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GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 584 AIRFOIL (goe584-il)
Reynolds number: 100,000
Max Cl/Cd: 51.64 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe584-il-100000.txt
Download as CSV file: xf-goe584-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 584 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2712   0.11075   0.10575  -0.0427   1.0000   0.1157
  -9.750  -0.3050   0.11135   0.10654  -0.0447   1.0000   0.1174
  -9.500  -0.3377   0.11189   0.10728  -0.0423   1.0000   0.1176
  -9.250  -0.2958   0.10481   0.10013  -0.0387   1.0000   0.1204
  -9.000  -0.3083   0.10431   0.09973  -0.0340   1.0000   0.1217
  -8.750  -0.3256   0.10416   0.09969  -0.0296   1.0000   0.1231
  -8.500  -0.3428   0.10382   0.09945  -0.0261   1.0000   0.1245
  -8.250  -0.3432   0.10080   0.09644  -0.0370   0.9898   0.1319
  -8.000  -0.3212   0.09533   0.09096  -0.0410   0.9843   0.1353
  -7.750  -0.2890   0.09170   0.08729  -0.0427   0.9793   0.1413
  -7.250  -0.2700   0.08348   0.07905  -0.0564   0.9584   0.1521
  -7.000  -0.2442   0.08028   0.07582  -0.0593   0.9516   0.1601
  -6.750  -0.2317   0.07517   0.07065  -0.0688   0.9409   0.1682
  -6.500  -0.2095   0.07262   0.06808  -0.0688   0.9331   0.1743
  -6.250  -0.1920   0.06768   0.06302  -0.0782   0.9246   0.1852
  -6.000  -0.1716   0.06554   0.06088  -0.0776   0.9162   0.1924
  -5.750  -0.1479   0.06155   0.05678  -0.0833   0.9093   0.2045
  -5.500  -0.1397   0.05892   0.05398  -0.0868   0.8979   0.2187
  -5.250  -0.1079   0.05608   0.05117  -0.0872   0.8933   0.2252
  -4.500  -0.0586   0.04011   0.03361  -0.0979   0.8655   0.1531
  -4.250  -0.0318   0.03617   0.02907  -0.0989   0.8593   0.1396
  -4.000   0.0035   0.03323   0.02512  -0.1001   0.8554   0.1330
  -3.750   0.0144   0.03218   0.02389  -0.0976   0.8443   0.1326
  -3.500   0.0498   0.03050   0.02185  -0.0987   0.8400   0.1329
  -3.250   0.0663   0.02949   0.02076  -0.0972   0.8312   0.1349
  -3.000   0.0967   0.02845   0.01959  -0.0975   0.8253   0.1371
  -2.750   0.1342   0.02727   0.01823  -0.0987   0.8215   0.1391
  -2.500   0.1474   0.02716   0.01802  -0.0963   0.8113   0.1408
  -2.250   0.1819   0.02638   0.01707  -0.0970   0.8066   0.1452
  -2.000   0.2075   0.02604   0.01658  -0.0963   0.8000   0.1493
  -1.750   0.2297   0.02563   0.01625  -0.0954   0.7921   0.1537
  -1.500   0.2652   0.02493   0.01553  -0.0961   0.7880   0.1606
  -1.250   0.2804   0.02506   0.01565  -0.0941   0.7788   0.1668
  -1.000   0.3100   0.02460   0.01528  -0.0940   0.7731   0.1804
  -0.750   0.3442   0.02381   0.01465  -0.0943   0.7695   0.2046
  -0.500   0.4504   0.02040   0.01388  -0.1083   0.7656   1.0000
  -0.250   0.4683   0.02078   0.01405  -0.1066   0.7573   1.0000
   0.000   0.4997   0.02067   0.01370  -0.1064   0.7526   1.0000
   0.250   0.5084   0.02143   0.01438  -0.1035   0.7423   1.0000
   0.500   0.5388   0.02133   0.01410  -0.1033   0.7370   1.0000
   0.750   0.5515   0.02198   0.01467  -0.1009   0.7278   1.0000
   1.000   0.5791   0.02199   0.01454  -0.1003   0.7216   1.0000
   1.250   0.6010   0.02228   0.01474  -0.0990   0.7146   1.0000
   1.500   0.6206   0.02265   0.01503  -0.0975   0.7064   1.0000
   1.750   0.6548   0.02239   0.01464  -0.0977   0.7020   1.0000
   2.000   0.6642   0.02324   0.01548  -0.0950   0.6914   1.0000
   2.250   0.6973   0.02300   0.01514  -0.0951   0.6864   1.0000
   2.500   0.7105   0.02371   0.01584  -0.0928   0.6767   1.0000
   2.750   0.7416   0.02355   0.01560  -0.0927   0.6709   1.0000
   3.000   0.7602   0.02401   0.01605  -0.0910   0.6623   1.0000
   3.250   0.7876   0.02401   0.01600  -0.0905   0.6552   1.0000
   3.500   0.8143   0.02408   0.01603  -0.0898   0.6482   1.0000
   3.750   0.8357   0.02435   0.01630  -0.0885   0.6393   1.0000
   4.000   0.8743   0.02384   0.01569  -0.0892   0.6346   1.0000
   4.250   0.8852   0.02459   0.01652  -0.0867   0.6230   1.0000
   4.500   0.9244   0.02405   0.01589  -0.0875   0.6180   1.0000
   4.750   0.9359   0.02476   0.01668  -0.0850   0.6063   1.0000
   5.000   0.9668   0.02461   0.01648  -0.0848   0.5991   1.0000
   5.250   0.9880   0.02483   0.01674  -0.0835   0.5889   1.0000
   5.500   1.0119   0.02499   0.01691  -0.0825   0.5797   1.0000
   5.750   1.0421   0.02477   0.01667  -0.0822   0.5709   1.0000
   6.000   1.0604   0.02514   0.01710  -0.0804   0.5599   1.0000
   6.250   1.1001   0.02448   0.01633  -0.0813   0.5521   1.0000
   6.500   1.1161   0.02475   0.01667  -0.0792   0.5391   1.0000
   6.750   1.1375   0.02477   0.01672  -0.0777   0.5266   1.0000
   7.000   1.1651   0.02454   0.01645  -0.0770   0.5152   1.0000
   7.250   1.1941   0.02430   0.01617  -0.0766   0.5039   1.0000
   7.500   1.2105   0.02462   0.01657  -0.0745   0.4910   1.0000
   7.750   1.2306   0.02481   0.01680  -0.0730   0.4787   1.0000
   8.000   1.2545   0.02487   0.01684  -0.0720   0.4666   1.0000
   8.250   1.2816   0.02482   0.01673  -0.0714   0.4544   1.0000
   8.500   1.2965   0.02520   0.01718  -0.0692   0.4408   1.0000
   8.750   1.3122   0.02557   0.01760  -0.0672   0.4272   1.0000
   9.000   1.3288   0.02593   0.01798  -0.0652   0.4133   1.0000
   9.250   1.3452   0.02630   0.01837  -0.0633   0.3993   1.0000
   9.500   1.3610   0.02674   0.01879  -0.0613   0.3850   1.0000
   9.750   1.3764   0.02725   0.01928  -0.0593   0.3706   1.0000
  10.000   1.3909   0.02785   0.01983  -0.0572   0.3560   1.0000
  10.250   1.4038   0.02851   0.02047  -0.0550   0.3413   1.0000
  10.500   1.4146   0.02924   0.02113  -0.0525   0.3264   1.0000
  10.750   1.4235   0.02999   0.02180  -0.0497   0.3119   1.0000
  11.000   1.4225   0.03094   0.02281  -0.0458   0.2989   1.0000
  11.250   1.4241   0.03198   0.02388  -0.0424   0.2861   1.0000
  11.500   1.4274   0.03305   0.02497  -0.0396   0.2739   1.0000
  11.750   1.4331   0.03409   0.02595  -0.0371   0.2623   1.0000
  12.000   1.4365   0.03523   0.02709  -0.0347   0.2515   1.0000
  12.250   1.4350   0.03671   0.02867  -0.0320   0.2415   1.0000
  12.500   1.4404   0.03795   0.02989  -0.0301   0.2319   1.0000
  12.750   1.4396   0.03948   0.03149  -0.0279   0.2227   1.0000
  13.000   1.4386   0.04118   0.03327  -0.0259   0.2140   1.0000
  13.250   1.4435   0.04256   0.03459  -0.0244   0.2052   1.0000
  13.500   1.4383   0.04474   0.03698  -0.0226   0.1977   1.0000
  13.750   1.4432   0.04626   0.03841  -0.0214   0.1894   1.0000
  14.000   1.4348   0.04884   0.04123  -0.0199   0.1820   1.0000
  14.250   1.4348   0.05083   0.04319  -0.0188   0.1739   1.0000
  14.500   1.4259   0.05368   0.04622  -0.0179   0.1660   1.0000
  14.750   1.4195   0.05645   0.04906  -0.0171   0.1577   1.0000
  15.000   1.4122   0.05937   0.05197  -0.0166   0.1486   1.0000
  15.250   1.3979   0.06336   0.05614  -0.0165   0.1393   1.0000
  15.500   1.3850   0.06739   0.06018  -0.0166   0.1290   1.0000
  15.750   1.3717   0.07165   0.06440  -0.0168   0.1181   1.0000
  16.000   1.3614   0.07573   0.06837  -0.0171   0.1075   1.0000
  16.250   1.3489   0.08048   0.07324  -0.0179   0.0990   1.0000
  16.500   1.3419   0.08456   0.07736  -0.0184   0.0918   1.0000
  16.750   1.3403   0.08782   0.08052  -0.0188   0.0857   1.0000
  17.000   1.3334   0.09221   0.08509  -0.0197   0.0812   1.0000
  17.250   1.3321   0.09567   0.08859  -0.0204   0.0770   1.0000
  17.500   1.3363   0.09831   0.09121  -0.0204   0.0734   1.0000
  17.750   1.3286   0.10306   0.09621  -0.0218   0.0709   1.0000
  18.000   1.3264   0.10688   0.10014  -0.0229   0.0683   1.0000
  18.250   1.3422   0.10760   0.10066  -0.0221   0.0650   1.0000
  18.500   1.3287   0.11348   0.10684  -0.0245   0.0638   1.0000
  18.750   1.3152   0.11948   0.11311  -0.0271   0.0628   1.0000
  19.000   1.2994   0.12608   0.11995  -0.0302   0.0619   1.0000
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