1.6730   0.05979   0.05310  -0.0568   0.2796   1.0000
  16.250   1.6733   0.06221   0.05559  -0.0562   0.2759   1.0000
  16.500   1.6911   0.06279   0.05611  -0.0560   0.2724   1.0000
  16.750   1.7025   0.06409   0.05742  -0.0556   0.2690   1.0000
  17.000   1.6705   0.07019   0.06377  -0.0547   0.2654   1.0000
  17.250   1.6590   0.07418   0.06788  -0.0544   0.2616   1.0000
  17.500   1.6717   0.07534   0.06903  -0.0543   0.2584   1.0000
  17.750   1.7135   0.07306   0.06658  -0.0542   0.2548   1.0000
  18.000   1.6578   0.08245   0.07632  -0.0541   0.2515   1.0000
  18.250   1.6106   0.09134   0.08546  -0.0546   0.2476   1.0000
  18.500   1.6248   0.09232   0.08644  -0.0547   0.2442   1.0000
  18.750   1.6768   0.08829   0.08224  -0.0542   0.2409   1.0000
  19.000   1.6188   0.09878   0.09303  -0.0554   0.2371   1.0000
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