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GOE 446 AIRFOIL (goe446-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 446 AIRFOIL (goe446-il)
Reynolds number: 200,000
Max Cl/Cd: 83.75 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe446-il-200000.txt
Download as CSV file: xf-goe446-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 446 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0293   0.09299   0.08923  -0.1034   0.9560   0.0632
  -8.500  -0.0191   0.09030   0.08653  -0.1054   0.9466   0.0653
  -8.250  -0.0280   0.08799   0.08423  -0.1155   0.9317   0.0683
  -8.000  -0.0160   0.08331   0.07955  -0.1190   0.9267   0.0690
  -7.750   0.0099   0.07979   0.07601  -0.1179   0.9254   0.0698
  -7.500   0.0188   0.07768   0.07390  -0.1166   0.9157   0.0706
  -7.250   0.0335   0.07498   0.07118  -0.1180   0.9109   0.0720
  -7.000   0.0391   0.07283   0.06903  -0.1188   0.9011   0.0735
  -6.750   0.0527   0.06958   0.06574  -0.1237   0.8952   0.0764
  -6.500   0.0614   0.06375   0.05975  -0.1391   0.8827   0.0793
  -6.250   0.0783   0.06112   0.05713  -0.1374   0.8797   0.0800
  -6.000   0.0904   0.05933   0.05536  -0.1358   0.8728   0.0810
  -5.750   0.1078   0.05722   0.05321  -0.1362   0.8675   0.0828
  -5.500   0.1441   0.05285   0.04824  -0.1509   0.8612   0.0907
  -5.250   0.1546   0.04873   0.04424  -0.1500   0.8546   0.0916
  -5.000   0.1751   0.04622   0.04173  -0.1501   0.8503   0.0925
  -4.750   0.1979   0.04402   0.03948  -0.1506   0.8458   0.0939
  -4.500   0.2208   0.03189   0.02629  -0.1575   0.8379   0.0694
  -4.250   0.2492   0.02913   0.02329  -0.1585   0.8333   0.0665
  -4.000   0.2736   0.02610   0.01985  -0.1589   0.8269   0.0658
  -3.750   0.2993   0.02326   0.01651  -0.1592   0.8208   0.0648
  -3.500   0.3298   0.02104   0.01381  -0.1598   0.8168   0.0647
  -3.250   0.3570   0.01981   0.01227  -0.1598   0.8119   0.0657
  -3.000   0.3830   0.01893   0.01115  -0.1594   0.8062   0.0672
  -2.750   0.4128   0.01805   0.01007  -0.1596   0.8018   0.0694
  -2.500   0.4435   0.01769   0.00971  -0.1601   0.7980   0.0731
  -2.250   0.4673   0.01746   0.00941  -0.1593   0.7914   0.0774
  -2.000   0.4957   0.01695   0.00889  -0.1594   0.7867   0.0827
  -1.750   0.5271   0.01651   0.00837  -0.1598   0.7829   0.0931
  -1.500   0.5515   0.01642   0.00835  -0.1592   0.7766   0.1100
  -1.250   0.5790   0.01633   0.00827  -0.1592   0.7710   0.1280
  -1.000   0.6099   0.01612   0.00798  -0.1596   0.7667   0.1408
  -0.750   0.6350   0.01617   0.00801  -0.1592   0.7606   0.1506
  -0.500   0.6617   0.01602   0.00792  -0.1590   0.7548   0.1622
  -0.250   0.6921   0.01582   0.00769  -0.1594   0.7504   0.1747
   0.000   0.7175   0.01581   0.00770  -0.1590   0.7442   0.1847
   0.250   0.7440   0.01560   0.00756  -0.1587   0.7379   0.1945
   0.500   0.7750   0.01537   0.00730  -0.1592   0.7331   0.2070
   0.750   0.7988   0.01530   0.00735  -0.1585   0.7258   0.2236
   1.000   0.8266   0.01501   0.00725  -0.1585   0.7197   0.2712
   1.250   0.8538   0.01337   0.00718  -0.1578   0.7151   1.0000
   1.500   0.8762   0.01356   0.00730  -0.1567   0.7070   1.0000
   1.750   0.9057   0.01359   0.00719  -0.1569   0.7011   1.0000
   2.000   0.9307   0.01374   0.00727  -0.1563   0.6936   1.0000
   2.250   0.9578   0.01379   0.00724  -0.1560   0.6862   1.0000
   2.500   0.9850   0.01389   0.00725  -0.1558   0.6791   1.0000
   2.750   1.0101   0.01399   0.00731  -0.1553   0.6707   1.0000
   3.000   1.0385   0.01406   0.00729  -0.1553   0.6640   1.0000
   3.250   1.0621   0.01419   0.00742  -0.1545   0.6548   1.0000
   3.500   1.0901   0.01428   0.00742  -0.1544   0.6475   1.0000
   3.750   1.1137   0.01441   0.00754  -0.1536   0.6378   1.0000
   4.000   1.1398   0.01453   0.00761  -0.1533   0.6295   1.0000
   4.250   1.1646   0.01466   0.00772  -0.1527   0.6204   1.0000
   4.500   1.1895   0.01485   0.00788  -0.1522   0.6118   1.0000
   4.750   1.2152   0.01500   0.00799  -0.1518   0.6033   1.0000
   5.000   1.2390   0.01522   0.00822  -0.1511   0.5944   1.0000
   5.250   1.2652   0.01539   0.00832  -0.1508   0.5864   1.0000
   5.500   1.2875   0.01564   0.00859  -0.1498   0.5769   1.0000
   5.750   1.3147   0.01579   0.00864  -0.1497   0.5687   1.0000
   6.000   1.3342   0.01605   0.00896  -0.1482   0.5583   1.0000
   6.250   1.3581   0.01628   0.00915  -0.1476   0.5493   1.0000
   6.500   1.3794   0.01647   0.00930  -0.1464   0.5382   1.0000
   6.750   1.3976   0.01673   0.00959  -0.1446   0.5265   1.0000
   7.000   1.4199   0.01702   0.00983  -0.1437   0.5174   1.0000
   7.250   1.4408   0.01735   0.01022  -0.1426   0.5097   1.0000
   7.500   1.4654   0.01769   0.01053  -0.1422   0.5030   1.0000
   7.750   1.4839   0.01806   0.01098  -0.1407   0.4951   1.0000
   8.000   1.5063   0.01840   0.01128  -0.1398   0.4869   1.0000
   8.250   1.5208   0.01877   0.01172  -0.1375   0.4767   1.0000
   8.500   1.5360   0.01916   0.01213  -0.1354   0.4662   1.0000
   8.750   1.5514   0.01955   0.01246  -0.1332   0.4555   1.0000
   9.000   1.5594   0.02002   0.01302  -0.1299   0.4451   1.0000
   9.250   1.5717   0.02053   0.01356  -0.1274   0.4348   1.0000
   9.500   1.5838   0.02107   0.01409  -0.1249   0.4245   1.0000
   9.750   1.5921   0.02169   0.01482  -0.1219   0.4139   1.0000
  10.000   1.6011   0.02237   0.01553  -0.1191   0.4027   1.0000
  10.250   1.6080   0.02315   0.01632  -0.1161   0.3902   1.0000
  10.500   1.6128   0.02404   0.01730  -0.1130   0.3767   1.0000
  10.750   1.6171   0.02506   0.01838  -0.1100   0.3621   1.0000
  11.000   1.6197   0.02626   0.01962  -0.1069   0.3452   1.0000
  11.250   1.6202   0.02769   0.02106  -0.1038   0.3246   1.0000
  11.500   1.6171   0.02950   0.02282  -0.1006   0.2988   1.0000
  11.750   1.6093   0.03180   0.02501  -0.0972   0.2705   1.0000
  12.000   1.5983   0.03454   0.02761  -0.0939   0.2434   1.0000
  12.250   1.5874   0.03748   0.03042  -0.0909   0.2214   1.0000
  12.500   1.5804   0.04030   0.03317  -0.0885   0.2027   1.0000
  12.750   1.5745   0.04313   0.03596  -0.0864   0.1866   1.0000
  13.000   1.5695   0.04600   0.03880  -0.0846   0.1721   1.0000
  13.250   1.5643   0.04899   0.04176  -0.0829   0.1577   1.0000
  13.500   1.5591   0.05209   0.04483  -0.0814   0.1438   1.0000
  13.750   1.5540   0.05527   0.04800  -0.0801   0.1302   1.0000
  14.000   1.5469   0.05876   0.05146  -0.0788   0.1146   1.0000
  14.250   1.5380   0.06258   0.05522  -0.0777   0.0977   1.0000
  14.500   1.5285   0.06656   0.05911  -0.0767   0.0758   1.0000
  14.750   1.5144   0.07116   0.06357  -0.0759   0.0562   1.0000
  15.250   1.4948   0.07970   0.07209  -0.0748   0.0455   1.0000
  15.500   1.4862   0.08396   0.07641  -0.0746   0.0432   1.0000
  15.750   1.4778   0.08830   0.08083  -0.0745   0.0415   1.0000
  16.000   1.4725   0.09230   0.08496  -0.0745   0.0402   1.0000
  16.250   1.4665   0.09645   0.08922  -0.0747   0.0391   1.0000
  16.500   1.4599   0.10068   0.09356  -0.0750   0.0381   1.0000
  16.750   1.4527   0.10503   0.09799  -0.0754   0.0373   1.0000
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