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GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 477 AIRFOIL (goe477-il)
Reynolds number: 500,000
Max Cl/Cd: 87.16 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe477-il-500000-n5.txt
Download as CSV file: xf-goe477-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 477 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2233   0.07926   0.07625  -0.0866   0.8409   0.0092
 -10.000  -0.3792   0.05348   0.05049  -0.0999   0.8299   0.0089
  -9.750  -0.4623   0.02745   0.02355  -0.1154   0.8236   0.0083
  -9.500  -0.4494   0.02443   0.02018  -0.1155   0.8216   0.0085
  -9.250  -0.4321   0.02238   0.01781  -0.1153   0.8195   0.0088
  -9.000  -0.4123   0.02082   0.01598  -0.1149   0.8174   0.0090
  -8.750  -0.3922   0.01941   0.01438  -0.1145   0.8155   0.0094
  -8.500  -0.3697   0.01842   0.01323  -0.1141   0.8138   0.0097
  -8.250  -0.3462   0.01756   0.01221  -0.1138   0.8121   0.0100
  -8.000  -0.3222   0.01676   0.01124  -0.1135   0.8103   0.0105
  -7.750  -0.2977   0.01603   0.01036  -0.1131   0.8086   0.0111
  -7.500  -0.2725   0.01541   0.00958  -0.1128   0.8066   0.0116
  -7.250  -0.2480   0.01467   0.00876  -0.1125   0.8045   0.0125
  -7.000  -0.2223   0.01415   0.00813  -0.1123   0.8025   0.0133
  -6.750  -0.1964   0.01364   0.00751  -0.1120   0.8007   0.0141
  -6.500  -0.1702   0.01318   0.00693  -0.1117   0.7990   0.0150
  -6.250  -0.1442   0.01268   0.00636  -0.1115   0.7973   0.0165
  -6.000  -0.1176   0.01231   0.00589  -0.1113   0.7957   0.0182
  -5.750  -0.0909   0.01193   0.00543  -0.1111   0.7942   0.0204
  -5.500  -0.0642   0.01158   0.00506  -0.1109   0.7926   0.0232
  -5.250  -0.0373   0.01130   0.00477  -0.1107   0.7908   0.0278
  -5.000  -0.0099   0.01114   0.00463  -0.1106   0.7888   0.0334
  -4.750   0.0177   0.01103   0.00453  -0.1105   0.7867   0.0386
  -4.500   0.0455   0.01099   0.00445  -0.1104   0.7842   0.0438
  -4.250   0.0734   0.01095   0.00433  -0.1103   0.7814   0.0472
  -4.000   0.1014   0.01096   0.00426  -0.1102   0.7786   0.0487
  -3.750   0.1278   0.01066   0.00396  -0.1100   0.7755   0.0518
  -3.500   0.1551   0.01051   0.00381  -0.1098   0.7721   0.0544
  -3.250   0.1825   0.01040   0.00366  -0.1097   0.7692   0.0570
  -3.000   0.2100   0.01027   0.00348  -0.1095   0.7665   0.0590
  -2.750   0.2373   0.01014   0.00329  -0.1093   0.7625   0.0603
  -2.500   0.2640   0.00995   0.00308  -0.1090   0.7566   0.0609
  -2.250   0.2909   0.00977   0.00284  -0.1087   0.7508   0.0613
  -2.000   0.3175   0.00957   0.00262  -0.1084   0.7440   0.0621
  -1.750   0.3442   0.00936   0.00239  -0.1080   0.7374   0.0637
  -1.500   0.3712   0.00921   0.00224  -0.1078   0.7321   0.0661
  -1.250   0.3982   0.00908   0.00211  -0.1076   0.7253   0.0683
  -1.000   0.4251   0.00897   0.00198  -0.1073   0.7181   0.0709
  -0.750   0.4520   0.00888   0.00187  -0.1070   0.7084   0.0737
  -0.500   0.4787   0.00877   0.00177  -0.1067   0.6978   0.0810
  -0.250   0.5050   0.00867   0.00168  -0.1063   0.6850   0.0936
   0.000   0.5307   0.00856   0.00162  -0.1059   0.6703   0.1258
   0.250   0.5558   0.00849   0.00159  -0.1053   0.6522   0.1670
   0.500   0.5800   0.00851   0.00158  -0.1046   0.6292   0.2003
   0.750   0.6033   0.00859   0.00161  -0.1037   0.6006   0.2337
   1.000   0.6250   0.00871   0.00170  -0.1025   0.5631   0.2856
   1.250   0.6438   0.00883   0.00186  -0.1009   0.5111   0.3901
   1.750   0.7139   0.00841   0.00243  -0.1049   0.4215   1.0000
   2.000   0.7356   0.00868   0.00257  -0.1037   0.4029   1.0000
   2.250   0.7578   0.00891   0.00271  -0.1026   0.3871   1.0000
   2.500   0.7803   0.00914   0.00285  -0.1016   0.3727   1.0000
   2.750   0.8029   0.00937   0.00300  -0.1006   0.3585   1.0000
   3.000   0.8253   0.00961   0.00315  -0.0996   0.3435   1.0000
   3.250   0.8476   0.00985   0.00331  -0.0986   0.3286   1.0000
   3.500   0.8700   0.01010   0.00348  -0.0976   0.3138   1.0000
   3.750   0.8925   0.01033   0.00365  -0.0967   0.3011   1.0000
   4.000   0.9150   0.01057   0.00384  -0.0957   0.2898   1.0000
   4.250   0.9371   0.01082   0.00403  -0.0947   0.2799   1.0000
   4.500   0.9596   0.01105   0.00424  -0.0938   0.2709   1.0000
   4.750   0.9817   0.01130   0.00445  -0.0928   0.2634   1.0000
   5.000   1.0039   0.01154   0.00467  -0.0918   0.2564   1.0000
   5.250   1.0255   0.01180   0.00492  -0.0908   0.2505   1.0000
   5.500   1.0477   0.01202   0.00515  -0.0898   0.2456   1.0000
   5.750   1.0688   0.01229   0.00541  -0.0887   0.2396   1.0000
   6.000   1.0895   0.01258   0.00568  -0.0875   0.2314   1.0000
   6.250   1.1089   0.01292   0.00597  -0.0861   0.2227   1.0000
   6.500   1.1290   0.01319   0.00625  -0.0848   0.2144   1.0000
   6.750   1.1464   0.01354   0.00656  -0.0831   0.2070   1.0000
   7.000   1.1658   0.01380   0.00685  -0.0816   0.2002   1.0000
   7.250   1.1827   0.01418   0.00720  -0.0799   0.1912   1.0000
   7.500   1.2008   0.01453   0.00753  -0.0783   0.1790   1.0000
   7.750   1.2165   0.01501   0.00794  -0.0764   0.1613   1.0000
   8.000   1.2119   0.01674   0.00912  -0.0718   0.0736   1.0000
   8.250   1.2158   0.01811   0.01028  -0.0685   0.0311   1.0000
   8.500   1.2312   0.01874   0.01093  -0.0668   0.0243   1.0000
   8.750   1.2453   0.01946   0.01166  -0.0650   0.0197   1.0000
   9.000   1.2611   0.02008   0.01233  -0.0635   0.0175   1.0000
   9.250   1.2747   0.02087   0.01315  -0.0619   0.0154   1.0000
   9.500   1.2894   0.02158   0.01392  -0.0603   0.0143   1.0000
   9.750   1.3033   0.02235   0.01474  -0.0588   0.0129   1.0000
  10.000   1.3153   0.02328   0.01571  -0.0571   0.0118   1.0000
  10.250   1.3284   0.02414   0.01664  -0.0556   0.0111   1.0000
  10.500   1.3403   0.02510   0.01767  -0.0541   0.0105   1.0000
  10.750   1.3516   0.02611   0.01876  -0.0525   0.0099   1.0000
  11.000   1.3604   0.02733   0.02003  -0.0508   0.0094   1.0000
  11.250   1.3692   0.02857   0.02136  -0.0492   0.0089   1.0000
  11.500   1.3789   0.02974   0.02261  -0.0477   0.0083   1.0000
  11.750   1.3865   0.03112   0.02407  -0.0462   0.0080   1.0000
  12.000   1.3932   0.03259   0.02561  -0.0447   0.0076   1.0000
  12.250   1.3977   0.03427   0.02736  -0.0431   0.0073   1.0000
  12.500   1.3983   0.03634   0.02952  -0.0415   0.0071   1.0000
  12.750   1.4016   0.03823   0.03155  -0.0401   0.0069   1.0000
  13.000   1.4029   0.04037   0.03380  -0.0388   0.0067   1.0000
  13.250   1.4027   0.04275   0.03629  -0.0376   0.0066   1.0000
  13.500   1.4027   0.04520   0.03886  -0.0366   0.0064   1.0000
  13.750   1.4009   0.04800   0.04176  -0.0358   0.0062   1.0000
  14.000   1.3996   0.05087   0.04473  -0.0353   0.0060   1.0000
  14.250   1.3972   0.05402   0.04800  -0.0350   0.0059   1.0000
  14.500   1.3914   0.05776   0.05185  -0.0350   0.0058   1.0000
  14.750   1.3912   0.06093   0.05510  -0.0353   0.0056   1.0000
  15.000   1.3857   0.06497   0.05924  -0.0358   0.0055   1.0000
  15.250   1.3757   0.06981   0.06421  -0.0367   0.0055   1.0000
  15.500   1.3669   0.07466   0.06918  -0.0379   0.0053   1.0000
  15.750   1.3607   0.07932   0.07397  -0.0392   0.0052   1.0000
  16.000   1.3532   0.08427   0.07905  -0.0407   0.0052   1.0000
  16.250   1.3454   0.08933   0.08423  -0.0423   0.0051   1.0000
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