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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 200,000
Max Cl/Cd: 85.65 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe450-il-200000-n5.txt
Download as CSV file: xf-goe450-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3050   0.11473   0.11109  -0.0376   1.0000   0.0241
  -9.750  -0.3069   0.11264   0.10904  -0.0369   1.0000   0.0254
  -9.500  -0.3163   0.11115   0.10762  -0.0366   1.0000   0.0266
  -9.250  -0.3113   0.10776   0.10424  -0.0417   0.9966   0.0269
  -9.000  -0.2996   0.10353   0.10002  -0.0467   0.9928   0.0270
  -8.750  -0.2871   0.09927   0.09575  -0.0511   0.9885   0.0271
  -8.500  -0.2735   0.09488   0.09136  -0.0560   0.9844   0.0271
  -8.250  -0.2612   0.09058   0.08706  -0.0606   0.9782   0.0271
  -8.000  -0.2454   0.08696   0.08343  -0.0592   0.9773   0.0279
  -7.750  -0.2258   0.08419   0.08065  -0.0613   0.9749   0.0296
  -7.500  -0.2116   0.08086   0.07733  -0.0659   0.9671   0.0325
  -7.250  -0.1848   0.07499   0.07140  -0.0818   0.9574   0.0343
  -7.000  -0.1608   0.06986   0.06620  -0.0896   0.9516   0.0344
  -6.500  -0.1276   0.06102   0.05730  -0.0962   0.9397   0.0354
  -6.250  -0.1093   0.05960   0.05589  -0.0956   0.9359   0.0374
  -6.000  -0.0862   0.05635   0.05256  -0.0998   0.9294   0.0404
  -5.750  -0.0501   0.04708   0.04296  -0.1117   0.9215   0.0337
  -5.500  -0.0211   0.04169   0.03730  -0.1167   0.9157   0.0339
  -5.000   0.0335   0.03274   0.02769  -0.1226   0.9039   0.0340
  -4.750   0.0580   0.02929   0.02388  -0.1238   0.8965   0.0340
  -4.500   0.0852   0.02588   0.02000  -0.1252   0.8907   0.0353
  -4.250   0.1122   0.02376   0.01758  -0.1259   0.8849   0.0358
  -4.000   0.1391   0.02176   0.01521  -0.1261   0.8779   0.0358
  -3.750   0.1686   0.02013   0.01325  -0.1267   0.8730   0.0360
  -3.500   0.1945   0.01892   0.01179  -0.1265   0.8645   0.0363
  -3.250   0.2235   0.01792   0.01057  -0.1267   0.8588   0.0371
  -3.000   0.2500   0.01721   0.00973  -0.1265   0.8501   0.0383
  -2.750   0.2791   0.01633   0.00863  -0.1266   0.8437   0.0389
  -2.500   0.3059   0.01557   0.00772  -0.1263   0.8343   0.0390
  -2.250   0.3342   0.01489   0.00689  -0.1262   0.8264   0.0394
  -2.000   0.3617   0.01431   0.00620  -0.1260   0.8168   0.0398
  -1.750   0.3890   0.01381   0.00563  -0.1257   0.8069   0.0404
  -1.500   0.4168   0.01337   0.00511  -0.1256   0.7974   0.0410
  -1.250   0.4440   0.01301   0.00469  -0.1253   0.7865   0.0417
  -1.000   0.4712   0.01276   0.00438  -0.1251   0.7756   0.0432
  -0.750   0.4987   0.01247   0.00405  -0.1249   0.7648   0.0447
  -0.500   0.5262   0.01223   0.00374  -0.1247   0.7539   0.0460
  -0.250   0.5533   0.01207   0.00353  -0.1245   0.7423   0.0474
   0.000   0.5806   0.01197   0.00337  -0.1243   0.7314   0.0494
   0.250   0.6080   0.01190   0.00323  -0.1241   0.7210   0.0525
   0.500   0.6352   0.01183   0.00316  -0.1239   0.7103   0.0597
   0.750   0.6623   0.01170   0.00314  -0.1237   0.7002   0.1072
   1.000   0.6873   0.01089   0.00332  -0.1237   0.6907   0.4783
   1.500   0.7403   0.01000   0.00334  -0.1226   0.6710   1.0000
   2.000   0.7938   0.01029   0.00345  -0.1221   0.6519   1.0000
   2.250   0.8204   0.01045   0.00353  -0.1218   0.6421   1.0000
   2.500   0.8467   0.01063   0.00362  -0.1214   0.6313   1.0000
   2.750   0.8728   0.01079   0.00374  -0.1211   0.6198   1.0000
   3.000   0.8989   0.01096   0.00387  -0.1207   0.6087   1.0000
   3.250   0.9247   0.01115   0.00401  -0.1203   0.5966   1.0000
   3.500   0.9501   0.01135   0.00415  -0.1198   0.5831   1.0000
   3.750   0.9752   0.01156   0.00431  -0.1192   0.5684   1.0000
   4.000   0.9999   0.01177   0.00450  -0.1187   0.5522   1.0000
   4.250   1.0243   0.01199   0.00468  -0.1180   0.5338   1.0000
   4.500   1.0483   0.01224   0.00488  -0.1173   0.5144   1.0000
   4.750   1.0716   0.01253   0.00510  -0.1165   0.4941   1.0000
   5.000   1.0948   0.01284   0.00536  -0.1156   0.4730   1.0000
   5.250   1.1172   0.01319   0.00563  -0.1147   0.4510   1.0000
   5.500   1.1391   0.01358   0.00594  -0.1137   0.4294   1.0000
   5.750   1.1609   0.01398   0.00630  -0.1127   0.4079   1.0000
   6.000   1.1821   0.01442   0.00668  -0.1116   0.3871   1.0000
   6.250   1.2033   0.01486   0.00708  -0.1105   0.3655   1.0000
   6.500   1.2232   0.01537   0.00752  -0.1093   0.3418   1.0000
   6.750   1.2408   0.01601   0.00805  -0.1077   0.3079   1.0000
   7.000   1.2580   0.01668   0.00860  -0.1060   0.2713   1.0000
   7.250   1.2706   0.01767   0.00931  -0.1038   0.2157   1.0000
   7.750   1.2909   0.02001   0.01117  -0.0987   0.1294   1.0000
   8.000   1.2953   0.02139   0.01224  -0.0953   0.0839   1.0000
   8.250   1.3055   0.02241   0.01322  -0.0927   0.0653   1.0000
   8.750   1.3258   0.02450   0.01526  -0.0878   0.0445   1.0000
   9.000   1.3353   0.02563   0.01640  -0.0855   0.0406   1.0000
   9.250   1.3464   0.02665   0.01756  -0.0834   0.0381   1.0000
   9.500   1.3555   0.02784   0.01885  -0.0812   0.0357   1.0000
   9.750   1.3619   0.02926   0.02035  -0.0788   0.0336   1.0000
  10.000   1.3638   0.03106   0.02224  -0.0761   0.0316   1.0000
  10.250   1.3727   0.03238   0.02370  -0.0743   0.0302   1.0000
  10.500   1.3792   0.03393   0.02538  -0.0724   0.0287   1.0000
  10.750   1.3841   0.03566   0.02722  -0.0704   0.0273   1.0000
  11.000   1.3879   0.03756   0.02924  -0.0686   0.0259   1.0000
  11.250   1.3881   0.03984   0.03158  -0.0667   0.0247   1.0000
  11.500   1.3876   0.04227   0.03410  -0.0648   0.0236   1.0000
  11.750   1.3944   0.04408   0.03607  -0.0636   0.0226   1.0000
  12.000   1.3984   0.04619   0.03832  -0.0622   0.0216   1.0000
  12.250   1.4018   0.04842   0.04067  -0.0610   0.0206   1.0000
  12.500   1.4050   0.05070   0.04305  -0.0599   0.0197   1.0000
  12.750   1.4076   0.05308   0.04553  -0.0590   0.0189   1.0000
  13.000   1.4083   0.05571   0.04822  -0.0581   0.0183   1.0000
  13.250   1.4096   0.05835   0.05097  -0.0572   0.0176   1.0000
  13.500   1.4127   0.06086   0.05366  -0.0564   0.0168   1.0000
  13.750   1.4147   0.06354   0.05649  -0.0557   0.0162   1.0000
  14.000   1.4161   0.06633   0.05943  -0.0551   0.0157   1.0000
  14.250   1.4170   0.06924   0.06248  -0.0546   0.0152   1.0000
  14.500   1.4174   0.07227   0.06564  -0.0544   0.0147   1.0000
  14.750   1.4170   0.07543   0.06891  -0.0543   0.0144   1.0000
  15.000   1.4160   0.07875   0.07235  -0.0545   0.0140   1.0000
  15.250   1.4141   0.08223   0.07592  -0.0547   0.0137   1.0000
  15.500   1.4108   0.08597   0.07978  -0.0549   0.0133   1.0000
  15.750   1.4067   0.09000   0.08405  -0.0554   0.0130   1.0000
  16.000   1.4012   0.09438   0.08865  -0.0562   0.0126   1.0000
  16.250   1.3946   0.09902   0.09351  -0.0573   0.0123   1.0000
  16.500   1.3872   0.10392   0.09862  -0.0587   0.0120   1.0000
  16.750   1.3787   0.10914   0.10404  -0.0605   0.0118   1.0000
  17.000   1.3692   0.11467   0.10977  -0.0626   0.0116   1.0000
  17.250   1.3588   0.12056   0.11585  -0.0651   0.0115   1.0000
  17.500   1.3474   0.12688   0.12237  -0.0682   0.0114   1.0000
  17.750   1.3351   0.13362   0.12931  -0.0718   0.0113   1.0000
  18.000   1.3214   0.14096   0.13685  -0.0760   0.0112   1.0000
  18.250   1.3060   0.14905   0.14513  -0.0809   0.0112   1.0000
  18.500   1.2879   0.15829   0.15458  -0.0867   0.0112   1.0000
  18.750   1.2643   0.16984   0.16635  -0.0944   0.0113   1.0000
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