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GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 430 AIRFOIL (goe430-il)
Reynolds number: 100,000
Max Cl/Cd: 60.87 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe430-il-100000-n5.txt
Download as CSV file: xf-goe430-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 430 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3390   0.11889   0.11328  -0.0493   1.0000   0.0673
 -11.250  -0.3500   0.11449   0.10893  -0.0507   1.0000   0.0681
 -11.000  -0.3641   0.10981   0.10430  -0.0520   1.0000   0.0686
 -10.750  -0.3632   0.10794   0.10248  -0.0506   1.0000   0.0691
 -10.500  -0.3718   0.10489   0.09948  -0.0500   1.0000   0.0692
 -10.250  -0.3814   0.10204   0.09668  -0.0490   1.0000   0.0692
 -10.000  -0.3899   0.09968   0.09437  -0.0476   1.0000   0.0695
  -9.750  -0.3939   0.09826   0.09299  -0.0457   1.0000   0.0700
  -9.500  -0.3887   0.09611   0.09085  -0.0461   0.9982   0.0710
  -9.250  -0.3753   0.09227   0.08698  -0.0502   0.9940   0.0722
  -9.000  -0.3705   0.08701   0.08171  -0.0551   0.9883   0.0728
  -8.500  -0.4487   0.04018   0.03378  -0.1146   0.9579   0.0744
  -8.250  -0.4263   0.03657   0.02972  -0.1191   0.9509   0.0761
  -8.000  -0.3942   0.03342   0.02606  -0.1239   0.9468   0.0778
  -7.750  -0.3583   0.03096   0.02312  -0.1281   0.9440   0.0791
  -7.500  -0.3304   0.02945   0.02141  -0.1295   0.9387   0.0803
  -7.250  -0.2999   0.02841   0.02030  -0.1310   0.9339   0.0816
  -7.000  -0.2647   0.02744   0.01925  -0.1332   0.9306   0.0835
  -6.750  -0.2269   0.02649   0.01814  -0.1359   0.9281   0.0862
  -6.500  -0.1990   0.02563   0.01711  -0.1366   0.9222   0.0888
  -6.250  -0.1665   0.02471   0.01599  -0.1380   0.9174   0.0914
  -6.000  -0.1311   0.02399   0.01527  -0.1399   0.9139   0.0940
  -5.750  -0.0937   0.02332   0.01454  -0.1421   0.9112   0.0975
  -5.500  -0.0681   0.02281   0.01394  -0.1420   0.9036   0.1014
  -5.250  -0.0335   0.02223   0.01333  -0.1435   0.8987   0.1069
  -5.000   0.0050   0.02165   0.01266  -0.1456   0.8949   0.1156
  -4.750   0.0319   0.02126   0.01229  -0.1455   0.8858   0.1234
  -4.500   0.0683   0.02067   0.01160  -0.1470   0.8800   0.1351
  -4.250   0.0980   0.02027   0.01109  -0.1473   0.8712   0.1471
  -4.000   0.1311   0.01980   0.01062  -0.1482   0.8643   0.1593
  -3.750   0.1612   0.01944   0.01025  -0.1486   0.8570   0.1709
  -3.500   0.1909   0.01914   0.00992  -0.1489   0.8495   0.1820
  -3.250   0.2248   0.01877   0.00953  -0.1499   0.8448   0.1934
  -3.000   0.2500   0.01863   0.00945  -0.1494   0.8348   0.2052
  -2.750   0.2827   0.01835   0.00918  -0.1501   0.8292   0.2214
  -2.500   0.3089   0.01827   0.00913  -0.1498   0.8195   0.2369
  -2.250   0.3407   0.01800   0.00888  -0.1503   0.8133   0.2530
  -2.000   0.3674   0.01786   0.00877  -0.1500   0.8034   0.2666
  -1.750   0.3992   0.01757   0.00847  -0.1504   0.7966   0.2835
  -1.500   0.4256   0.01745   0.00838  -0.1501   0.7860   0.3021
  -1.250   0.4561   0.01721   0.00815  -0.1503   0.7781   0.3233
  -1.000   0.4839   0.01708   0.00807  -0.1501   0.7678   0.3437
  -0.750   0.5127   0.01693   0.00798  -0.1501   0.7585   0.3650
  -0.500   0.5422   0.01680   0.00789  -0.1501   0.7495   0.3889
  -0.250   0.5699   0.01676   0.00791  -0.1499   0.7390   0.4139
   0.000   0.5998   0.01666   0.00783  -0.1499   0.7302   0.4406
   0.250   0.6274   0.01665   0.00786  -0.1496   0.7193   0.4654
   0.500   0.6556   0.01664   0.00786  -0.1494   0.7088   0.4899
   1.000   0.7120   0.01661   0.00787  -0.1488   0.6866   0.5438
   1.250   0.7389   0.01664   0.00793  -0.1483   0.6742   0.5717
   1.500   0.7664   0.01668   0.00798  -0.1478   0.6625   0.6003
   1.750   0.7939   0.01674   0.00802  -0.1473   0.6512   0.6291
   2.000   0.8200   0.01684   0.00815  -0.1467   0.6395   0.6558
   2.250   0.8468   0.01693   0.00824  -0.1462   0.6289   0.6831
   2.500   0.8733   0.01699   0.00830  -0.1457   0.6183   0.7087
   2.750   0.8983   0.01707   0.00844  -0.1449   0.6071   0.7339
   3.000   0.9234   0.01711   0.00852  -0.1441   0.5976   0.7637
   3.250   0.9453   0.01708   0.00865  -0.1425   0.5877   0.8100
   3.500   0.9678   0.01701   0.00870  -0.1411   0.5787   1.0000
   3.750   0.9958   0.01729   0.00890  -0.1412   0.5694   1.0000
   4.000   1.0229   0.01758   0.00916  -0.1411   0.5599   1.0000
   4.250   1.0504   0.01786   0.00938  -0.1410   0.5515   1.0000
   4.500   1.0762   0.01817   0.00969  -0.1407   0.5412   1.0000
   4.750   1.1020   0.01846   0.00992  -0.1402   0.5304   1.0000
   5.000   1.1271   0.01875   0.01019  -0.1397   0.5193   1.0000
   5.250   1.1518   0.01908   0.01053  -0.1391   0.5087   1.0000
   5.500   1.1764   0.01940   0.01082  -0.1385   0.4981   1.0000
   5.750   1.2003   0.01973   0.01114  -0.1377   0.4866   1.0000
   6.000   1.2233   0.02010   0.01152  -0.1368   0.4744   1.0000
   6.250   1.2461   0.02047   0.01190  -0.1359   0.4626   1.0000
   6.500   1.2684   0.02087   0.01227  -0.1349   0.4504   1.0000
   6.750   1.2896   0.02130   0.01271  -0.1337   0.4372   1.0000
   7.000   1.3097   0.02176   0.01320  -0.1324   0.4227   1.0000
   7.250   1.3289   0.02226   0.01371  -0.1310   0.4077   1.0000
   7.500   1.3467   0.02279   0.01427  -0.1293   0.3907   1.0000
   7.750   1.3627   0.02337   0.01487  -0.1274   0.3711   1.0000
   8.000   1.3776   0.02398   0.01553  -0.1254   0.3474   1.0000
   8.250   1.3899   0.02469   0.01620  -0.1230   0.3203   1.0000
   8.500   1.3972   0.02557   0.01696  -0.1199   0.2927   1.0000
   8.750   1.4035   0.02666   0.01790  -0.1169   0.2724   1.0000
   9.000   1.4101   0.02786   0.01901  -0.1141   0.2580   1.0000
   9.250   1.4166   0.02914   0.02022  -0.1115   0.2470   1.0000
   9.500   1.4257   0.03035   0.02144  -0.1093   0.2375   1.0000
   9.750   1.4330   0.03170   0.02278  -0.1069   0.2297   1.0000
  10.000   1.4427   0.03295   0.02410  -0.1050   0.2217   1.0000
  10.500   1.4585   0.03578   0.02703  -0.1010   0.2061   1.0000
  10.750   1.4635   0.03743   0.02865  -0.0988   0.1982   1.0000
  11.000   1.4714   0.03891   0.03028  -0.0972   0.1885   1.0000
  11.250   1.4754   0.04070   0.03208  -0.0953   0.1799   1.0000
  11.500   1.4813   0.04241   0.03393  -0.0938   0.1700   1.0000
  11.750   1.4860   0.04426   0.03586  -0.0923   0.1612   1.0000
  12.000   1.4894   0.04629   0.03797  -0.0909   0.1526   1.0000
  12.250   1.4945   0.04823   0.04004  -0.0897   0.1445   1.0000
  12.500   1.4959   0.05056   0.04241  -0.0885   0.1374   1.0000
  12.750   1.4999   0.05274   0.04470  -0.0875   0.1295   1.0000
  13.000   1.5000   0.05535   0.04735  -0.0865   0.1227   1.0000
  13.250   1.5017   0.05788   0.04999  -0.0857   0.1156   1.0000
  13.500   1.5007   0.06080   0.05296  -0.0850   0.1095   1.0000
  13.750   1.4996   0.06384   0.05609  -0.0845   0.1023   1.0000
  14.000   1.4965   0.06720   0.05949  -0.0841   0.0961   1.0000
  14.250   1.4918   0.07085   0.06320  -0.0839   0.0893   1.0000
  14.500   1.4870   0.07464   0.06706  -0.0839   0.0825   1.0000
  14.750   1.4803   0.07878   0.07126  -0.0841   0.0761   1.0000
  15.000   1.4774   0.08251   0.07516  -0.0843   0.0685   1.0000
  15.250   1.4730   0.08655   0.07934  -0.0847   0.0592   1.0000
  15.500   1.4656   0.09111   0.08398  -0.0854   0.0489   1.0000
  15.750   1.4541   0.09642   0.08931  -0.0866   0.0434   1.0000
  16.000   1.4414   0.10203   0.09494  -0.0881   0.0401   1.0000
  16.250   1.4290   0.10774   0.10074  -0.0898   0.0379   1.0000
  16.500   1.4162   0.11367   0.10676  -0.0918   0.0361   1.0000
  16.750   1.4029   0.11985   0.11305  -0.0941   0.0348   1.0000
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