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GOE 404 AIRFOIL (goe404-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 404 AIRFOIL (goe404-il)
Reynolds number: 200,000
Max Cl/Cd: 68.76 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe404-il-200000.txt
Download as CSV file: xf-goe404-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 404 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  -0.2308   0.09994   0.09642  -0.0335   1.0000   0.0683
  -8.500  -0.2362   0.09831   0.09487  -0.0321   1.0000   0.0694
  -8.250  -0.2508   0.09734   0.09400  -0.0293   1.0000   0.0704
  -7.750  -0.2235   0.08717   0.08384  -0.0467   0.9840   0.0732
  -7.500  -0.1930   0.08351   0.08018  -0.0495   0.9799   0.0741
  -7.250  -0.1678   0.07979   0.07646  -0.0541   0.9705   0.0755
  -7.000  -0.1464   0.07570   0.07236  -0.0605   0.9571   0.0776
  -6.750  -0.1318   0.06655   0.06299  -0.0823   0.9359   0.0810
  -6.500  -0.1154   0.06415   0.06062  -0.0805   0.9212   0.0815
  -6.250  -0.1002   0.06189   0.05835  -0.0796   0.9052   0.0823
  -6.000  -0.0855   0.05962   0.05604  -0.0794   0.8886   0.0836
  -5.750  -0.0690   0.05350   0.04928  -0.0909   0.8692   0.0900
  -5.500  -0.0534   0.05037   0.04622  -0.0896   0.8551   0.0906
  -5.250  -0.0362   0.04813   0.04396  -0.0887   0.8413   0.0913
  -5.000  -0.0240   0.03587   0.03073  -0.0935   0.8284   0.0728
  -4.750  -0.0024   0.03458   0.02944  -0.0929   0.8142   0.0735
  -4.500   0.0185   0.03131   0.02587  -0.0927   0.8018   0.0702
  -4.250   0.0393   0.02735   0.02137  -0.0924   0.7895   0.0701
  -4.000   0.0612   0.02387   0.01728  -0.0918   0.7771   0.0707
  -3.750   0.0852   0.02110   0.01373  -0.0909   0.7663   0.0726
  -3.500   0.1110   0.02043   0.01307  -0.0905   0.7533   0.0743
  -3.250   0.1373   0.01996   0.01249  -0.0899   0.7405   0.0768
  -3.000   0.1639   0.01898   0.01110  -0.0892   0.7290   0.0815
  -2.750   0.1903   0.01877   0.01094  -0.0887   0.7157   0.0850
  -2.500   0.2170   0.01804   0.00992  -0.0881   0.7035   0.0911
  -2.250   0.2439   0.01783   0.00965  -0.0876   0.6920   0.0965
  -2.000   0.2703   0.01738   0.00912  -0.0871   0.6784   0.1038
  -1.750   0.2973   0.01729   0.00889  -0.0865   0.6655   0.1112
  -1.500   0.3238   0.01685   0.00838  -0.0861   0.6529   0.1175
  -1.250   0.3504   0.01672   0.00817  -0.0855   0.6382   0.1241
  -1.000   0.3769   0.01634   0.00775  -0.0851   0.6241   0.1303
  -0.750   0.4036   0.01627   0.00760  -0.0846   0.6107   0.1372
  -0.500   0.4305   0.01607   0.00725  -0.0840   0.5969   0.1425
  -0.250   0.4569   0.01572   0.00693  -0.0836   0.5824   0.1469
   0.000   0.4836   0.01558   0.00672  -0.0831   0.5690   0.1513
   0.250   0.5104   0.01547   0.00647  -0.0825   0.5567   0.1551
   0.500   0.5370   0.01529   0.00626  -0.0820   0.5436   0.1588
   0.750   0.5633   0.01510   0.00609  -0.0816   0.5320   0.1640
   1.000   0.5900   0.01506   0.00597  -0.0811   0.5221   0.1695
   1.500   0.6432   0.01496   0.00584  -0.0803   0.5037   0.1841
   1.750   0.6696   0.01492   0.00586  -0.0799   0.4944   0.1957
   2.000   0.6960   0.01488   0.00580  -0.0794   0.4862   0.2162
   2.250   0.7393   0.01303   0.00593  -0.0824   0.4763   1.0000
   2.500   0.7653   0.01328   0.00596  -0.0818   0.4689   1.0000
   2.750   0.7911   0.01353   0.00611  -0.0812   0.4617   1.0000
   3.000   0.8169   0.01375   0.00624  -0.0807   0.4546   1.0000
   3.500   0.8690   0.01431   0.00662  -0.0798   0.4425   1.0000
   3.750   0.8951   0.01457   0.00682  -0.0793   0.4370   1.0000
   4.000   0.9217   0.01490   0.00703  -0.0790   0.4319   1.0000
   4.250   0.9473   0.01517   0.00729  -0.0785   0.4260   1.0000
   4.500   0.9727   0.01541   0.00750  -0.0780   0.4198   1.0000
   4.750   0.9989   0.01571   0.00772  -0.0776   0.4147   1.0000
   5.000   1.0249   0.01605   0.00802  -0.0773   0.4097   1.0000
   5.250   1.0498   0.01628   0.00829  -0.0767   0.4038   1.0000
   5.500   1.0754   0.01655   0.00852  -0.0762   0.3986   1.0000
   5.750   1.1023   0.01697   0.00882  -0.0760   0.3940   1.0000
   6.000   1.1263   0.01720   0.00916  -0.0754   0.3890   1.0000
   6.250   1.1511   0.01746   0.00945  -0.0748   0.3835   1.0000
   6.500   1.1765   0.01775   0.00967  -0.0744   0.3784   1.0000
   6.750   1.2011   0.01808   0.01002  -0.0738   0.3730   1.0000
   7.000   1.2243   0.01830   0.01032  -0.0730   0.3666   1.0000
   7.250   1.2487   0.01855   0.01051  -0.0724   0.3606   1.0000
   7.500   1.2717   0.01884   0.01084  -0.0716   0.3542   1.0000
   7.750   1.2938   0.01903   0.01110  -0.0707   0.3467   1.0000
   8.000   1.3170   0.01932   0.01130  -0.0699   0.3397   1.0000
   8.250   1.3369   0.01951   0.01162  -0.0686   0.3312   1.0000
   8.500   1.3587   0.01980   0.01182  -0.0677   0.3235   1.0000
   8.750   1.3773   0.02003   0.01221  -0.0663   0.3141   1.0000
   9.000   1.3964   0.02036   0.01249  -0.0649   0.3052   1.0000
   9.250   1.4134   0.02067   0.01288  -0.0633   0.2939   1.0000
   9.500   1.4293   0.02108   0.01332  -0.0615   0.2819   1.0000
   9.750   1.4434   0.02157   0.01379  -0.0596   0.2698   1.0000
  10.000   1.4542   0.02215   0.01432  -0.0571   0.2586   1.0000
  10.250   1.4659   0.02279   0.01499  -0.0549   0.2472   1.0000
  10.500   1.4766   0.02356   0.01575  -0.0527   0.2378   1.0000
  10.750   1.4862   0.02444   0.01659  -0.0506   0.2297   1.0000
  11.000   1.4974   0.02533   0.01751  -0.0488   0.2224   1.0000
  11.250   1.5065   0.02635   0.01850  -0.0469   0.2159   1.0000
  11.500   1.5161   0.02743   0.01959  -0.0452   0.2100   1.0000
  11.750   1.5256   0.02854   0.02074  -0.0436   0.2042   1.0000
  12.000   1.5334   0.02983   0.02197  -0.0420   0.1998   1.0000
  12.250   1.5434   0.03104   0.02325  -0.0406   0.1956   1.0000
  12.500   1.5523   0.03234   0.02462  -0.0393   0.1913   1.0000
  12.750   1.5602   0.03375   0.02603  -0.0380   0.1875   1.0000
  13.000   1.5694   0.03515   0.02738  -0.0368   0.1839   1.0000
  13.250   1.5771   0.03666   0.02903  -0.0358   0.1805   1.0000
  13.500   1.5840   0.03826   0.03071  -0.0348   0.1769   1.0000
  13.750   1.5910   0.03988   0.03233  -0.0338   0.1734   1.0000
  14.000   1.6008   0.04133   0.03374  -0.0328   0.1697   1.0000
  14.250   1.6034   0.04340   0.03598  -0.0320   0.1665   1.0000
  14.500   1.6066   0.04545   0.03813  -0.0314   0.1629   1.0000
  14.750   1.6114   0.04736   0.04004  -0.0306   0.1591   1.0000
  15.000   1.6170   0.04924   0.04194  -0.0298   0.1553   1.0000
  15.250   1.6130   0.05212   0.04502  -0.0296   0.1517   1.0000
  15.500   1.6118   0.05478   0.04776  -0.0293   0.1477   1.0000
  15.750   1.6202   0.05635   0.04919  -0.0284   0.1430   1.0000
  16.000   1.6084   0.06040   0.05352  -0.0289   0.1396   1.0000
  16.250   1.6026   0.06387   0.05711  -0.0293   0.1353   1.0000
  16.500   1.6040   0.06637   0.05956  -0.0291   0.1312   1.0000
  16.750   1.5951   0.07040   0.06376  -0.0297   0.1273   1.0000
  17.000   1.5874   0.07439   0.06788  -0.0305   0.1233   1.0000
  17.250   1.5865   0.07742   0.07090  -0.0309   0.1200   1.0000
  17.500   1.5847   0.08059   0.07413  -0.0311   0.1168   1.0000
  17.750   1.5756   0.08503   0.07874  -0.0323   0.1138   1.0000
  18.000   1.5727   0.08855   0.08234  -0.0331   0.1112   1.0000
  18.250   1.5743   0.09135   0.08516  -0.0336   0.1090   1.0000
  18.500   1.5815   0.09316   0.08692  -0.0333   0.1068   1.0000
  18.750   1.5701   0.09817   0.09215  -0.0350   0.1050   1.0000
  19.000   1.5622   0.10265   0.09678  -0.0365   0.1032   1.0000
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