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GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 592 AIRFOIL (goe592-il)
Reynolds number: 500,000
Max Cl/Cd: 107.05 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe592-il-500000-n5.txt
Download as CSV file: xf-goe592-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 592 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3289   0.02711   0.02296  -0.1710   0.8275   0.0316
 -11.000  -0.3268   0.02382   0.01924  -0.1707   0.8215   0.0320
 -10.750  -0.3124   0.02232   0.01755  -0.1700   0.8155   0.0322
 -10.500  -0.2934   0.02139   0.01650  -0.1693   0.8097   0.0325
 -10.250  -0.2726   0.02062   0.01561  -0.1687   0.8045   0.0328
 -10.000  -0.2511   0.01991   0.01481  -0.1681   0.7988   0.0332
  -9.750  -0.2291   0.01923   0.01401  -0.1675   0.7933   0.0335
  -9.250  -0.1841   0.01786   0.01237  -0.1664   0.7827   0.0344
  -9.000  -0.1611   0.01721   0.01158  -0.1658   0.7767   0.0349
  -8.750  -0.1377   0.01660   0.01079  -0.1653   0.7712   0.0355
  -8.500  -0.1139   0.01601   0.01004  -0.1647   0.7659   0.0360
  -8.250  -0.0899   0.01548   0.00940  -0.1642   0.7602   0.0364
  -8.000  -0.0651   0.01509   0.00894  -0.1637   0.7546   0.0369
  -7.750  -0.0399   0.01474   0.00853  -0.1632   0.7491   0.0373
  -7.500  -0.0146   0.01442   0.00813  -0.1627   0.7430   0.0379
  -7.250   0.0108   0.01410   0.00772  -0.1623   0.7374   0.0385
  -7.000   0.0363   0.01377   0.00730  -0.1618   0.7321   0.0392
  -6.750   0.0619   0.01345   0.00687  -0.1613   0.7261   0.0399
  -6.500   0.0874   0.01315   0.00646  -0.1608   0.7203   0.0406
  -6.250   0.1133   0.01292   0.00620  -0.1604   0.7150   0.0415
  -6.000   0.1395   0.01274   0.00598  -0.1600   0.7093   0.0423
  -5.750   0.1654   0.01256   0.00573  -0.1596   0.7035   0.0433
  -5.500   0.1914   0.01235   0.00545  -0.1591   0.6983   0.0444
  -5.250   0.2175   0.01214   0.00515  -0.1587   0.6928   0.0454
  -5.000   0.2435   0.01198   0.00498  -0.1582   0.6872   0.0464
  -4.750   0.2696   0.01188   0.00483  -0.1578   0.6821   0.0476
  -4.500   0.2960   0.01174   0.00465  -0.1574   0.6767   0.0489
  -4.250   0.3221   0.01161   0.00446  -0.1569   0.6713   0.0505
  -4.000   0.3480   0.01153   0.00434  -0.1564   0.6661   0.0519
  -3.750   0.3744   0.01147   0.00426  -0.1561   0.6613   0.0534
  -3.500   0.4006   0.01138   0.00414  -0.1556   0.6561   0.0552
  -3.250   0.4264   0.01129   0.00399  -0.1551   0.6510   0.0568
  -3.000   0.4523   0.01125   0.00392  -0.1546   0.6464   0.0582
  -2.750   0.4787   0.01120   0.00387  -0.1542   0.6417   0.0600
  -2.500   0.5046   0.01115   0.00379  -0.1538   0.6368   0.0620
  -2.250   0.5302   0.01110   0.00370  -0.1532   0.6322   0.0637
  -2.000   0.5559   0.01107   0.00365  -0.1527   0.6279   0.0654
  -1.750   0.5818   0.01103   0.00361  -0.1523   0.6234   0.0672
  -1.500   0.6074   0.01100   0.00356  -0.1518   0.6187   0.0693
  -1.250   0.6326   0.01097   0.00350  -0.1512   0.6143   0.0710
  -1.000   0.6577   0.01094   0.00347  -0.1506   0.6100   0.0731
  -0.750   0.6832   0.01091   0.00344  -0.1500   0.6056   0.0751
  -0.500   0.7082   0.01089   0.00342  -0.1494   0.6011   0.0771
  -0.250   0.7329   0.01091   0.00340  -0.1488   0.5966   0.0787
   0.000   0.7572   0.01087   0.00336  -0.1480   0.5924   0.0810
   0.250   0.7820   0.01084   0.00336  -0.1474   0.5881   0.0833
   0.500   0.8063   0.01085   0.00337  -0.1467   0.5835   0.0856
   0.750   0.8301   0.01088   0.00338  -0.1458   0.5790   0.0877
   1.000   0.8535   0.01091   0.00339  -0.1449   0.5745   0.0905
   1.250   0.8775   0.01090   0.00343  -0.1442   0.5701   0.0941
   1.500   0.9006   0.01093   0.00347  -0.1432   0.5653   0.0978
   1.750   0.9225   0.01099   0.00352  -0.1420   0.5606   0.1026
   2.000   0.9438   0.01102   0.00358  -0.1407   0.5561   0.1111
   2.250   0.9651   0.01103   0.00366  -0.1394   0.5512   0.1269
   2.500   0.9851   0.01106   0.00375  -0.1379   0.5460   0.1535
   2.750   1.0044   0.01113   0.00387  -0.1363   0.5410   0.1864
   3.000   1.0253   0.01112   0.00402  -0.1350   0.5360   0.2440
   3.250   1.0440   0.01100   0.00423  -0.1335   0.5306   0.3909
   3.750   1.1122   0.01039   0.00482  -0.1368   0.5172   1.0000
   4.000   1.1296   0.01060   0.00498  -0.1349   0.5094   1.0000
   4.250   1.1480   0.01082   0.00516  -0.1332   0.5024   1.0000
   4.500   1.1659   0.01105   0.00535  -0.1314   0.4942   1.0000
   4.750   1.1827   0.01133   0.00558  -0.1295   0.4858   1.0000
   5.000   1.2002   0.01160   0.00582  -0.1277   0.4769   1.0000
   5.250   1.2172   0.01191   0.00608  -0.1259   0.4692   1.0000
   5.500   1.2361   0.01218   0.00634  -0.1245   0.4621   1.0000
   5.750   1.2518   0.01256   0.00666  -0.1225   0.4545   1.0000
   6.000   1.2705   0.01286   0.00696  -0.1211   0.4463   1.0000
   6.250   1.2848   0.01331   0.00735  -0.1190   0.4376   1.0000
   6.500   1.3032   0.01365   0.00769  -0.1176   0.4296   1.0000
   6.750   1.3177   0.01414   0.00813  -0.1157   0.4211   1.0000
   7.000   1.3353   0.01454   0.00852  -0.1143   0.4133   1.0000
   7.250   1.3504   0.01504   0.00899  -0.1125   0.4054   1.0000
   7.500   1.3667   0.01551   0.00946  -0.1110   0.3973   1.0000
   7.750   1.3798   0.01613   0.01004  -0.1090   0.3879   1.0000
   8.000   1.3941   0.01672   0.01061  -0.1073   0.3769   1.0000
   8.250   1.4057   0.01746   0.01131  -0.1052   0.3660   1.0000
   8.500   1.4185   0.01817   0.01200  -0.1034   0.3557   1.0000
   8.750   1.4319   0.01888   0.01269  -0.1018   0.3468   1.0000
   9.250   1.4527   0.02068   0.01442  -0.0979   0.3235   1.0000
   9.500   1.4610   0.02175   0.01545  -0.0958   0.3095   1.0000
   9.750   1.4682   0.02293   0.01658  -0.0937   0.2956   1.0000
  10.000   1.4741   0.02424   0.01784  -0.0915   0.2814   1.0000
  10.250   1.4799   0.02561   0.01915  -0.0895   0.2676   1.0000
  10.500   1.4863   0.02700   0.02050  -0.0876   0.2557   1.0000
  10.750   1.4934   0.02837   0.02185  -0.0858   0.2440   1.0000
  11.000   1.4987   0.02992   0.02336  -0.0840   0.2318   1.0000
  11.250   1.5035   0.03156   0.02497  -0.0823   0.2208   1.0000
  11.500   1.5079   0.03326   0.02664  -0.0806   0.2090   1.0000
  11.750   1.5131   0.03496   0.02831  -0.0791   0.1975   1.0000
  12.000   1.5150   0.03696   0.03028  -0.0774   0.1841   1.0000
  12.250   1.5149   0.03919   0.03246  -0.0757   0.1683   1.0000
  12.500   1.5123   0.04168   0.03487  -0.0740   0.1508   1.0000
  12.750   1.5083   0.04437   0.03748  -0.0722   0.1339   1.0000
  13.000   1.5057   0.04701   0.04007  -0.0708   0.1210   1.0000
  13.250   1.5051   0.04953   0.04257  -0.0695   0.1119   1.0000
  13.500   1.5079   0.05174   0.04479  -0.0685   0.1060   1.0000
  13.750   1.5094   0.05414   0.04721  -0.0675   0.1012   1.0000
  14.000   1.5125   0.05641   0.04951  -0.0666   0.0973   1.0000
  14.250   1.5168   0.05860   0.05174  -0.0659   0.0948   1.0000
  14.500   1.5193   0.06099   0.05417  -0.0652   0.0920   1.0000
  14.750   1.5216   0.06342   0.05664  -0.0645   0.0899   1.0000
  15.000   1.5239   0.06589   0.05917  -0.0639   0.0880   1.0000
  15.250   1.5289   0.06811   0.06145  -0.0634   0.0867   1.0000
  15.500   1.5325   0.07049   0.06389  -0.0630   0.0854   1.0000
  15.750   1.5354   0.07298   0.06644  -0.0626   0.0841   1.0000
  16.000   1.5377   0.07554   0.06907  -0.0622   0.0828   1.0000
  16.250   1.5388   0.07827   0.07185  -0.0619   0.0815   1.0000
  16.500   1.5392   0.08114   0.07477  -0.0617   0.0802   1.0000
  16.750   1.5382   0.08419   0.07788  -0.0615   0.0788   1.0000
  17.000   1.5400   0.08694   0.08070  -0.0614   0.0778   1.0000
  17.250   1.5436   0.08948   0.08332  -0.0614   0.0770   1.0000
  17.500   1.5472   0.09201   0.08593  -0.0614   0.0756   1.0000
  17.750   1.5491   0.09478   0.08877  -0.0615   0.0746   1.0000
  18.000   1.5508   0.09760   0.09165  -0.0617   0.0730   1.0000
  18.250   1.5509   0.10068   0.09478  -0.0620   0.0718   1.0000
  18.500   1.5507   0.10379   0.09794  -0.0623   0.0706   1.0000
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