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GOE 417 AIRFOIL (goe417-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 417 AIRFOIL (goe417-il)
Reynolds number: 200,000
Max Cl/Cd: 78.39 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe417-il-200000-n5.txt
Download as CSV file: xf-goe417-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 417 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2745   0.10897   0.10560  -0.0250   1.0000   0.0158
  -8.500  -0.2764   0.10716   0.10384  -0.0236   1.0000   0.0160
  -8.250  -0.2797   0.10549   0.10223  -0.0220   1.0000   0.0161
  -8.000  -0.2691   0.10254   0.09929  -0.0241   0.9979   0.0165
  -7.750  -0.2521   0.09902   0.09577  -0.0281   0.9941   0.0170
  -7.500  -0.2344   0.09564   0.09240  -0.0323   0.9893   0.0184
  -7.250  -0.2153   0.09223   0.08899  -0.0371   0.9837   0.0191
  -7.000  -0.1889   0.08905   0.08579  -0.0458   0.9767   0.0197
  -6.750  -0.1663   0.08569   0.08242  -0.0528   0.9691   0.0198
  -6.500  -0.1377   0.08171   0.07841  -0.0605   0.9655   0.0199
  -6.250  -0.1158   0.07815   0.07483  -0.0657   0.9585   0.0199
  -6.000  -0.0866   0.07397   0.07061  -0.0723   0.9546   0.0199
  -5.750  -0.0534   0.06957   0.06617  -0.0794   0.9520   0.0200
  -5.500  -0.0304   0.06594   0.06250  -0.0834   0.9444   0.0200
  -5.250  -0.0185   0.06195   0.05855  -0.0825   0.9409   0.0206
  -5.000   0.0069   0.05915   0.05572  -0.0854   0.9380   0.0232
  -4.750   0.0456   0.05620   0.05266  -0.0931   0.9299   0.0258
  -4.500   0.0875   0.05237   0.04869  -0.1006   0.9251   0.0261
  -4.250   0.1202   0.04882   0.04502  -0.1049   0.9181   0.0262
  -4.000   0.1576   0.04511   0.04114  -0.1097   0.9112   0.0264
  -3.750   0.1748   0.04126   0.03729  -0.1107   0.9027   0.0275
  -3.500   0.2032   0.03869   0.03462  -0.1128   0.8949   0.0290
  -3.250   0.2332   0.03615   0.03195  -0.1149   0.8840   0.0313
  -3.000   0.2829   0.03393   0.02926  -0.1189   0.8741   0.0355
  -2.750   0.3039   0.03019   0.02551  -0.1203   0.8649   0.0379
  -2.500   0.3309   0.02832   0.02351  -0.1211   0.8549   0.0403
  -2.250   0.3693   0.02601   0.02067  -0.1227   0.8461   0.0482
  -1.750   0.4244   0.02185   0.01618  -0.1236   0.8264   0.0437
  -1.500   0.4555   0.01927   0.01316  -0.1238   0.8160   0.0387
  -1.250   0.4834   0.01829   0.01195  -0.1237   0.8043   0.0417
  -1.000   0.5124   0.01685   0.01015  -0.1235   0.7917   0.0402
  -0.750   0.5408   0.01562   0.00854  -0.1231   0.7777   0.0388
  -0.500   0.5683   0.01478   0.00741  -0.1227   0.7624   0.0384
  -0.250   0.5952   0.01414   0.00655  -0.1222   0.7452   0.0386
   0.000   0.6217   0.01365   0.00587  -0.1216   0.7252   0.0393
   0.250   0.6478   0.01334   0.00541  -0.1210   0.7031   0.0416
   0.500   0.6736   0.01301   0.00488  -0.1203   0.6795   0.0419
   0.750   0.6991   0.01273   0.00445  -0.1196   0.6572   0.0416
   1.000   0.7241   0.01255   0.00412  -0.1188   0.6356   0.0415
   1.250   0.7489   0.01244   0.00388  -0.1180   0.6144   0.0415
   1.500   0.7734   0.01238   0.00372  -0.1172   0.5927   0.0417
   1.750   0.7978   0.01239   0.00362  -0.1165   0.5714   0.0422
   2.000   0.8222   0.01243   0.00356  -0.1157   0.5490   0.0430
   2.250   0.8461   0.01254   0.00354  -0.1149   0.5246   0.0443
   2.750   0.8926   0.01293   0.00360  -0.1130   0.4686   0.0480
   3.000   0.9154   0.01316   0.00370  -0.1120   0.4402   0.0557
   3.500   0.9657   0.01236   0.00418  -0.1115   0.3930   1.0000
   4.000   1.0137   0.01296   0.00457  -0.1100   0.3676   1.0000
   4.250   1.0378   0.01325   0.00480  -0.1094   0.3575   1.0000
   4.500   1.0615   0.01357   0.00505  -0.1086   0.3483   1.0000
   4.750   1.0857   0.01385   0.00532  -0.1080   0.3392   1.0000
   5.000   1.1095   0.01416   0.00561  -0.1073   0.3309   1.0000
   5.250   1.1333   0.01447   0.00591  -0.1066   0.3225   1.0000
   5.500   1.1571   0.01478   0.00622  -0.1060   0.3146   1.0000
   5.750   1.1805   0.01511   0.00658  -0.1052   0.3064   1.0000
   6.000   1.2041   0.01542   0.00693  -0.1045   0.2983   1.0000
   6.250   1.2269   0.01577   0.00730  -0.1037   0.2900   1.0000
   6.500   1.2503   0.01608   0.00767  -0.1030   0.2808   1.0000
   6.750   1.2727   0.01645   0.00809  -0.1022   0.2702   1.0000
   7.000   1.2944   0.01683   0.00848  -0.1012   0.2539   1.0000
   7.250   1.3142   0.01732   0.00889  -0.1000   0.2302   1.0000
   7.500   1.3333   0.01789   0.00936  -0.0988   0.2032   1.0000
   7.750   1.3519   0.01852   0.00994  -0.0975   0.1818   1.0000
   8.000   1.3696   0.01923   0.01058  -0.0960   0.1629   1.0000
   8.250   1.3866   0.01999   0.01128  -0.0945   0.1445   1.0000
   8.500   1.4008   0.02098   0.01213  -0.0927   0.1172   1.0000
   8.750   1.4059   0.02274   0.01344  -0.0897   0.0505   1.0000
   9.000   1.4093   0.02444   0.01499  -0.0862   0.0231   1.0000
   9.250   1.4194   0.02554   0.01620  -0.0836   0.0180   1.0000
   9.500   1.4301   0.02658   0.01739  -0.0812   0.0161   1.0000
   9.750   1.4387   0.02777   0.01875  -0.0786   0.0147   1.0000
  10.000   1.4448   0.02914   0.02030  -0.0758   0.0136   1.0000
  10.250   1.4453   0.03093   0.02231  -0.0726   0.0125   1.0000
  10.500   1.4482   0.03254   0.02409  -0.0700   0.0118   1.0000
  10.750   1.4519   0.03414   0.02586  -0.0677   0.0111   1.0000
  11.000   1.4517   0.03614   0.02802  -0.0652   0.0107   1.0000
  11.250   1.4500   0.03837   0.03042  -0.0631   0.0103   1.0000
  11.500   1.4467   0.04089   0.03313  -0.0611   0.0101   1.0000
  11.750   1.4424   0.04369   0.03608  -0.0596   0.0098   1.0000
  12.000   1.4372   0.04677   0.03930  -0.0584   0.0095   1.0000
  12.250   1.4317   0.05009   0.04277  -0.0576   0.0093   1.0000
  12.500   1.4258   0.05367   0.04649  -0.0572   0.0092   1.0000
  12.750   1.4197   0.05748   0.05044  -0.0571   0.0090   1.0000
  13.000   1.4134   0.06150   0.05459  -0.0573   0.0088   1.0000
  13.250   1.4068   0.06571   0.05891  -0.0578   0.0086   1.0000
  13.500   1.3995   0.07010   0.06340  -0.0583   0.0084   1.0000
  13.750   1.3921   0.07453   0.06791  -0.0585   0.0081   1.0000
  14.000   1.3901   0.07848   0.07202  -0.0594   0.0079   1.0000
  14.250   1.3877   0.08262   0.07635  -0.0605   0.0076   1.0000
  14.500   1.3848   0.08686   0.08074  -0.0615   0.0074   1.0000
  14.750   1.3818   0.09119   0.08523  -0.0626   0.0073   1.0000
  15.000   1.3786   0.09563   0.08982  -0.0638   0.0071   1.0000
  15.250   1.3748   0.10025   0.09464  -0.0652   0.0070   1.0000
  15.500   1.3706   0.10504   0.09960  -0.0668   0.0069   1.0000
  15.750   1.3657   0.11010   0.10483  -0.0687   0.0068   1.0000
  16.000   1.3601   0.11539   0.11030  -0.0709   0.0068   1.0000
  16.250   1.3535   0.12100   0.11609  -0.0735   0.0067   1.0000
  16.500   1.3463   0.12688   0.12215  -0.0764   0.0066   1.0000
  16.750   1.3387   0.13303   0.12848  -0.0797   0.0066   1.0000
  17.000   1.3304   0.13947   0.13509  -0.0833   0.0066   1.0000
  17.250   1.3215   0.14623   0.14202  -0.0873   0.0066   1.0000
  17.500   1.3122   0.15327   0.14924  -0.0916   0.0066   1.0000
  17.750   1.3025   0.16064   0.15677  -0.0963   0.0066   1.0000
  18.000   1.2923   0.16844   0.16473  -0.1014   0.0066   1.0000
  18.250   1.2818   0.17667   0.17312  -0.1068   0.0066   1.0000
  18.500   1.2707   0.18547   0.18207  -0.1126   0.0067   1.0000
  18.750   1.2592   0.19493   0.19166  -0.1188   0.0068   1.0000
  19.000   1.2468   0.20532   0.20217  -0.1255   0.0069   1.0000
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