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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 50,000
Max Cl/Cd: 38.84 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe499-il-50000.txt
Download as CSV file: xf-goe499-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 499 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3643   0.11024   0.10406  -0.0187   1.0000   0.1608
  -6.750  -0.3817   0.11047   0.10441  -0.0166   1.0000   0.1637
  -6.500  -0.3979   0.11146   0.10552  -0.0181   1.0000   0.1651
  -6.250  -0.3839   0.10516   0.09920  -0.0139   1.0000   0.1699
  -6.000  -0.3861   0.10325   0.09735  -0.0130   1.0000   0.1754
  -5.750  -0.3950   0.10375   0.09794  -0.0176   1.0000   0.1794
  -5.500  -0.3887   0.09872   0.09294  -0.0130   1.0000   0.1833
  -5.250  -0.3859   0.09631   0.09055  -0.0125   1.0000   0.1897
  -5.000  -0.3832   0.09443   0.08872  -0.0167   1.0000   0.1953
  -4.750  -0.3784   0.09113   0.08543  -0.0134   1.0000   0.2038
  -4.500  -0.3718   0.08840   0.08269  -0.0156   1.0000   0.2118
  -4.250  -0.3576   0.08617   0.08045  -0.0213   1.0000   0.2237
  -4.000  -0.3543   0.08267   0.07698  -0.0168   1.0000   0.2302
  -3.750  -0.3397   0.07969   0.07399  -0.0203   1.0000   0.2408
  -3.500  -0.3219   0.07676   0.07103  -0.0241   1.0000   0.2538
  -3.000  -0.2881   0.07076   0.06498  -0.0279   1.0000   0.2829
  -2.750  -0.2686   0.06826   0.06243  -0.0300   1.0000   0.3078
  -2.500  -0.2547   0.06526   0.05942  -0.0298   1.0000   0.3267
  -2.250  -0.2316   0.06269   0.05680  -0.0324   1.0000   0.3539
  -2.000  -0.2182   0.06008   0.05420  -0.0311   1.0000   0.3747
  -1.500   0.0549   0.04250   0.03429  -0.0994   1.0000   0.1800
  -1.250   0.0942   0.03979   0.03128  -0.1035   1.0000   0.1715
  -1.000   0.1470   0.03676   0.02739  -0.1101   1.0000   0.1633
  -0.750   0.1837   0.03517   0.02528  -0.1128   1.0000   0.1636
  -0.500   0.2158   0.03410   0.02386  -0.1145   1.0000   0.1674
  -0.250   0.2443   0.03355   0.02307  -0.1154   1.0000   0.1759
   0.000   0.2724   0.03334   0.02264  -0.1163   1.0000   0.1950
   0.250   0.2992   0.03320   0.02248  -0.1168   1.0000   0.2266
   0.500   0.3326   0.03249   0.02189  -0.1180   1.0000   0.3390
   0.750   0.3529   0.03285   0.02273  -0.1175   1.0000   0.4522
   1.000   0.3730   0.03324   0.02345  -0.1168   1.0000   0.5509
   1.250   0.3991   0.03271   0.02367  -0.1168   1.0000   0.7269
   1.500   0.4168   0.03341   0.02407  -0.1177   0.9968   1.0000
   1.750   0.4687   0.03514   0.02533  -0.1238   0.9795   1.0000
   2.000   0.5135   0.03664   0.02656  -0.1284   0.9619   1.0000
   2.250   0.5569   0.03803   0.02777  -0.1325   0.9454   1.0000
   2.500   0.5986   0.03934   0.02896  -0.1362   0.9296   1.0000
   2.750   0.6371   0.04056   0.03012  -0.1391   0.9140   1.0000
   3.000   0.6672   0.04170   0.03124  -0.1407   0.8977   1.0000
   3.250   0.6984   0.04286   0.03240  -0.1424   0.8825   1.0000
   3.500   0.7291   0.04403   0.03363  -0.1439   0.8684   1.0000
   3.750   0.7593   0.04520   0.03485  -0.1453   0.8550   1.0000
   4.000   0.7915   0.04634   0.03606  -0.1469   0.8429   1.0000
   4.250   0.8201   0.04753   0.03735  -0.1480   0.8309   1.0000
   4.500   0.8406   0.04889   0.03885  -0.1480   0.8183   1.0000
   4.750   0.8600   0.05034   0.04042  -0.1479   0.8062   1.0000
   5.000   0.8812   0.05176   0.04198  -0.1480   0.7946   1.0000
   5.250   0.9059   0.05307   0.04346  -0.1484   0.7832   1.0000
   5.500   0.9342   0.05413   0.04473  -0.1489   0.7707   1.0000
   5.750   0.9637   0.05505   0.04594  -0.1494   0.7579   1.0000
   6.000   0.9973   0.05576   0.04695  -0.1501   0.7456   1.0000
   6.250   1.0206   0.05668   0.04815  -0.1495   0.7306   1.0000
   6.500   1.1744   0.03024   0.01964  -0.1261   0.1970   1.0000
   6.750   1.1697   0.03383   0.02232  -0.1221   0.1310   1.0000
   7.000   1.1721   0.03650   0.02484  -0.1188   0.1145   1.0000
   7.250   1.1787   0.03881   0.02719  -0.1158   0.1033   1.0000
   7.500   1.1920   0.04106   0.02949  -0.1134   0.0959   1.0000
   7.750   1.2392   0.04290   0.03144  -0.1139   0.0888   1.0000
   8.000   1.3343   0.04694   0.03543  -0.1208   0.0820   1.0000
   8.250   1.3738   0.05019   0.03905  -0.1213   0.0794   1.0000
   8.500   1.4081   0.05419   0.04353  -0.1211   0.0804   1.0000
   8.750   1.4352   0.05862   0.04836  -0.1203   0.0823   1.0000
   9.000   1.4627   0.06436   0.05432  -0.1200   0.0844   1.0000
   9.250   1.4616   0.06641   0.05738  -0.1150   0.0882   1.0000
   9.500   1.4632   0.07102   0.06264  -0.1115   0.0927   1.0000
   9.750   1.4762   0.07719   0.06904  -0.1102   0.0969   1.0000
  10.000   1.4607   0.08020   0.07281  -0.1052   0.1016   1.0000
  10.250   1.4381   0.08469   0.07783  -0.1010   0.1056   1.0000
  10.500   1.4524   0.09162   0.08493  -0.1005   0.1129   1.0000
  10.750   1.4092   0.09425   0.08799  -0.0953   0.1145   1.0000
  11.000   1.3712   0.09845   0.09245  -0.0924   0.1155   1.0000
  11.250   1.3347   0.10381   0.09802  -0.0917   0.1163   1.0000
  11.500   1.2994   0.11024   0.10462  -0.0930   0.1167   1.0000
  11.750   1.2639   0.11798   0.11247  -0.0965   0.1170   1.0000
  12.000   1.2269   0.12780   0.12235  -0.1028   0.1180   1.0000
  12.250   1.2140   0.13776   0.13234  -0.1081   0.1274   1.0000
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