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GOE 598 AIRFOIL (goe598-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 598 AIRFOIL (goe598-il)
Reynolds number: 500,000
Max Cl/Cd: 54.61 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe598-il-500000-n5.txt
Download as CSV file: xf-goe598-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6455   0.08721   0.08513   0.0054   1.0000   0.0035
  -8.500  -0.6486   0.08176   0.07970   0.0015   1.0000   0.0035
  -8.250  -0.6521   0.07575   0.07373  -0.0046   1.0000   0.0035
  -8.000  -0.6500   0.06766   0.06560  -0.0141   1.0000   0.0034
  -7.750  -0.6466   0.05936   0.05719  -0.0211   1.0000   0.0034
  -7.500  -0.6420   0.05063   0.04825  -0.0259   1.0000   0.0034
  -7.250  -0.6371   0.04063   0.03785  -0.0284   1.0000   0.0034
  -7.000  -0.6362   0.02701   0.02327  -0.0283   1.0000   0.0035
  -6.750  -0.6180   0.02257   0.01815  -0.0275   1.0000   0.0038
  -6.500  -0.5981   0.01930   0.01438  -0.0269   1.0000   0.0042
  -6.250  -0.5751   0.01741   0.01217  -0.0263   1.0000   0.0043
  -6.000  -0.5512   0.01595   0.01047  -0.0258   1.0000   0.0046
  -5.750  -0.5269   0.01472   0.00903  -0.0252   1.0000   0.0049
  -5.500  -0.5024   0.01363   0.00776  -0.0247   1.0000   0.0053
  -5.250  -0.4778   0.01270   0.00664  -0.0241   1.0000   0.0059
  -5.000  -0.4530   0.01199   0.00580  -0.0235   1.0000   0.0063
  -4.750  -0.4285   0.01130   0.00505  -0.0231   1.0000   0.0080
  -4.500  -0.4036   0.01079   0.00447  -0.0225   1.0000   0.0094
  -4.250  -0.3788   0.01023   0.00381  -0.0219   1.0000   0.0112
  -4.000  -0.3537   0.00987   0.00344  -0.0214   1.0000   0.0170
  -3.750  -0.3230   0.00957   0.00310  -0.0222   0.9975   0.0221
  -3.500  -0.2897   0.00932   0.00280  -0.0236   0.9940   0.0282
  -3.250  -0.2569   0.00906   0.00248  -0.0248   0.9893   0.0325
  -3.000  -0.2243   0.00874   0.00210  -0.0260   0.9838   0.0379
  -2.750  -0.1911   0.00853   0.00187  -0.0272   0.9777   0.0438
  -2.500  -0.1595   0.00828   0.00172  -0.0282   0.9696   0.0687
  -2.250  -0.1279   0.00818   0.00157  -0.0290   0.9606   0.0770
  -2.000  -0.0972   0.00803   0.00144  -0.0297   0.9498   0.0858
  -1.750  -0.0678   0.00790   0.00132  -0.0300   0.9361   0.0958
  -1.500  -0.0398   0.00779   0.00121  -0.0300   0.9184   0.1039
  -1.250  -0.0131   0.00763   0.00109  -0.0296   0.8958   0.1288
  -1.000   0.0122   0.00731   0.00098  -0.0292   0.8694   0.2173
  -0.500   0.0632   0.00668   0.00082  -0.0284   0.8213   0.4185
  -0.250   0.0892   0.00643   0.00082  -0.0282   0.8024   0.5138
   0.000   0.1153   0.00623   0.00082  -0.0279   0.7818   0.5942
   0.250   0.1403   0.00600   0.00084  -0.0272   0.7546   0.6885
   0.500   0.1615   0.00561   0.00090  -0.0255   0.7282   0.8317
   0.750   0.1852   0.00546   0.00095  -0.0240   0.7069   0.9403
   1.000   0.2241   0.00552   0.00097  -0.0264   0.6831   0.9878
   1.250   0.2555   0.00567   0.00100  -0.0272   0.6507   1.0000
   1.500   0.2820   0.00582   0.00104  -0.0270   0.6238   1.0000
   1.750   0.3088   0.00595   0.00111  -0.0268   0.6005   1.0000
   2.000   0.3353   0.00614   0.00120  -0.0265   0.5599   1.0000
   2.250   0.3602   0.00661   0.00129  -0.0261   0.4517   1.0000
   2.500   0.3836   0.00756   0.00158  -0.0258   0.2907   1.0000
   2.750   0.4079   0.00839   0.00186  -0.0257   0.1541   1.0000
   3.000   0.4331   0.00903   0.00216  -0.0255   0.0662   1.0000
   3.250   0.4589   0.00956   0.00250  -0.0253   0.0218   1.0000
   3.500   0.4855   0.00991   0.00287  -0.0251   0.0131   1.0000
   3.750   0.5121   0.01029   0.00334  -0.0248   0.0104   1.0000
   4.000   0.5374   0.01109   0.00426  -0.0243   0.0079   1.0000
   4.250   0.5638   0.01147   0.00470  -0.0240   0.0070   1.0000
   4.500   0.5892   0.01212   0.00544  -0.0236   0.0063   1.0000
   4.750   0.6143   0.01287   0.00626  -0.0231   0.0057   1.0000
   5.000   0.6390   0.01374   0.00723  -0.0226   0.0053   1.0000
   5.250   0.6630   0.01485   0.00844  -0.0219   0.0050   1.0000
   5.500   0.6859   0.01653   0.01028  -0.0211   0.0046   1.0000
   5.750   0.7116   0.01725   0.01117  -0.0206   0.0040   1.0000
   6.000   0.7356   0.01892   0.01308  -0.0198   0.0037   1.0000
   6.250   0.7588   0.02091   0.01538  -0.0188   0.0034   1.0000
   6.500   0.7811   0.02312   0.01791  -0.0178   0.0032   1.0000
   6.750   0.8014   0.02587   0.02103  -0.0167   0.0031   1.0000
   7.000   0.8183   0.02978   0.02545  -0.0151   0.0031   1.0000
   7.250   0.8274   0.03707   0.03340  -0.0124   0.0032   1.0000
   7.500   0.8341   0.04365   0.04045  -0.0105   0.0035   1.0000
   7.750   0.8389   0.04974   0.04688  -0.0094   0.0037   1.0000
   8.000   0.8409   0.05552   0.05293  -0.0090   0.0038   1.0000
   8.250   0.8397   0.06111   0.05872  -0.0092   0.0040   1.0000
   8.500   0.8347   0.06669   0.06447  -0.0103   0.0041   1.0000
   8.750   0.8245   0.07219   0.07009  -0.0120   0.0042   1.0000
   9.000   0.8109   0.07866   0.07664  -0.0169   0.0042   1.0000
   9.250   0.8019   0.08759   0.08554  -0.0264   0.0042   1.0000
   9.500   0.7962   0.09431   0.09224  -0.0314   0.0043   1.0000
   9.750   0.7916   0.10021   0.09812  -0.0350   0.0044   1.0000
  10.000   0.7868   0.10573   0.10362  -0.0380   0.0045   1.0000
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