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GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 595 AIRFOIL (goe595-il)
Reynolds number: 50,000
Max Cl/Cd: 38.07 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe595-il-50000-n5.txt
Download as CSV file: xf-goe595-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 595 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3888   0.10868   0.10176  -0.0339   1.0000   0.1070
  -9.000  -0.4056   0.10702   0.10026  -0.0361   1.0000   0.1107
  -8.500  -0.4133   0.09488   0.08822  -0.0403   1.0000   0.0560
  -8.250  -0.4146   0.09189   0.08531  -0.0392   1.0000   0.0552
  -8.000  -0.4218   0.08900   0.08252  -0.0384   1.0000   0.0546
  -7.750  -0.4295   0.08610   0.07972  -0.0378   1.0000   0.0537
  -7.500  -0.4366   0.08280   0.07650  -0.0378   1.0000   0.0528
  -7.250  -0.4440   0.07928   0.07304  -0.0379   1.0000   0.0519
  -7.000  -0.4504   0.07567   0.06945  -0.0380   1.0000   0.0508
  -6.750  -0.4562   0.07163   0.06541  -0.0383   1.0000   0.0496
  -6.500  -0.4606   0.06707   0.06076  -0.0389   1.0000   0.0482
  -6.250  -0.4653   0.06067   0.05385  -0.0408   1.0000   0.0454
  -6.000  -0.4601   0.05720   0.05025  -0.0399   1.0000   0.0450
  -5.750  -0.4536   0.05346   0.04627  -0.0391   1.0000   0.0448
  -5.500  -0.4445   0.04982   0.04234  -0.0384   1.0000   0.0446
  -5.250  -0.4330   0.04624   0.03838  -0.0376   1.0000   0.0446
  -5.000  -0.4187   0.04273   0.03423  -0.0368   1.0000   0.0453
  -4.750  -0.4042   0.04026   0.03165  -0.0360   1.0000   0.0473
  -4.500  -0.3871   0.03808   0.02918  -0.0351   1.0000   0.0496
  -4.250  -0.3675   0.03551   0.02612  -0.0342   1.0000   0.0509
  -4.000  -0.3460   0.03321   0.02332  -0.0333   1.0000   0.0523
  -3.750  -0.3235   0.03134   0.02090  -0.0323   1.0000   0.0557
  -3.500  -0.3024   0.02991   0.01929  -0.0314   1.0000   0.0601
  -3.250  -0.2801   0.02858   0.01766  -0.0303   1.0000   0.0638
  -3.000  -0.2549   0.02749   0.01619  -0.0296   0.9991   0.0693
  -2.750  -0.2204   0.02649   0.01510  -0.0311   0.9942   0.0803
  -2.500  -0.1856   0.02555   0.01399  -0.0325   0.9890   0.0902
  -2.250  -0.1504   0.02482   0.01319  -0.0342   0.9832   0.1149
  -2.000  -0.1129   0.02378   0.01245  -0.0365   0.9773   0.1852
  -1.750  -0.0805   0.02231   0.01217  -0.0383   0.9695   0.4208
  -1.500  -0.0144   0.02096   0.01208  -0.0441   0.9656   1.0000
  -1.250   0.0253   0.02117   0.01182  -0.0468   0.9546   1.0000
  -1.000   0.0615   0.02135   0.01161  -0.0487   0.9436   1.0000
  -0.750   0.0973   0.02155   0.01150  -0.0506   0.9337   1.0000
  -0.500   0.1366   0.02176   0.01144  -0.0531   0.9254   1.0000
  -0.250   0.1673   0.02193   0.01138  -0.0540   0.9145   1.0000
   0.000   0.1999   0.02211   0.01137  -0.0552   0.9043   1.0000
   0.250   0.2403   0.02225   0.01133  -0.0577   0.8962   1.0000
   0.500   0.2695   0.02239   0.01136  -0.0582   0.8843   1.0000
   0.750   0.3000   0.02253   0.01140  -0.0588   0.8729   1.0000
   1.000   0.3327   0.02263   0.01142  -0.0598   0.8617   1.0000
   1.250   0.3698   0.02266   0.01138  -0.0615   0.8520   1.0000
   1.500   0.4025   0.02269   0.01139  -0.0623   0.8404   1.0000
   1.750   0.4323   0.02274   0.01143  -0.0625   0.8274   1.0000
   2.250   0.4921   0.02279   0.01150  -0.0629   0.8008   1.0000
   2.500   0.5222   0.02279   0.01155  -0.0630   0.7871   1.0000
   2.750   0.5533   0.02270   0.01150  -0.0632   0.7723   1.0000
   3.000   0.5862   0.02246   0.01133  -0.0633   0.7558   1.0000
   3.250   0.6178   0.02217   0.01107  -0.0631   0.7363   1.0000
   3.500   0.6461   0.02198   0.01093  -0.0623   0.7144   1.0000
   3.750   0.6782   0.02177   0.01077  -0.0622   0.6943   1.0000
   4.000   0.7035   0.02187   0.01094  -0.0613   0.6729   1.0000
   4.250   0.7326   0.02190   0.01102  -0.0610   0.6530   1.0000
   4.500   0.7587   0.02205   0.01128  -0.0602   0.6318   1.0000
   4.750   0.7855   0.02222   0.01151  -0.0596   0.6107   1.0000
   5.000   0.8115   0.02245   0.01180  -0.0589   0.5895   1.0000
   5.250   0.8366   0.02275   0.01217  -0.0580   0.5682   1.0000
   5.500   0.8623   0.02309   0.01259  -0.0573   0.5475   1.0000
   5.750   0.8858   0.02353   0.01314  -0.0563   0.5265   1.0000
   6.000   0.9109   0.02399   0.01366  -0.0555   0.5064   1.0000
   6.250   0.9338   0.02455   0.01436  -0.0545   0.4862   1.0000
   6.500   0.9559   0.02511   0.01504  -0.0532   0.4636   1.0000
   6.750   0.9722   0.02566   0.01563  -0.0510   0.4352   1.0000
   7.000   0.9851   0.02621   0.01617  -0.0483   0.4042   1.0000
   7.250   0.9982   0.02682   0.01689  -0.0458   0.3767   1.0000
   7.500   1.0120   0.02745   0.01770  -0.0434   0.3517   1.0000
   7.750   1.0212   0.02810   0.01844  -0.0404   0.3199   1.0000
   8.000   1.0237   0.02893   0.01917  -0.0366   0.2756   1.0000
   8.250   1.0246   0.03014   0.02014  -0.0327   0.2292   1.0000
   8.500   1.0258   0.03169   0.02156  -0.0292   0.1701   1.0000
   8.750   1.0221   0.03395   0.02329  -0.0258   0.1121   1.0000
   9.250   1.0193   0.03875   0.02772  -0.0203   0.0790   1.0000
   9.500   1.0204   0.04101   0.03004  -0.0180   0.0705   1.0000
   9.750   1.0187   0.04357   0.03261  -0.0157   0.0648   1.0000
  10.000   1.0228   0.04584   0.03510  -0.0138   0.0597   1.0000
  10.250   1.0248   0.04837   0.03768  -0.0121   0.0548   1.0000
  10.500   1.0341   0.05078   0.04022  -0.0104   0.0508   1.0000
  10.750   1.0498   0.05299   0.04273  -0.0089   0.0471   1.0000
  11.000   1.0617   0.05547   0.04543  -0.0077   0.0433   1.0000
  11.250   1.0816   0.05854   0.04856  -0.0069   0.0400   1.0000
  11.500   1.0896   0.06160   0.05204  -0.0056   0.0389   1.0000
  11.750   1.0910   0.06499   0.05581  -0.0045   0.0379   1.0000
  12.000   1.0867   0.06863   0.05978  -0.0036   0.0370   1.0000
  12.250   1.0784   0.07254   0.06400  -0.0031   0.0362   1.0000
  12.500   1.0680   0.07678   0.06852  -0.0032   0.0357   1.0000
  12.750   1.0549   0.08148   0.07348  -0.0039   0.0354   1.0000
  13.000   1.0391   0.08675   0.07899  -0.0055   0.0350   1.0000
  13.250   1.0215   0.09267   0.08513  -0.0079   0.0350   1.0000
  13.500   1.0023   0.09939   0.09207  -0.0112   0.0355   1.0000
  13.750   0.9818   0.10700   0.09985  -0.0156   0.0361   1.0000
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