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GOE 590 AIRFOIL (goe590-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 590 AIRFOIL (goe590-il)
Reynolds number: 200,000
Max Cl/Cd: 70.1 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe590-il-200000-n5.txt
Download as CSV file: xf-goe590-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 590 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3911   0.09790   0.09455  -0.0134   1.0000   0.0170
  -7.750  -0.3887   0.09545   0.09216  -0.0152   1.0000   0.0171
  -7.500  -0.3871   0.09293   0.08968  -0.0169   1.0000   0.0172
  -7.250  -0.3810   0.08998   0.08677  -0.0197   1.0000   0.0173
  -7.000  -0.3725   0.08685   0.08365  -0.0222   1.0000   0.0173
  -6.750  -0.3626   0.08357   0.08038  -0.0244   1.0000   0.0174
  -6.500  -0.3516   0.08018   0.07699  -0.0265   1.0000   0.0174
  -6.250  -0.3398   0.07675   0.07356  -0.0283   1.0000   0.0175
  -6.000  -0.3276   0.07339   0.07020  -0.0298   1.0000   0.0175
  -5.750  -0.3150   0.06992   0.06668  -0.0310   1.0000   0.0175
  -5.500  -0.2931   0.06568   0.06239  -0.0343   0.9904   0.0175
  -5.250  -0.2606   0.06107   0.05766  -0.0396   0.9653   0.0176
  -4.750  -0.2049   0.05028   0.04663  -0.0482   0.9125   0.0165
  -4.500  -0.1776   0.04589   0.04205  -0.0512   0.8848   0.0146
  -4.250  -0.1502   0.04202   0.03792  -0.0531   0.8564   0.0135
  -4.000  -0.1244   0.03832   0.03394  -0.0539   0.8296   0.0129
  -3.750  -0.0996   0.03478   0.03006  -0.0540   0.8053   0.0125
  -3.500  -0.0751   0.03134   0.02627  -0.0537   0.7847   0.0124
  -3.250  -0.0504   0.02803   0.02253  -0.0529   0.7668   0.0127
  -3.000  -0.0254   0.02493   0.01900  -0.0519   0.7510   0.0144
  -2.750  -0.0001   0.02098   0.01444  -0.0505   0.7372   0.0156
  -2.500   0.0256   0.01739   0.01007  -0.0490   0.7240   0.0168
  -2.250   0.0511   0.01591   0.00819  -0.0483   0.7101   0.0196
  -2.000   0.0773   0.01505   0.00700  -0.0476   0.6964   0.0245
  -1.750   0.1035   0.01415   0.00578  -0.0470   0.6831   0.0304
  -1.500   0.1294   0.01364   0.00506  -0.0466   0.6694   0.0363
  -1.250   0.1549   0.01304   0.00432  -0.0460   0.6556   0.0420
  -1.000   0.1803   0.01262   0.00377  -0.0455   0.6421   0.0455
  -0.750   0.2057   0.01231   0.00331  -0.0449   0.6294   0.0481
  -0.500   0.2309   0.01204   0.00294  -0.0444   0.6173   0.0524
  -0.250   0.2561   0.01182   0.00262  -0.0439   0.6057   0.0543
   0.000   0.2816   0.01166   0.00237  -0.0434   0.5945   0.0568
   0.250   0.3073   0.01155   0.00215  -0.0429   0.5847   0.0616
   0.500   0.3327   0.01144   0.00201  -0.0424   0.5764   0.0783
   0.750   0.3578   0.01129   0.00197  -0.0420   0.5683   0.1291
   1.000   0.3820   0.01108   0.00195  -0.0414   0.5613   0.2258
   1.500   0.4946   0.00959   0.00205  -0.0542   0.5455   1.0000
   1.750   0.5194   0.00971   0.00212  -0.0536   0.5397   1.0000
   2.000   0.5442   0.00986   0.00219  -0.0530   0.5347   1.0000
   2.250   0.5692   0.00998   0.00231  -0.0525   0.5292   1.0000
   2.500   0.5940   0.01012   0.00243  -0.0520   0.5239   1.0000
   2.750   0.6189   0.01029   0.00260  -0.0515   0.5196   1.0000
   3.000   0.6440   0.01043   0.00279  -0.0510   0.5148   1.0000
   3.250   0.6690   0.01058   0.00300  -0.0505   0.5102   1.0000
   3.500   0.6937   0.01076   0.00320  -0.0500   0.5038   1.0000
   3.750   0.7182   0.01090   0.00344  -0.0493   0.4941   1.0000
   4.000   0.7427   0.01104   0.00367  -0.0487   0.4838   1.0000
   4.250   0.7670   0.01120   0.00391  -0.0480   0.4739   1.0000
   4.500   0.7899   0.01131   0.00406  -0.0470   0.4486   1.0000
   4.750   0.8097   0.01155   0.00414  -0.0455   0.3665   1.0000
   5.000   0.8095   0.01461   0.00554  -0.0421   0.0463   1.0000
   5.250   0.8282   0.01555   0.00648  -0.0405   0.0232   1.0000
   5.500   0.8465   0.01651   0.00759  -0.0389   0.0176   1.0000
   5.750   0.8656   0.01731   0.00856  -0.0375   0.0138   1.0000
   6.000   0.8819   0.01841   0.00981  -0.0356   0.0123   1.0000
   6.250   0.8959   0.01977   0.01132  -0.0334   0.0112   1.0000
   6.500   0.9046   0.02196   0.01359  -0.0305   0.0096   1.0000
   6.750   0.9232   0.02302   0.01479  -0.0290   0.0087   1.0000
   7.000   0.9408   0.02474   0.01663  -0.0273   0.0083   1.0000
   7.250   0.9606   0.02687   0.01894  -0.0257   0.0079   1.0000
   7.500   0.9815   0.02924   0.02154  -0.0243   0.0077   1.0000
   7.750   1.0016   0.03200   0.02461  -0.0228   0.0076   1.0000
   8.000   1.0193   0.03518   0.02815  -0.0211   0.0077   1.0000
   8.250   1.0338   0.03846   0.03179  -0.0191   0.0077   1.0000
   8.500   1.0449   0.03918   0.03262  -0.0181   0.0062   1.0000
   9.000   1.0547   0.04626   0.04041  -0.0135   0.0056   1.0000
   9.250   1.0555   0.04975   0.04418  -0.0113   0.0057   1.0000
   9.500   1.0527   0.05325   0.04797  -0.0089   0.0057   1.0000
   9.750   1.0450   0.05666   0.05163  -0.0061   0.0057   1.0000
  10.000   1.0357   0.05954   0.05469  -0.0036   0.0058   1.0000
  10.250   1.0266   0.06233   0.05767  -0.0017   0.0059   1.0000
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