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GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 802 B AIRFOIL (goe802b-il)
Reynolds number: 500,000
Max Cl/Cd: 104.6 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe802b-il-500000.txt
Download as CSV file: xf-goe802b-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 802 B 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3096   0.11217   0.10988  -0.0258   1.0000   0.0207
  -9.750  -0.3062   0.10918   0.10691  -0.0288   1.0000   0.0207
  -9.500  -0.3033   0.10613   0.10387  -0.0318   1.0000   0.0208
  -9.250  -0.2984   0.10246   0.10023  -0.0331   1.0000   0.0209
  -9.000  -0.2890   0.09883   0.09662  -0.0322   1.0000   0.0210
  -8.750  -0.2838   0.09617   0.09399  -0.0321   1.0000   0.0212
  -8.500  -0.2810   0.09387   0.09173  -0.0321   0.9984   0.0213
  -8.250  -0.2629   0.09026   0.08812  -0.0363   0.9941   0.0217
  -8.000  -0.2456   0.08676   0.08461  -0.0407   0.9868   0.0222
  -7.750  -0.2271   0.08303   0.08088  -0.0459   0.9789   0.0229
  -7.500  -0.2095   0.07926   0.07710  -0.0512   0.9684   0.0237
  -7.250  -0.1876   0.07505   0.07283  -0.0602   0.9545   0.0248
  -7.000  -0.1648   0.07063   0.06831  -0.0697   0.9415   0.0249
  -6.750  -0.1451   0.06674   0.06429  -0.0745   0.9317   0.0250
  -6.500  -0.1361   0.06297   0.06054  -0.0740   0.9225   0.0252
  -6.250  -0.1243   0.06033   0.05786  -0.0735   0.9144   0.0254
  -6.000  -0.1078   0.05768   0.05519  -0.0747   0.9054   0.0257
  -5.750  -0.0891   0.05500   0.05242  -0.0765   0.8974   0.0261
  -5.500  -0.0674   0.05216   0.04951  -0.0788   0.8888   0.0267
  -5.250  -0.0447   0.04929   0.04653  -0.0810   0.8801   0.0275
  -5.000  -0.0180   0.04623   0.04333  -0.0836   0.8707   0.0289
  -4.750   0.0221   0.04314   0.03973  -0.0877   0.8616   0.0298
  -4.500   0.0393   0.03923   0.03585  -0.0884   0.8526   0.0302
  -4.250   0.0604   0.03708   0.03363  -0.0888   0.8441   0.0305
  -4.000   0.0840   0.03511   0.03159  -0.0895   0.8354   0.0310
  -3.750   0.1088   0.03329   0.02963  -0.0900   0.8261   0.0319
  -3.500   0.1356   0.03141   0.02759  -0.0906   0.8165   0.0334
  -3.250   0.1691   0.02996   0.02560  -0.0907   0.8073   0.0354
  -3.000   0.1924   0.02736   0.02300  -0.0913   0.7973   0.0359
  -2.750   0.2173   0.02580   0.02134  -0.0915   0.7877   0.0366
  -2.500   0.2439   0.02449   0.01992  -0.0918   0.7765   0.0378
  -2.250   0.2759   0.02515   0.02012  -0.0910   0.7656   0.0412
  -2.000   0.3005   0.02223   0.01714  -0.0916   0.7538   0.0420
  -1.750   0.3266   0.02092   0.01577  -0.0919   0.7404   0.0430
  -1.500   0.3537   0.02010   0.01480  -0.0919   0.7260   0.0453
  -1.250   0.3826   0.01959   0.01398  -0.0915   0.7111   0.0483
  -1.000   0.4091   0.01839   0.01269  -0.0917   0.6952   0.0494
  -0.750   0.4364   0.01774   0.01190  -0.0916   0.6787   0.0519
  -0.500   0.4650   0.01747   0.01134  -0.0912   0.6614   0.0549
  -0.250   0.4917   0.01644   0.01021  -0.0913   0.6438   0.0563
   0.000   0.5203   0.01716   0.01067  -0.0908   0.6265   0.0605
   0.250   0.5477   0.01608   0.00943  -0.0908   0.6106   0.0611
   0.500   0.5748   0.01508   0.00836  -0.0908   0.5956   0.0619
   0.750   0.6022   0.01456   0.00774  -0.0908   0.5813   0.0633
   1.000   0.6300   0.01177   0.00449  -0.0899   0.5701   0.0410
   1.250   0.6558   0.01095   0.00363  -0.0897   0.5572   0.0415
   1.500   0.6831   0.01083   0.00348  -0.0897   0.5444   0.0431
   1.750   0.7104   0.01085   0.00347  -0.0895   0.5319   0.0451
   2.000   0.7371   0.01083   0.00340  -0.0894   0.5187   0.0476
   2.250   0.7650   0.01115   0.00368  -0.0893   0.5041   0.0510
   2.500   0.7923   0.01136   0.00385  -0.0891   0.4893   0.0561
   2.750   0.8198   0.01169   0.00409  -0.0890   0.4761   0.0672
   3.000   0.8472   0.01208   0.00438  -0.0888   0.4631   0.0792
   3.250   0.8741   0.01217   0.00440  -0.0888   0.4503   0.0919
   3.500   0.9007   0.01206   0.00428  -0.0887   0.4377   0.0974
   3.750   0.9270   0.01201   0.00422  -0.0886   0.4257   0.1032
   4.000   0.9533   0.01200   0.00419  -0.0884   0.4141   0.1089
   4.250   0.9799   0.01206   0.00425  -0.0883   0.4042   0.1115
   4.500   1.0058   0.01220   0.00434  -0.0881   0.3940   0.1154
   4.750   1.0323   0.01198   0.00423  -0.0881   0.3835   0.1220
   5.000   1.0583   0.01199   0.00425  -0.0880   0.3729   0.1271
   5.250   1.0844   0.01206   0.00433  -0.0879   0.3629   0.1307
   5.500   1.1106   0.01217   0.00443  -0.0878   0.3542   0.1339
   5.750   1.1365   0.01233   0.00459  -0.0876   0.3455   0.1373
   6.000   1.1623   0.01247   0.00480  -0.0875   0.3375   0.1833
   6.250   1.1877   0.01266   0.00503  -0.0873   0.3274   0.2093
   6.500   1.2112   0.01191   0.00543  -0.0871   0.3181   0.7830
   6.750   1.2340   0.01181   0.00565  -0.0861   0.3087   1.0000
   7.000   1.2594   0.01204   0.00589  -0.0858   0.2994   1.0000
   7.250   1.2836   0.01235   0.00615  -0.0854   0.2868   1.0000
   7.500   1.3074   0.01269   0.00644  -0.0850   0.2706   1.0000
   7.750   1.3308   0.01306   0.00674  -0.0845   0.2508   1.0000
   8.000   1.3531   0.01352   0.00709  -0.0838   0.2283   1.0000
   8.250   1.3738   0.01411   0.00753  -0.0830   0.2049   1.0000
   8.500   1.3942   0.01470   0.00803  -0.0821   0.1859   1.0000
   8.750   1.4143   0.01529   0.00855  -0.0811   0.1713   1.0000
   9.250   1.4543   0.01639   0.00957  -0.0792   0.1491   1.0000
   9.500   1.4737   0.01695   0.01011  -0.0781   0.1406   1.0000
   9.750   1.4931   0.01747   0.01063  -0.0771   0.1320   1.0000
  10.000   1.5116   0.01803   0.01119  -0.0759   0.1239   1.0000
  10.250   1.5282   0.01866   0.01178  -0.0744   0.1141   1.0000
  10.500   1.5438   0.01925   0.01237  -0.0728   0.1044   1.0000
  10.750   1.5563   0.01998   0.01306  -0.0707   0.0935   1.0000
  11.000   1.5671   0.02085   0.01387  -0.0685   0.0816   1.0000
  11.250   1.5761   0.02187   0.01482  -0.0663   0.0706   1.0000
  11.500   1.5844   0.02298   0.01589  -0.0641   0.0626   1.0000
  11.750   1.5944   0.02402   0.01694  -0.0622   0.0560   1.0000
  12.000   1.6026   0.02522   0.01816  -0.0603   0.0490   1.0000
  12.250   1.6068   0.02679   0.01968  -0.0582   0.0361   1.0000
  12.500   1.5991   0.02939   0.02215  -0.0554   0.0220   1.0000
  12.750   1.6009   0.03136   0.02418  -0.0536   0.0197   1.0000
  13.000   1.6052   0.03320   0.02613  -0.0521   0.0187   1.0000
  13.250   1.6084   0.03523   0.02827  -0.0509   0.0180   1.0000
  13.500   1.6096   0.03751   0.03068  -0.0497   0.0174   1.0000
  13.750   1.6089   0.04010   0.03339  -0.0487   0.0169   1.0000
  14.000   1.6060   0.04303   0.03644  -0.0479   0.0165   1.0000
  14.250   1.6006   0.04638   0.03992  -0.0473   0.0161   1.0000
  14.500   1.5932   0.05013   0.04380  -0.0470   0.0158   1.0000
  14.750   1.5830   0.05440   0.04821  -0.0471   0.0155   1.0000
  15.000   1.5759   0.05847   0.05241  -0.0474   0.0153   1.0000
  15.250   1.5694   0.06259   0.05666  -0.0480   0.0152   1.0000
  15.500   1.5610   0.06707   0.06127  -0.0487   0.0150   1.0000
  15.750   1.5515   0.07180   0.06613  -0.0496   0.0149   1.0000
  16.000   1.5408   0.07683   0.07130  -0.0507   0.0147   1.0000
  16.250   1.5291   0.08206   0.07665  -0.0520   0.0146   1.0000
  16.500   1.5169   0.08745   0.08217  -0.0534   0.0144   1.0000
  16.750   1.5048   0.09292   0.08776  -0.0550   0.0143   1.0000
  17.000   1.4921   0.09856   0.09352  -0.0566   0.0141   1.0000
  17.250   1.4796   0.10423   0.09931  -0.0584   0.0140   1.0000
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