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GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 599 AIRFOIL (goe599-il)
Reynolds number: 200,000
Max Cl/Cd: 51.23 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe599-il-200000-n5.txt
Download as CSV file: xf-goe599-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 599 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6283   0.08198   0.07841  -0.0324   1.0000   0.0135
 -10.500  -0.6944   0.05868   0.05498  -0.0509   1.0000   0.0125
 -10.250  -0.7274   0.05167   0.04776  -0.0553   1.0000   0.0123
 -10.000  -0.7522   0.04738   0.04322  -0.0536   1.0000   0.0122
  -9.750  -0.7663   0.04348   0.03902  -0.0515   1.0000   0.0123
  -9.500  -0.7730   0.03994   0.03515  -0.0492   1.0000   0.0125
  -9.250  -0.7735   0.03678   0.03163  -0.0470   1.0000   0.0127
  -9.000  -0.7691   0.03393   0.02842  -0.0448   1.0000   0.0130
  -8.750  -0.7609   0.03137   0.02550  -0.0427   1.0000   0.0135
  -8.500  -0.7490   0.02924   0.02298  -0.0409   1.0000   0.0141
  -8.250  -0.7339   0.02759   0.02101  -0.0392   1.0000   0.0150
  -8.000  -0.7189   0.02567   0.01880  -0.0376   1.0000   0.0158
  -7.750  -0.7024   0.02415   0.01714  -0.0362   1.0000   0.0166
  -7.500  -0.6838   0.02304   0.01589  -0.0350   1.0000   0.0175
  -7.250  -0.6646   0.02198   0.01470  -0.0337   1.0000   0.0185
  -7.000  -0.6447   0.02101   0.01358  -0.0326   1.0000   0.0200
  -6.750  -0.6239   0.02024   0.01265  -0.0314   1.0000   0.0218
  -6.500  -0.6039   0.01918   0.01145  -0.0303   1.0000   0.0235
  -6.250  -0.5834   0.01832   0.01054  -0.0293   1.0000   0.0255
  -6.000  -0.5539   0.01764   0.00978  -0.0301   0.9982   0.0288
  -5.750  -0.5208   0.01695   0.00896  -0.0316   0.9956   0.0324
  -5.500  -0.4888   0.01611   0.00807  -0.0330   0.9927   0.0371
  -5.250  -0.4555   0.01562   0.00744  -0.0344   0.9894   0.0421
  -5.000  -0.4220   0.01492   0.00673  -0.0361   0.9866   0.0491
  -4.750  -0.3893   0.01442   0.00619  -0.0374   0.9830   0.0579
  -4.500  -0.3566   0.01391   0.00581  -0.0388   0.9791   0.0795
  -4.250  -0.3216   0.01354   0.00543  -0.0406   0.9761   0.1087
  -4.000  -0.2902   0.01313   0.00506  -0.0417   0.9714   0.1296
  -3.750  -0.2575   0.01262   0.00476  -0.0432   0.9672   0.1723
  -3.500  -0.2228   0.01214   0.00452  -0.0451   0.9642   0.2431
  -3.250  -0.1927   0.01179   0.00433  -0.0458   0.9583   0.2911
  -3.000  -0.1595   0.01145   0.00414  -0.0472   0.9539   0.3393
  -2.750  -0.1252   0.01104   0.00397  -0.0489   0.9507   0.4047
  -2.500  -0.0976   0.01071   0.00387  -0.0490   0.9431   0.4664
  -2.250  -0.0654   0.01045   0.00376  -0.0499   0.9380   0.5175
  -2.000  -0.0356   0.01024   0.00365  -0.0503   0.9313   0.5601
  -1.750  -0.0052   0.01006   0.00355  -0.0508   0.9244   0.5936
  -1.500   0.0249   0.00988   0.00345  -0.0511   0.9171   0.6237
  -1.250   0.0551   0.00967   0.00333  -0.0515   0.9084   0.6553
  -1.000   0.0844   0.00943   0.00320  -0.0514   0.8957   0.6913
  -0.750   0.1139   0.00919   0.00307  -0.0513   0.8821   0.7315
  -0.500   0.1429   0.00899   0.00298  -0.0511   0.8696   0.7725
  -0.250   0.1713   0.00885   0.00295  -0.0507   0.8593   0.8158
   0.000   0.2009   0.00876   0.00293  -0.0505   0.8497   0.8604
   0.250   0.2332   0.00872   0.00295  -0.0510   0.8392   0.9043
   0.500   0.2711   0.00872   0.00295  -0.0528   0.8285   0.9409
   0.750   0.3107   0.00873   0.00289  -0.0549   0.8088   0.9687
   1.000   0.3507   0.00878   0.00282  -0.0572   0.7790   0.9893
   1.250   0.3867   0.00886   0.00278  -0.0588   0.7477   1.0000
   1.500   0.4103   0.00894   0.00278  -0.0579   0.7205   1.0000
   1.750   0.4340   0.00904   0.00278  -0.0570   0.6926   1.0000
   2.000   0.4576   0.00918   0.00281  -0.0560   0.6613   1.0000
   2.250   0.4804   0.00938   0.00284  -0.0549   0.6198   1.0000
   2.500   0.5005   0.00977   0.00289  -0.0532   0.5506   1.0000
   2.750   0.5200   0.01028   0.00304  -0.0516   0.4755   1.0000
   3.000   0.5399   0.01083   0.00325  -0.0502   0.4080   1.0000
   3.250   0.5607   0.01138   0.00351  -0.0490   0.3450   1.0000
   3.500   0.5805   0.01209   0.00383  -0.0477   0.2567   1.0000
   3.750   0.5965   0.01335   0.00439  -0.0461   0.1197   1.0000
   4.000   0.6188   0.01393   0.00477  -0.0452   0.0830   1.0000
   4.250   0.6428   0.01433   0.00514  -0.0446   0.0755   1.0000
   4.500   0.6668   0.01472   0.00557  -0.0440   0.0715   1.0000
   4.750   0.6903   0.01517   0.00604  -0.0433   0.0683   1.0000
   5.000   0.7137   0.01563   0.00654  -0.0425   0.0659   1.0000
   5.250   0.7372   0.01606   0.00705  -0.0418   0.0638   1.0000
   5.500   0.7602   0.01655   0.00763  -0.0410   0.0622   1.0000
   5.750   0.7827   0.01709   0.00824  -0.0402   0.0607   1.0000
   6.000   0.8049   0.01769   0.00890  -0.0393   0.0592   1.0000
   6.250   0.8267   0.01835   0.00961  -0.0383   0.0578   1.0000
   6.500   0.8477   0.01912   0.01041  -0.0373   0.0557   1.0000
   6.750   0.8679   0.02008   0.01142  -0.0362   0.0522   1.0000
   7.000   0.8919   0.02038   0.01186  -0.0357   0.0487   1.0000
   7.250   0.9145   0.02089   0.01245  -0.0350   0.0452   1.0000
   7.500   0.9352   0.02162   0.01318  -0.0341   0.0418   1.0000
   7.750   0.9578   0.02212   0.01384  -0.0334   0.0384   1.0000
   8.000   0.9809   0.02242   0.01429  -0.0327   0.0341   1.0000
   8.250   1.0034   0.02279   0.01475  -0.0320   0.0299   1.0000
   8.500   1.0259   0.02318   0.01522  -0.0313   0.0256   1.0000
   8.750   1.0458   0.02394   0.01606  -0.0302   0.0225   1.0000
   9.000   1.0660   0.02460   0.01679  -0.0292   0.0197   1.0000
   9.250   1.0840   0.02549   0.01768  -0.0279   0.0175   1.0000
   9.500   1.1003   0.02673   0.01911  -0.0264   0.0162   1.0000
   9.750   1.1159   0.02804   0.02059  -0.0247   0.0152   1.0000
  10.000   1.1306   0.02938   0.02210  -0.0230   0.0143   1.0000
  10.250   1.1440   0.03074   0.02365  -0.0213   0.0135   1.0000
  10.500   1.1540   0.03224   0.02529  -0.0191   0.0128   1.0000
  10.750   1.1580   0.03440   0.02764  -0.0163   0.0121   1.0000
  11.000   1.1657   0.03616   0.02968  -0.0140   0.0116   1.0000
  11.250   1.1701   0.03823   0.03203  -0.0116   0.0112   1.0000
  11.500   1.1707   0.04062   0.03470  -0.0090   0.0108   1.0000
  11.750   1.1679   0.04330   0.03766  -0.0065   0.0106   1.0000
  12.000   1.1619   0.04631   0.04096  -0.0043   0.0104   1.0000
  12.250   1.1526   0.04973   0.04466  -0.0026   0.0102   1.0000
  12.500   1.1400   0.05368   0.04889  -0.0016   0.0101   1.0000
  12.750   1.1241   0.05833   0.05382  -0.0015   0.0101   1.0000
  13.000   1.1047   0.06389   0.05964  -0.0026   0.0100   1.0000
  13.250   1.0817   0.07063   0.06664  -0.0053   0.0101   1.0000
  13.500   1.0544   0.07913   0.07540  -0.0100   0.0102   1.0000
  13.750   1.0208   0.09040   0.08690  -0.0174   0.0104   1.0000
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