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GOE 621 AIRFOIL (goe621-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 621 AIRFOIL (goe621-il)
Reynolds number: 100,000
Max Cl/Cd: 51.15 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe621-il-100000.txt
Download as CSV file: xf-goe621-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 621 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2160   0.10282   0.09818  -0.0538   0.9659   0.1527
  -8.000  -0.2080   0.10001   0.09537  -0.0573   0.9582   0.1585
  -7.750  -0.2500   0.09762   0.09307  -0.0648   0.9442   0.1629
  -7.500  -0.1911   0.09349   0.08887  -0.0631   0.9441   0.1668
  -7.250  -0.1713   0.09047   0.08583  -0.0673   0.9396   0.1744
  -7.000  -0.2196   0.08775   0.08318  -0.0738   0.9235   0.1795
  -6.750  -0.1951   0.08583   0.08127  -0.0686   0.9187   0.1817
  -6.500  -0.1782   0.08362   0.07906  -0.0681   0.9123   0.1855
  -6.000  -0.3081   0.04838   0.04183  -0.0898   0.8847   0.1037
  -5.750  -0.2965   0.04568   0.03889  -0.0889   0.8788   0.1032
  -5.500  -0.2721   0.04267   0.03539  -0.0899   0.8748   0.1034
  -5.250  -0.2539   0.04051   0.03289  -0.0895   0.8699   0.1048
  -5.000  -0.2435   0.03954   0.03188  -0.0874   0.8629   0.1065
  -4.750  -0.2166   0.03824   0.03040  -0.0878   0.8590   0.1086
  -4.500  -0.1814   0.03667   0.02849  -0.0893   0.8561   0.1110
  -4.250  -0.1768   0.03621   0.02782  -0.0859   0.8486   0.1127
  -4.000  -0.1532   0.03545   0.02667  -0.0853   0.8437   0.1163
  -3.750  -0.1206   0.03441   0.02565  -0.0863   0.8403   0.1216
  -3.500  -0.0799   0.03356   0.02458  -0.0882   0.8379   0.1294
  -3.250  -0.0844   0.03374   0.02467  -0.0834   0.8290   0.1323
  -3.000  -0.0559   0.03325   0.02427  -0.0837   0.8249   0.1419
  -2.750  -0.0184   0.03255   0.02360  -0.0851   0.8219   0.1573
  -2.500  -0.0121   0.03271   0.02381  -0.0821   0.8145   0.1681
  -2.250   0.0107   0.03255   0.02372  -0.0814   0.8092   0.1907
  -2.000   0.0469   0.03216   0.02347  -0.0825   0.8054   0.2245
  -1.750   0.0603   0.03246   0.02381  -0.0805   0.7981   0.2489
  -1.500   0.0898   0.03226   0.02373  -0.0804   0.7906   0.2831
  -1.250   0.1466   0.03131   0.02295  -0.0838   0.7863   0.3387
  -1.000   0.1516   0.03168   0.02344  -0.0801   0.7738   0.3649
  -0.750   0.2015   0.03080   0.02267  -0.0824   0.7698   0.4185
  -0.500   0.2037   0.03151   0.02345  -0.0787   0.7590   0.4402
  -0.250   0.2434   0.03093   0.02297  -0.0798   0.7544   0.4795
   0.000   0.2936   0.02991   0.02204  -0.0823   0.7517   0.5235
   0.250   0.2912   0.03086   0.02306  -0.0781   0.7395   0.5457
   0.500   0.3406   0.02978   0.02218  -0.0805   0.7360   0.5979
   0.750   0.4760   0.02700   0.02048  -0.0978   0.7364   1.0000
   1.000   0.5371   0.02594   0.01911  -0.1024   0.7343   1.0000
   1.250   0.5326   0.02701   0.02007  -0.0974   0.7211   1.0000
   1.500   0.5888   0.02593   0.01880  -0.1009   0.7182   1.0000
   1.750   0.6392   0.02506   0.01777  -0.1035   0.7144   1.0000
   2.000   0.6465   0.02562   0.01827  -0.1000   0.7021   1.0000
   2.250   0.7034   0.02442   0.01693  -0.1034   0.6987   1.0000
   2.500   0.7111   0.02495   0.01742  -0.0999   0.6859   1.0000
   2.750   0.7652   0.02384   0.01618  -0.1029   0.6812   1.0000
   3.000   0.7789   0.02410   0.01641  -0.1001   0.6686   1.0000
   3.250   0.8330   0.02298   0.01515  -0.1032   0.6627   1.0000
   3.500   0.8472   0.02316   0.01532  -0.1004   0.6490   1.0000
   3.750   0.8772   0.02284   0.01493  -0.0999   0.6378   1.0000
   4.000   0.9187   0.02213   0.01409  -0.1012   0.6274   1.0000
   4.250   0.9385   0.02206   0.01400  -0.0992   0.6124   1.0000
   4.500   0.9621   0.02190   0.01377  -0.0978   0.5973   1.0000
   4.750   0.9871   0.02172   0.01352  -0.0966   0.5818   1.0000
   5.000   1.0116   0.02158   0.01328  -0.0954   0.5658   1.0000
   5.250   1.0350   0.02152   0.01312  -0.0940   0.5493   1.0000
   5.500   1.0574   0.02155   0.01304  -0.0926   0.5329   1.0000
   5.750   1.0793   0.02165   0.01304  -0.0912   0.5168   1.0000
   6.000   1.1015   0.02182   0.01308  -0.0899   0.5015   1.0000
   6.250   1.1245   0.02203   0.01314  -0.0888   0.4869   1.0000
   6.500   1.1442   0.02237   0.01338  -0.0872   0.4726   1.0000
   6.750   1.1607   0.02283   0.01378  -0.0852   0.4588   1.0000
   7.000   1.1794   0.02331   0.01418  -0.0836   0.4461   1.0000
   7.250   1.2025   0.02376   0.01452  -0.0828   0.4343   1.0000
   7.500   1.2229   0.02428   0.01494  -0.0815   0.4228   1.0000
   7.750   1.2390   0.02492   0.01558  -0.0797   0.4118   1.0000
   8.000   1.2646   0.02549   0.01601  -0.0794   0.4016   1.0000
   8.250   1.2799   0.02617   0.01671  -0.0774   0.3916   1.0000
   8.500   1.3011   0.02687   0.01736  -0.0765   0.3822   1.0000
   8.750   1.3215   0.02755   0.01800  -0.0755   0.3727   1.0000
   9.000   1.3387   0.02837   0.01885  -0.0740   0.3640   1.0000
   9.250   1.3612   0.02908   0.01948  -0.0733   0.3548   1.0000
   9.500   1.3741   0.02998   0.02045  -0.0712   0.3464   1.0000
   9.750   1.3968   0.03072   0.02113  -0.0707   0.3375   1.0000
  10.000   1.4074   0.03170   0.02218  -0.0683   0.3296   1.0000
  10.250   1.4252   0.03252   0.02299  -0.0670   0.3214   1.0000
  10.500   1.4419   0.03356   0.02406  -0.0656   0.3140   1.0000
  10.750   1.4475   0.03452   0.02514  -0.0625   0.3067   1.0000
  11.000   1.4787   0.03550   0.02600  -0.0635   0.2988   1.0000
  11.250   1.4703   0.03666   0.02738  -0.0584   0.2927   1.0000
  11.500   1.4967   0.03745   0.02809  -0.0585   0.2854   1.0000
  11.750   1.4998   0.03877   0.02954  -0.0555   0.2795   1.0000
  12.000   1.4977   0.04006   0.03100  -0.0519   0.2739   1.0000
  12.250   1.5357   0.04080   0.03159  -0.0536   0.2675   1.0000
  12.500   1.5276   0.04250   0.03352  -0.0494   0.2632   1.0000
  12.750   1.5195   0.04424   0.03547  -0.0456   0.2588   1.0000
  13.000   1.5320   0.04540   0.03669  -0.0442   0.2541   1.0000
  13.250   1.5640   0.04641   0.03764  -0.0451   0.2492   1.0000
  13.500   1.5381   0.04891   0.04045  -0.0400   0.2460   1.0000
  13.750   1.5234   0.05134   0.04310  -0.0365   0.2425   1.0000
  14.000   1.5262   0.05310   0.04496  -0.0348   0.2389   1.0000
  14.250   1.5729   0.05329   0.04504  -0.0365   0.2348   1.0000
  14.500   1.5469   0.05673   0.04876  -0.0328   0.2327   1.0000
  14.750   1.4948   0.06205   0.05443  -0.0285   0.2309   1.0000
  15.000   1.3990   0.07245   0.06522  -0.0255   0.2295   1.0000
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