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GOE 622 AIRFOIL (goe622-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 622 AIRFOIL (goe622-il)
Reynolds number: 500,000
Max Cl/Cd: 75.52 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe622-il-500000-n5.txt
Download as CSV file: xf-goe622-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 622 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5316   0.08471   0.08256  -0.0159   1.0000   0.0055
  -8.750  -0.5390   0.07880   0.07670  -0.0195   1.0000   0.0054
  -8.250  -0.6272   0.03371   0.03091  -0.0503   1.0000   0.0048
  -8.000  -0.6250   0.02696   0.02348  -0.0500   1.0000   0.0049
  -7.750  -0.6122   0.02365   0.01971  -0.0489   1.0000   0.0050
  -7.500  -0.5962   0.02129   0.01698  -0.0477   1.0000   0.0052
  -7.250  -0.5706   0.01924   0.01456  -0.0482   0.9984   0.0055
  -7.000  -0.5382   0.01757   0.01256  -0.0498   0.9954   0.0057
  -6.750  -0.5059   0.01634   0.01108  -0.0512   0.9915   0.0060
  -6.500  -0.4740   0.01475   0.00926  -0.0526   0.9875   0.0065
  -6.250  -0.4422   0.01412   0.00855  -0.0538   0.9823   0.0071
  -6.000  -0.4094   0.01347   0.00777  -0.0551   0.9772   0.0079
  -5.750  -0.3789   0.01273   0.00689  -0.0558   0.9698   0.0085
  -5.500  -0.3475   0.01209   0.00612  -0.0566   0.9640   0.0091
  -5.250  -0.3171   0.01124   0.00512  -0.0573   0.9566   0.0104
  -5.000  -0.2859   0.01076   0.00459  -0.0581   0.9495   0.0123
  -4.750  -0.2548   0.01039   0.00415  -0.0588   0.9417   0.0145
  -4.500  -0.2246   0.00992   0.00362  -0.0592   0.9331   0.0198
  -4.250  -0.1948   0.00964   0.00328  -0.0596   0.9244   0.0264
  -4.000  -0.1665   0.00938   0.00301  -0.0597   0.9148   0.0346
  -3.750  -0.1386   0.00914   0.00274  -0.0596   0.9061   0.0423
  -3.500  -0.1109   0.00893   0.00250  -0.0595   0.8973   0.0515
  -3.250  -0.0836   0.00872   0.00232  -0.0594   0.8880   0.0668
  -3.000  -0.0562   0.00857   0.00218  -0.0593   0.8794   0.0848
  -2.750  -0.0287   0.00845   0.00203  -0.0591   0.8707   0.0964
  -2.500  -0.0011   0.00835   0.00190  -0.0590   0.8617   0.1047
  -2.250   0.0264   0.00826   0.00177  -0.0589   0.8523   0.1130
  -2.000   0.0539   0.00815   0.00164  -0.0587   0.8424   0.1235
  -1.750   0.0814   0.00804   0.00154  -0.0586   0.8322   0.1351
  -1.500   0.1087   0.00795   0.00144  -0.0584   0.8194   0.1495
  -1.250   0.1355   0.00776   0.00134  -0.0582   0.8031   0.1925
  -1.000   0.1620   0.00751   0.00126  -0.0580   0.7855   0.2647
  -0.750   0.1885   0.00727   0.00120  -0.0578   0.7649   0.3440
  -0.500   0.2143   0.00705   0.00114  -0.0574   0.7371   0.4342
  -0.250   0.2390   0.00689   0.00109  -0.0568   0.6919   0.5311
   0.000   0.2629   0.00675   0.00108  -0.0560   0.6462   0.6410
   0.250   0.2863   0.00656   0.00112  -0.0550   0.6160   0.7544
   0.500   0.3085   0.00638   0.00118  -0.0535   0.5974   0.8564
   0.750   0.3355   0.00634   0.00122  -0.0529   0.5821   0.9373
   1.000   0.3776   0.00642   0.00124  -0.0560   0.5646   0.9930
   1.250   0.4076   0.00653   0.00127  -0.0565   0.5496   1.0000
   1.500   0.4342   0.00664   0.00132  -0.0563   0.5367   1.0000
   1.750   0.4609   0.00677   0.00138  -0.0560   0.5224   1.0000
   2.000   0.4875   0.00690   0.00144  -0.0558   0.5055   1.0000
   2.250   0.5141   0.00704   0.00152  -0.0555   0.4867   1.0000
   2.500   0.5402   0.00725   0.00161  -0.0552   0.4567   1.0000
   2.750   0.5660   0.00750   0.00171  -0.0549   0.4179   1.0000
   3.000   0.5913   0.00783   0.00184  -0.0545   0.3709   1.0000
   3.250   0.6165   0.00819   0.00203  -0.0541   0.3280   1.0000
   3.500   0.6420   0.00853   0.00222  -0.0538   0.2933   1.0000
   3.750   0.6676   0.00886   0.00243  -0.0535   0.2617   1.0000
   4.000   0.6924   0.00932   0.00268  -0.0531   0.2171   1.0000
   4.250   0.7170   0.00981   0.00296  -0.0528   0.1689   1.0000
   4.500   0.7411   0.01036   0.00328  -0.0523   0.1257   1.0000
   4.750   0.7667   0.01070   0.00356  -0.0520   0.1090   1.0000
   5.000   0.7923   0.01103   0.00383  -0.0517   0.0918   1.0000
   5.250   0.8159   0.01165   0.00424  -0.0512   0.0511   1.0000
   5.500   0.8391   0.01235   0.00476  -0.0506   0.0187   1.0000
   5.750   0.8642   0.01276   0.00519  -0.0501   0.0133   1.0000
   6.000   0.8894   0.01317   0.00568  -0.0497   0.0111   1.0000
   6.250   0.9144   0.01357   0.00617  -0.0492   0.0097   1.0000
   6.500   0.9388   0.01407   0.00677  -0.0487   0.0087   1.0000
   6.750   0.9621   0.01471   0.00750  -0.0480   0.0078   1.0000
   7.000   0.9840   0.01557   0.00848  -0.0471   0.0072   1.0000
   7.250   1.0075   0.01613   0.00912  -0.0465   0.0067   1.0000
   7.500   1.0306   0.01672   0.00978  -0.0458   0.0061   1.0000
   7.750   1.0529   0.01740   0.01052  -0.0451   0.0056   1.0000
   8.000   1.0744   0.01817   0.01136  -0.0442   0.0052   1.0000
   8.250   1.0941   0.01913   0.01244  -0.0431   0.0050   1.0000
   8.500   1.1105   0.02054   0.01396  -0.0416   0.0047   1.0000
   8.750   1.1297   0.02155   0.01509  -0.0404   0.0045   1.0000
   9.000   1.1475   0.02272   0.01640  -0.0390   0.0044   1.0000
   9.250   1.1641   0.02404   0.01788  -0.0375   0.0042   1.0000
   9.500   1.1795   0.02551   0.01951  -0.0359   0.0041   1.0000
   9.750   1.1944   0.02698   0.02115  -0.0343   0.0039   1.0000
  10.000   1.2089   0.02833   0.02265  -0.0327   0.0037   1.0000
  10.250   1.2227   0.02960   0.02406  -0.0312   0.0035   1.0000
  10.500   1.2353   0.03080   0.02538  -0.0296   0.0033   1.0000
  10.750   1.2449   0.03205   0.02675  -0.0276   0.0032   1.0000
  11.000   1.2501   0.03351   0.02832  -0.0252   0.0031   1.0000
  11.250   1.2507   0.03553   0.03050  -0.0226   0.0031   1.0000
  11.500   1.2461   0.03817   0.03334  -0.0200   0.0030   1.0000
  11.750   1.2392   0.04119   0.03664  -0.0179   0.0030   1.0000
  12.000   1.2336   0.04420   0.03988  -0.0166   0.0029   1.0000
  12.250   1.2258   0.04769   0.04359  -0.0160   0.0029   1.0000
  12.500   1.2159   0.05177   0.04789  -0.0162   0.0029   1.0000
  12.750   1.2035   0.05658   0.05293  -0.0173   0.0029   1.0000
  13.000   1.1902   0.06203   0.05858  -0.0195   0.0028   1.0000
  13.250   1.1747   0.06829   0.06505  -0.0226   0.0028   1.0000
  13.500   1.1585   0.07516   0.07209  -0.0264   0.0029   1.0000
  13.750   1.1406   0.08275   0.07985  -0.0307   0.0029   1.0000
  14.000   1.1228   0.09079   0.08804  -0.0355   0.0029   1.0000
  14.250   1.1045   0.09944   0.09682  -0.0405   0.0029   1.0000
  14.500   1.0860   0.10858   0.10606  -0.0457   0.0029   1.0000
  14.750   1.0672   0.11809   0.11564  -0.0509   0.0029   1.0000
  15.000   1.0488   0.12761   0.12524  -0.0559   0.0030   1.0000
  15.250   0.8170   0.12404   0.12189  -0.0350   0.0034   1.0000
  15.500   0.7632   0.13758   0.13559  -0.0414   0.0038   1.0000
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