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GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 482 AIRFOIL (goe482-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.59 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe482-il-1000000.txt
Download as CSV file: xf-goe482-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 482 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500   0.0800   0.12521   0.12237  -0.1184   0.8005   0.0192
 -14.250   0.0823   0.12103   0.11815  -0.1200   0.7960   0.0197
 -14.000   0.0801   0.11579   0.11292  -0.1220   0.7931   0.0210
 -13.750   0.0953   0.11478   0.11189  -0.1229   0.7887   0.0213
 -13.500   0.1071   0.11299   0.11009  -0.1239   0.7845   0.0218
 -13.250   0.0935   0.10557   0.10264  -0.1266   0.7814   0.0241
 -13.000   0.1068   0.10418   0.10123  -0.1274   0.7773   0.0244
 -12.750   0.1205   0.10279   0.09984  -0.1283   0.7737   0.0246
 -12.500   0.1336   0.10132   0.09836  -0.1291   0.7693   0.0250
 -12.250   0.1225   0.09498   0.09200  -0.1318   0.7659   0.0279
 -12.000   0.1392   0.09441   0.09139  -0.1322   0.7607   0.0281
 -11.750   0.1522   0.09291   0.08990  -0.1329   0.7569   0.0284
 -11.500   0.1678   0.09198   0.08897  -0.1335   0.7526   0.0288
 -11.250   0.1550   0.08589   0.08287  -0.1363   0.7489   0.0320
 -11.000   0.1718   0.08528   0.08223  -0.1364   0.7440   0.0323
 -10.750   0.1942   0.08559   0.08253  -0.1363   0.7394   0.0328
 -10.500   0.2084   0.08442   0.08136  -0.1369   0.7344   0.0337
  -8.250   0.0665   0.02166   0.01768  -0.1890   0.6864   0.0449
  -8.000   0.0916   0.01970   0.01543  -0.1910   0.6794   0.0454
  -7.750   0.1181   0.01863   0.01413  -0.1920   0.6719   0.0460
  -7.500   0.1457   0.01778   0.01310  -0.1928   0.6637   0.0463
  -7.250   0.1730   0.01719   0.01232  -0.1932   0.6547   0.0466
  -7.000   0.2007   0.01627   0.01121  -0.1939   0.6454   0.0469
  -6.750   0.2270   0.01464   0.00936  -0.1948   0.6362   0.0475
  -6.500   0.2547   0.01410   0.00873  -0.1951   0.6256   0.0479
  -6.250   0.2825   0.01374   0.00828  -0.1952   0.6153   0.0483
  -6.000   0.3100   0.01345   0.00788  -0.1953   0.6043   0.0487
  -5.750   0.3382   0.01317   0.00752  -0.1954   0.5943   0.0491
  -5.500   0.3660   0.01297   0.00724  -0.1955   0.5847   0.0497
  -5.250   0.3940   0.01270   0.00687  -0.1956   0.5752   0.0501
  -5.000   0.4220   0.01243   0.00650  -0.1957   0.5669   0.0505
  -4.750   0.4501   0.01216   0.00615  -0.1958   0.5591   0.0510
  -4.500   0.4780   0.01195   0.00585  -0.1958   0.5518   0.0514
  -4.250   0.5066   0.01173   0.00557  -0.1959   0.5458   0.0519
  -4.000   0.5346   0.01159   0.00535  -0.1959   0.5396   0.0523
  -3.750   0.5627   0.01148   0.00517  -0.1959   0.5341   0.0527
  -3.500   0.5914   0.01137   0.00503  -0.1960   0.5294   0.0530
  -3.250   0.6196   0.01092   0.00451  -0.1963   0.5245   0.0538
  -3.000   0.6474   0.01074   0.00429  -0.1963   0.5195   0.0547
  -2.750   0.6761   0.01062   0.00416  -0.1965   0.5160   0.0555
  -2.500   0.7048   0.01052   0.00405  -0.1966   0.5119   0.0563
  -2.250   0.7330   0.01045   0.00395  -0.1967   0.5078   0.0570
  -2.000   0.7607   0.01042   0.00387  -0.1966   0.5035   0.0578
  -1.750   0.7888   0.01038   0.00380  -0.1966   0.4999   0.0587
  -1.500   0.8176   0.01032   0.00373  -0.1968   0.4971   0.0595
  -1.250   0.8459   0.01029   0.00369  -0.1968   0.4935   0.0601
  -1.000   0.8740   0.01020   0.00356  -0.1969   0.4896   0.0613
  -0.750   0.9013   0.01019   0.00350  -0.1969   0.4854   0.0630
  -0.500   0.9293   0.01018   0.00349  -0.1969   0.4823   0.0647
  -0.250   0.9578   0.01015   0.00347  -0.1970   0.4796   0.0664
   0.000   0.9858   0.01016   0.00346  -0.1970   0.4763   0.0679
   0.250   1.0133   0.01017   0.00345  -0.1970   0.4728   0.0701
   0.500   1.0401   0.01021   0.00347  -0.1968   0.4689   0.0739
   0.750   1.0672   0.01026   0.00351  -0.1967   0.4654   0.0777
   1.000   1.0955   0.01020   0.00352  -0.1968   0.4625   0.0936
   1.250   1.1233   0.01010   0.00360  -0.1970   0.4591   0.1661
   1.500   1.1503   0.01007   0.00368  -0.1970   0.4555   0.2180
   1.750   1.1764   0.01005   0.00384  -0.1969   0.4517   0.3136
   2.000   1.2027   0.01013   0.00398  -0.1967   0.4484   0.3506
   2.250   1.2299   0.01018   0.00407  -0.1966   0.4455   0.3692
   2.500   1.2563   0.01027   0.00417  -0.1964   0.4420   0.3835
   2.750   1.2817   0.01038   0.00429  -0.1960   0.4381   0.3989
   3.000   1.3058   0.01055   0.00444  -0.1954   0.4337   0.4115
   3.250   1.3318   0.01063   0.00454  -0.1952   0.4305   0.4218
   3.500   1.3576   0.01070   0.00466  -0.1949   0.4269   0.4366
   3.750   1.3822   0.01080   0.00480  -0.1944   0.4230   0.4589
   4.000   1.4054   0.01090   0.00501  -0.1938   0.4188   0.5166
   4.250   1.4288   0.01099   0.00524  -0.1931   0.4150   0.6001
   4.500   1.4528   0.01099   0.00541  -0.1926   0.4117   0.6738
   4.750   1.4722   0.01070   0.00563  -0.1910   0.4079   1.0000
   5.000   1.4923   0.01092   0.00581  -0.1897   0.4037   1.0000
   5.250   1.5109   0.01118   0.00603  -0.1882   0.3994   1.0000
   5.500   1.5336   0.01134   0.00620  -0.1874   0.3961   1.0000
   5.750   1.5543   0.01155   0.00640  -0.1862   0.3920   1.0000
   6.000   1.5729   0.01184   0.00665  -0.1848   0.3876   1.0000
   6.250   1.5901   0.01218   0.00696  -0.1831   0.3831   1.0000
   6.500   1.6116   0.01239   0.00719  -0.1823   0.3800   1.0000
   6.750   1.6314   0.01266   0.00746  -0.1811   0.3762   1.0000
   7.000   1.6486   0.01303   0.00781  -0.1796   0.3720   1.0000
   7.250   1.6637   0.01349   0.00824  -0.1777   0.3671   1.0000
   7.500   1.6841   0.01376   0.00853  -0.1768   0.3635   1.0000
   7.750   1.7015   0.01415   0.00892  -0.1754   0.3585   1.0000
   8.000   1.7147   0.01473   0.00946  -0.1735   0.3530   1.0000
   8.250   1.7325   0.01515   0.00989  -0.1723   0.3491   1.0000
   8.500   1.7499   0.01559   0.01034  -0.1711   0.3451   1.0000
   8.750   1.7643   0.01619   0.01093  -0.1695   0.3403   1.0000
   9.000   1.7759   0.01694   0.01166  -0.1676   0.3351   1.0000
   9.250   1.7940   0.01740   0.01216  -0.1666   0.3312   1.0000
   9.500   1.8088   0.01805   0.01281  -0.1652   0.3269   1.0000
   9.750   1.8199   0.01892   0.01367  -0.1635   0.3222   1.0000
  10.000   1.8338   0.01968   0.01444  -0.1622   0.3179   1.0000
  10.250   1.8494   0.02035   0.01514  -0.1611   0.3141   1.0000
  10.500   1.8615   0.02125   0.01605  -0.1597   0.3097   1.0000
  10.750   1.8708   0.02236   0.01715  -0.1580   0.3051   1.0000
  11.000   1.8851   0.02317   0.01800  -0.1569   0.3010   1.0000
  11.250   1.8973   0.02413   0.01898  -0.1557   0.2960   1.0000
  11.500   1.9037   0.02551   0.02034  -0.1539   0.2900   1.0000
  11.750   1.9154   0.02657   0.02143  -0.1527   0.2852   1.0000
  12.000   1.9239   0.02786   0.02273  -0.1513   0.2784   1.0000
  12.250   1.9284   0.02949   0.02436  -0.1496   0.2719   1.0000
  12.500   1.9355   0.03098   0.02585  -0.1483   0.2640   1.0000
  12.750   1.9372   0.03294   0.02780  -0.1466   0.2549   1.0000
  13.000   1.9329   0.03548   0.03029  -0.1446   0.2425   1.0000
  13.250   1.9253   0.03843   0.03319  -0.1425   0.2275   1.0000
  13.500   1.9091   0.04233   0.03701  -0.1403   0.2073   1.0000
  13.750   1.8868   0.04709   0.04169  -0.1381   0.1882   1.0000
  14.000   1.8636   0.05224   0.04677  -0.1362   0.1702   1.0000
  14.250   1.8432   0.05735   0.05186  -0.1349   0.1557   1.0000
  14.500   1.8210   0.06296   0.05744  -0.1339   0.1413   1.0000
  14.750   1.7990   0.06875   0.06321  -0.1333   0.1269   1.0000
  15.000   1.7728   0.07537   0.06978  -0.1329   0.1114   1.0000
  15.250   1.7398   0.08315   0.07752  -0.1330   0.0913   1.0000
  15.500   1.7080   0.09109   0.08541  -0.1334   0.0717   1.0000
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