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GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 598 AIRFOIL (goe598-il)
Reynolds number: 200,000
Max Cl/Cd: 54.82 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe598-il-200000.txt
Download as CSV file: xf-goe598-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 598 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6151   0.09069   0.08736  -0.0092   1.0000   0.0360
  -8.250  -0.6129   0.08462   0.08124  -0.0161   1.0000   0.0361
  -8.000  -0.6198   0.07835   0.07506  -0.0154   1.0000   0.0374
  -7.750  -0.6131   0.07557   0.07228  -0.0146   1.0000   0.0387
  -7.500  -0.6059   0.07133   0.06801  -0.0173   1.0000   0.0402
  -7.250  -0.5977   0.06634   0.06294  -0.0212   1.0000   0.0420
  -7.000  -0.5879   0.06065   0.05710  -0.0256   1.0000   0.0446
  -5.750  -0.5148   0.04049   0.03587  -0.0320   1.0000   0.0758
  -5.500  -0.4950   0.03774   0.03256  -0.0321   1.0000   0.0870
  -5.250  -0.4681   0.02523   0.01862  -0.0296   1.0000   0.0374
  -5.000  -0.4424   0.02340   0.01645  -0.0286   1.0000   0.0358
  -4.750  -0.4184   0.02069   0.01330  -0.0277   1.0000   0.0364
  -4.500  -0.3951   0.01779   0.01016  -0.0271   1.0000   0.0400
  -4.250  -0.3702   0.01616   0.00836  -0.0261   1.0000   0.0418
  -4.000  -0.3455   0.01487   0.00696  -0.0252   1.0000   0.0449
  -3.750  -0.3216   0.01377   0.00579  -0.0245   1.0000   0.0508
  -3.500  -0.2970   0.01308   0.00509  -0.0237   1.0000   0.0566
  -3.250  -0.2725   0.01243   0.00446  -0.0231   1.0000   0.0647
  -3.000  -0.2477   0.01189   0.00394  -0.0225   1.0000   0.0790
  -2.750  -0.2229   0.01107   0.00325  -0.0221   1.0000   0.1170
  -2.500  -0.1988   0.01006   0.00285  -0.0220   1.0000   0.2581
  -2.250  -0.1762   0.00887   0.00273  -0.0217   1.0000   0.5230
  -2.000  -0.1534   0.00835   0.00268  -0.0206   1.0000   0.6513
  -1.750  -0.1324   0.00794   0.00269  -0.0188   1.0000   0.7651
  -1.500  -0.1105   0.00770   0.00274  -0.0165   1.0000   0.8980
  -1.250  -0.0643   0.00765   0.00265  -0.0203   1.0000   1.0000
  -1.000  -0.0427   0.00773   0.00263  -0.0195   1.0000   1.0000
  -0.750  -0.0209   0.00784   0.00267  -0.0188   1.0000   1.0000
  -0.500   0.0009   0.00801   0.00277  -0.0183   1.0000   1.0000
  -0.250   0.0352   0.00816   0.00285  -0.0203   0.9961   1.0000
   0.000   0.0804   0.00824   0.00289  -0.0244   0.9877   1.0000
   0.250   0.1274   0.00829   0.00292  -0.0287   0.9791   1.0000
   0.500   0.1760   0.00827   0.00292  -0.0332   0.9702   1.0000
   0.750   0.2191   0.00823   0.00291  -0.0364   0.9583   1.0000
   1.000   0.2598   0.00814   0.00285  -0.0388   0.9431   1.0000
   1.250   0.2922   0.00805   0.00278  -0.0393   0.9210   1.0000
   1.500   0.3206   0.00799   0.00275  -0.0388   0.8997   1.0000
   1.750   0.3461   0.00801   0.00278  -0.0378   0.8781   1.0000
   2.000   0.3710   0.00805   0.00282  -0.0366   0.8571   1.0000
   2.250   0.3946   0.00812   0.00286  -0.0351   0.8313   1.0000
   2.500   0.4180   0.00823   0.00297  -0.0336   0.8004   1.0000
   2.750   0.4418   0.00836   0.00306  -0.0321   0.7667   1.0000
   3.000   0.4640   0.00853   0.00309  -0.0302   0.7104   1.0000
   3.250   0.4857   0.00886   0.00313  -0.0283   0.6265   1.0000
   3.500   0.5002   0.01036   0.00331  -0.0258   0.3303   1.0000
   3.750   0.5155   0.01321   0.00470  -0.0245   0.0516   1.0000
   4.000   0.5384   0.01453   0.00606  -0.0235   0.0408   1.0000
   4.250   0.5636   0.01528   0.00689  -0.0228   0.0359   1.0000
   4.500   0.5876   0.01646   0.00810  -0.0220   0.0331   1.0000
   4.750   0.6119   0.01793   0.00960  -0.0211   0.0317   1.0000
   5.000   0.6373   0.01971   0.01147  -0.0202   0.0312   1.0000
   5.250   0.6614   0.02290   0.01489  -0.0194   0.0288   1.0000
   5.500   0.6869   0.02482   0.01713  -0.0185   0.0284   1.0000
   5.750   0.7122   0.02743   0.01998  -0.0176   0.0298   1.0000
   6.000   0.7474   0.03628   0.03059  -0.0123   0.0837   1.0000
   6.250   0.7649   0.03903   0.03361  -0.0116   0.0729   1.0000
   6.500   0.7842   0.04196   0.03657  -0.0111   0.0688   1.0000
   6.750   0.7964   0.04552   0.04067  -0.0100   0.0601   1.0000
   7.000   0.8121   0.04859   0.04384  -0.0095   0.0567   1.0000
   9.500   0.6618   0.09353   0.09038  -0.0193   0.0483   1.0000
   9.750   0.6542   0.09892   0.09576  -0.0214   0.0473   1.0000
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