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GOE 433 AIRFOIL (goe433-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 433 AIRFOIL (goe433-il)
Reynolds number: 50,000
Max Cl/Cd: 22.75 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe433-il-50000-n5.txt
Download as CSV file: xf-goe433-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 433 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2857   0.11571   0.10791  -0.0461   1.0000   0.1287
 -10.250  -0.2984   0.11385   0.10614  -0.0445   1.0000   0.1292
 -10.000  -0.3132   0.11203   0.10441  -0.0427   1.0000   0.1294
  -9.750  -0.3061   0.10730   0.09965  -0.0473   0.9931   0.1303
  -9.500  -0.3032   0.10175   0.09406  -0.0531   0.9845   0.1322
  -9.250  -0.3103   0.09459   0.08685  -0.0605   0.9751   0.1339
  -9.000  -0.2938   0.09085   0.08310  -0.0644   0.9670   0.1354
  -8.750  -0.2718   0.08831   0.08052  -0.0672   0.9587   0.1375
  -8.500  -0.2558   0.08456   0.07675  -0.0716   0.9504   0.1403
  -8.250  -0.2581   0.07931   0.07146  -0.0765   0.9380   0.1429
  -8.000  -0.3445   0.05682   0.04850  -0.1021   0.9141   0.1473
  -7.750  -0.3365   0.05349   0.04504  -0.1050   0.9014   0.1501
  -7.500  -0.3088   0.05198   0.04347  -0.1071   0.8942   0.1534
  -7.250  -0.2972   0.04816   0.03935  -0.1110   0.8827   0.1573
  -7.000  -0.2811   0.04300   0.03344  -0.1175   0.8730   0.1632
  -6.750  -0.2540   0.04244   0.03299  -0.1176   0.8647   0.1665
  -6.500  -0.2204   0.04108   0.03152  -0.1198   0.8594   0.1715
  -6.250  -0.2018   0.03929   0.02939  -0.1210   0.8486   0.1768
  -6.000  -0.1701   0.03800   0.02797  -0.1228   0.8425   0.1823
  -5.750  -0.1446   0.03741   0.02735  -0.1230   0.8344   0.1877
  -5.500  -0.1167   0.03603   0.02563  -0.1246   0.8263   0.1951
  -5.250  -0.0834   0.03541   0.02506  -0.1256   0.8213   0.2013
  -5.000  -0.0620   0.03496   0.02451  -0.1254   0.8116   0.2085
  -4.750  -0.0316   0.03421   0.02364  -0.1263   0.8049   0.2165
  -4.500   0.0033   0.03356   0.02292  -0.1276   0.8003   0.2261
  -4.250   0.0218   0.03337   0.02266  -0.1268   0.7895   0.2340
  -4.000   0.0535   0.03291   0.02215  -0.1275   0.7836   0.2443
  -3.750   0.0795   0.03264   0.02185  -0.1275   0.7759   0.2543
  -3.500   0.1055   0.03238   0.02150  -0.1276   0.7676   0.2663
  -3.250   0.1381   0.03199   0.02115  -0.1281   0.7625   0.2785
  -3.000   0.1592   0.03199   0.02111  -0.1276   0.7530   0.2910
  -2.750   0.1881   0.03173   0.02082  -0.1278   0.7464   0.3051
  -2.500   0.2214   0.03133   0.02046  -0.1282   0.7420   0.3198
  -2.250   0.2387   0.03160   0.02075  -0.1272   0.7314   0.3326
  -2.000   0.2704   0.03130   0.02042  -0.1275   0.7259   0.3497
  -1.750   0.2939   0.03148   0.02067  -0.1269   0.7183   0.3645
  -1.500   0.3186   0.03160   0.02085  -0.1263   0.7106   0.3801
  -1.250   0.3512   0.03139   0.02064  -0.1264   0.7058   0.3985
  -1.000   0.3702   0.03188   0.02117  -0.1254   0.6965   0.4145
  -0.750   0.3990   0.03190   0.02118  -0.1252   0.6903   0.4334
  -0.500   0.4330   0.03167   0.02090  -0.1254   0.6861   0.4534
  -0.250   0.4494   0.03236   0.02162  -0.1243   0.6756   0.4700
   0.250   0.5075   0.03241   0.02161  -0.1239   0.6641   0.5091
   0.500   0.5277   0.03293   0.02215  -0.1229   0.6553   0.5277
   0.750   0.5587   0.03278   0.02199  -0.1227   0.6503   0.5487
   1.000   0.5809   0.03318   0.02242  -0.1219   0.6429   0.5678
   1.250   0.6031   0.03357   0.02283  -0.1211   0.6350   0.5861
   1.500   0.6351   0.03335   0.02258  -0.1211   0.6303   0.6051
   1.750   0.6536   0.03393   0.02322  -0.1199   0.6223   0.6198
   2.000   0.6752   0.03435   0.02369  -0.1190   0.6146   0.6354
   2.250   0.7069   0.03414   0.02347  -0.1189   0.6101   0.6531
   2.500   0.7237   0.03494   0.02433  -0.1178   0.6017   0.6684
   2.750   0.7439   0.03551   0.02495  -0.1169   0.5941   0.6852
   3.000   0.7749   0.03534   0.02479  -0.1167   0.5896   0.7039
   3.250   0.7867   0.03642   0.02598  -0.1150   0.5811   0.7200
   3.500   0.8039   0.03711   0.02677  -0.1137   0.5735   0.7389
   3.750   0.8342   0.03690   0.02660  -0.1134   0.5693   0.7631
   4.250   0.8529   0.03910   0.02910  -0.1094   0.5530   0.8198
   4.750   0.8725   0.04136   0.03157  -0.1064   0.5373   1.0000
   5.000   0.9037   0.04181   0.03194  -0.1073   0.5322   1.0000
   5.250   0.9451   0.04155   0.03157  -0.1088   0.5291   1.0000
   5.750   0.9553   0.04563   0.03564  -0.1063   0.5119   1.0000
   6.000   0.9914   0.04542   0.03537  -0.1068   0.5087   1.0000
   6.250   0.9631   0.05042   0.04046  -0.1044   0.4948   1.0000
   6.500   1.0011   0.04975   0.03973  -0.1045   0.4921   1.0000
   7.000   1.0077   0.05466   0.04469  -0.1026   0.4747   1.0000
   7.500   1.0282   0.05781   0.04787  -0.1007   0.4571   1.0000
   7.750   1.0793   0.05491   0.04490  -0.1000   0.4548   1.0000
   8.000   1.0526   0.06033   0.05040  -0.0987   0.4394   1.0000
   8.250   1.1005   0.05760   0.04765  -0.0978   0.4370   1.0000
   8.750   1.0545   0.06883   0.05904  -0.0965   0.4088   1.0000
   9.000   1.0807   0.06844   0.05867  -0.0955   0.4038   1.0000
   9.250   1.1193   0.06653   0.05676  -0.0942   0.4011   1.0000
   9.750   1.1299   0.07090   0.06123  -0.0926   0.3829   1.0000
  10.250   1.1422   0.07497   0.06541  -0.0911   0.3645   1.0000
  10.750   1.1291   0.08260   0.07316  -0.0905   0.3414   1.0000
  11.250   1.1594   0.08390   0.07452  -0.0885   0.3257   1.0000
  11.750   1.1254   0.09528   0.08605  -0.0897   0.2996   1.0000
  12.000   1.1542   0.09369   0.08449  -0.0881   0.2949   1.0000
  12.500   1.1609   0.09895   0.08984  -0.0878   0.2777   1.0000
  13.000   1.1611   0.10565   0.09664  -0.0883   0.2613   1.0000
  13.500   1.1584   0.11307   0.10418  -0.0893   0.2455   1.0000
  13.750   1.1905   0.11070   0.10182  -0.0874   0.2429   1.0000
  14.000   1.1525   0.12145   0.11267  -0.0913   0.2305   1.0000
  14.250   1.1817   0.11943   0.11068  -0.0895   0.2276   1.0000
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