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GOE 592 AIRFOIL (goe592-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 592 AIRFOIL (goe592-il)
Reynolds number: 500,000
Max Cl/Cd: 114.86 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe592-il-500000.txt
Download as CSV file: xf-goe592-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500   0.1341   0.09631   0.09344  -0.1414   0.9338   0.0390
 -11.250   0.1236   0.09199   0.08907  -0.1476   0.9252   0.0414
 -11.000   0.1334   0.08920   0.08628  -0.1472   0.9184   0.0416
 -10.750   0.1511   0.08723   0.08429  -0.1470   0.9127   0.0419
 -10.500   0.1660   0.08502   0.08203  -0.1482   0.9074   0.0423
 -10.250   0.1735   0.08344   0.08045  -0.1476   0.8992   0.0429
 -10.000   0.1832   0.08128   0.07825  -0.1485   0.8926   0.0437
  -9.750   0.1570   0.07738   0.07434  -0.1515   0.8800   0.0463
  -9.500   0.1656   0.07438   0.07129  -0.1520   0.8740   0.0466
  -9.250   0.1788   0.07285   0.06975  -0.1509   0.8672   0.0469
  -9.000   0.1913   0.07121   0.06809  -0.1506   0.8604   0.0472
  -8.750   0.2018   0.06957   0.06642  -0.1505   0.8536   0.0478
  -8.500   0.2075   0.06778   0.06462  -0.1502   0.8454   0.0485
  -8.250   0.2125   0.06573   0.06251  -0.1506   0.8380   0.0497
  -7.750   0.1632   0.05771   0.05449  -0.1534   0.8160   0.0522
  -7.500   0.1742   0.05618   0.05294  -0.1527   0.8091   0.0524
  -7.250   0.1856   0.05460   0.05131  -0.1526   0.8026   0.0527
  -7.000   0.0537   0.01895   0.01356  -0.1644   0.7885   0.0467
  -6.750   0.0780   0.01852   0.01312  -0.1640   0.7827   0.0473
  -6.500   0.1031   0.01831   0.01289  -0.1635   0.7766   0.0480
  -6.250   0.1284   0.01783   0.01229  -0.1631   0.7713   0.0488
  -6.000   0.1514   0.01692   0.01119  -0.1624   0.7655   0.0498
  -5.750   0.1741   0.01593   0.00993  -0.1617   0.7594   0.0510
  -5.500   0.1987   0.01508   0.00882  -0.1611   0.7540   0.0522
  -5.250   0.2243   0.01474   0.00847  -0.1607   0.7485   0.0532
  -5.000   0.2501   0.01459   0.00831  -0.1603   0.7424   0.0543
  -4.750   0.2767   0.01435   0.00796  -0.1599   0.7369   0.0557
  -4.500   0.3027   0.01399   0.00743  -0.1595   0.7316   0.0574
  -4.250   0.3276   0.01345   0.00682  -0.1589   0.7257   0.0588
  -4.000   0.3543   0.01329   0.00664  -0.1586   0.7203   0.0602
  -3.750   0.3812   0.01315   0.00643  -0.1583   0.7152   0.0619
  -3.500   0.4070   0.01299   0.00621  -0.1578   0.7095   0.0640
  -3.250   0.4329   0.01263   0.00578  -0.1574   0.7042   0.0661
  -3.000   0.4603   0.01254   0.00565  -0.1572   0.6992   0.0680
  -2.750   0.4858   0.01239   0.00550  -0.1567   0.6940   0.0702
  -2.500   0.5122   0.01232   0.00534  -0.1562   0.6887   0.0722
  -2.250   0.5384   0.01196   0.00496  -0.1559   0.6839   0.0748
  -2.000   0.5647   0.01188   0.00489  -0.1555   0.6790   0.0773
  -1.750   0.5904   0.01178   0.00477  -0.1550   0.6739   0.0798
  -1.500   0.6166   0.01164   0.00456  -0.1546   0.6691   0.0820
  -1.250   0.6435   0.01145   0.00435  -0.1544   0.6644   0.0851
  -1.000   0.6683   0.01135   0.00429  -0.1537   0.6597   0.0877
  -0.750   0.6939   0.01129   0.00422  -0.1532   0.6548   0.0904
  -0.500   0.7198   0.01115   0.00404  -0.1528   0.6501   0.0930
  -0.250   0.7460   0.01106   0.00394  -0.1524   0.6455   0.0963
   0.000   0.7706   0.01100   0.00392  -0.1517   0.6408   0.0995
   0.250   0.7959   0.01096   0.00387  -0.1512   0.6360   0.1023
   0.500   0.8218   0.01090   0.00378  -0.1508   0.6315   0.1063
   0.750   0.8472   0.01088   0.00378  -0.1503   0.6269   0.1108
   1.000   0.8715   0.01086   0.00379  -0.1495   0.6221   0.1151
   1.250   0.8962   0.01083   0.00377  -0.1488   0.6173   0.1221
   1.500   0.9228   0.01087   0.00379  -0.1486   0.6126   0.1325
   1.750   0.9460   0.01081   0.00386  -0.1477   0.6079   0.1583
   2.000   0.9681   0.01061   0.00396  -0.1467   0.6030   0.2618
   2.250   1.0255   0.00938   0.00432  -0.1535   0.5979   1.0000
   2.500   1.0498   0.00954   0.00439  -0.1528   0.5931   1.0000
   2.750   1.0708   0.00963   0.00448  -0.1514   0.5879   1.0000
   3.000   1.0927   0.00974   0.00455  -0.1502   0.5825   1.0000
   3.250   1.1170   0.00992   0.00463  -0.1495   0.5772   1.0000
   3.500   1.1364   0.01001   0.00474  -0.1478   0.5716   1.0000
   3.750   1.1562   0.01013   0.00483  -0.1462   0.5652   1.0000
   4.000   1.1784   0.01032   0.00493  -0.1451   0.5592   1.0000
   4.250   1.1962   0.01042   0.00507  -0.1431   0.5532   1.0000
   4.500   1.2129   0.01056   0.00517  -0.1409   0.5466   1.0000
   4.750   1.2299   0.01074   0.00531  -0.1388   0.5400   1.0000
   5.000   1.2451   0.01089   0.00547  -0.1364   0.5330   1.0000
   5.250   1.2623   0.01110   0.00562  -0.1344   0.5264   1.0000
   5.500   1.2796   0.01129   0.00582  -0.1325   0.5200   1.0000
   5.750   1.2964   0.01151   0.00603  -0.1305   0.5131   1.0000
   6.000   1.3136   0.01177   0.00625  -0.1287   0.5065   1.0000
   6.250   1.3304   0.01200   0.00650  -0.1268   0.4991   1.0000
   6.500   1.3464   0.01231   0.00676  -0.1248   0.4919   1.0000
   6.750   1.3631   0.01258   0.00706  -0.1230   0.4843   1.0000
   7.000   1.3788   0.01292   0.00737  -0.1210   0.4767   1.0000
   7.250   1.3951   0.01327   0.00771  -0.1192   0.4693   1.0000
   7.500   1.4103   0.01365   0.00808  -0.1173   0.4611   1.0000
   7.750   1.4260   0.01405   0.00848  -0.1155   0.4539   1.0000
   8.000   1.4410   0.01448   0.00890  -0.1136   0.4454   1.0000
   8.250   1.4549   0.01498   0.00938  -0.1116   0.4369   1.0000
   8.500   1.4679   0.01552   0.00991  -0.1096   0.4272   1.0000
   8.750   1.4819   0.01606   0.01045  -0.1077   0.4185   1.0000
   9.000   1.4945   0.01668   0.01105  -0.1057   0.4096   1.0000
   9.250   1.5074   0.01731   0.01168  -0.1039   0.3998   1.0000
   9.500   1.5165   0.01813   0.01246  -0.1015   0.3895   1.0000
   9.750   1.5289   0.01885   0.01319  -0.0997   0.3784   1.0000
  10.000   1.5389   0.01971   0.01404  -0.0977   0.3678   1.0000
  10.250   1.5472   0.02070   0.01499  -0.0955   0.3573   1.0000
  10.500   1.5584   0.02158   0.01588  -0.0937   0.3463   1.0000
  10.750   1.5665   0.02266   0.01695  -0.0917   0.3356   1.0000
  11.000   1.5724   0.02391   0.01816  -0.0896   0.3240   1.0000
  11.250   1.5804   0.02511   0.01936  -0.0877   0.3116   1.0000
  11.500   1.5862   0.02648   0.02071  -0.0858   0.2990   1.0000
  11.750   1.5905   0.02800   0.02220  -0.0837   0.2863   1.0000
  12.000   1.5924   0.02976   0.02392  -0.0816   0.2724   1.0000
  12.250   1.5934   0.03166   0.02577  -0.0796   0.2586   1.0000
  12.500   1.5947   0.03359   0.02767  -0.0777   0.2448   1.0000
  12.750   1.5945   0.03571   0.02975  -0.0758   0.2300   1.0000
  13.000   1.5927   0.03803   0.03201  -0.0740   0.2146   1.0000
  13.250   1.5879   0.04067   0.03459  -0.0720   0.1975   1.0000
  13.500   1.5808   0.04360   0.03744  -0.0701   0.1757   1.0000
  13.750   1.5697   0.04700   0.04071  -0.0682   0.1539   1.0000
  14.000   1.5589   0.05047   0.04409  -0.0665   0.1353   1.0000
  14.250   1.5520   0.05365   0.04722  -0.0651   0.1242   1.0000
  14.500   1.5463   0.05680   0.05035  -0.0639   0.1169   1.0000
  14.750   1.5466   0.05938   0.05296  -0.0630   0.1122   1.0000
  15.000   1.5447   0.06223   0.05584  -0.0622   0.1085   1.0000
  15.250   1.5400   0.06543   0.05906  -0.0613   0.1051   1.0000
  15.500   1.5428   0.06786   0.06155  -0.0607   0.1029   1.0000
  15.750   1.5446   0.07041   0.06418  -0.0602   0.1010   1.0000
  16.000   1.5457   0.07308   0.06690  -0.0598   0.0990   1.0000
  16.250   1.5442   0.07607   0.06994  -0.0593   0.0972   1.0000
  16.500   1.5417   0.07919   0.07308  -0.0589   0.0951   1.0000
  16.750   1.5396   0.08230   0.07623  -0.0587   0.0930   1.0000
  17.000   1.5442   0.08465   0.07867  -0.0585   0.0917   1.0000
  17.250   1.5470   0.08727   0.08137  -0.0585   0.0900   1.0000
  17.500   1.5495   0.08988   0.08405  -0.0584   0.0886   1.0000
  17.750   1.5495   0.09286   0.08707  -0.0585   0.0869   1.0000
  18.000   1.5499   0.09575   0.09000  -0.0585   0.0856   1.0000
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