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GOE 421 AIRFOIL (goe421-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 421 AIRFOIL (goe421-il)
Reynolds number: 200,000
Max Cl/Cd: 60.42 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe421-il-200000-n5.txt
Download as CSV file: xf-goe421-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 421 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2323   0.04596   0.04091  -0.1793   0.8785   0.0468
 -12.000  -0.2581   0.04043   0.03520  -0.1836   0.8670   0.0471
 -11.750  -0.2677   0.03599   0.03051  -0.1889   0.8588   0.0475
 -11.500  -0.2651   0.03392   0.02825  -0.1896   0.8511   0.0482
 -11.250  -0.2509   0.03189   0.02598  -0.1912   0.8466   0.0491
 -11.000  -0.2444   0.03049   0.02438  -0.1903   0.8389   0.0499
 -10.750  -0.2290   0.02897   0.02258  -0.1906   0.8336   0.0510
 -10.500  -0.2062   0.02759   0.02097  -0.1916   0.8301   0.0520
 -10.250  -0.1912   0.02688   0.02025  -0.1904   0.8236   0.0528
 -10.000  -0.1701   0.02609   0.01939  -0.1902   0.8184   0.0537
  -9.750  -0.1438   0.02517   0.01834  -0.1910   0.8145   0.0549
  -9.500  -0.1230   0.02442   0.01745  -0.1906   0.8093   0.0561
  -9.250  -0.1033   0.02373   0.01662  -0.1898   0.8036   0.0574
  -9.000  -0.0778   0.02298   0.01566  -0.1901   0.7994   0.0587
  -8.750  -0.0493   0.02221   0.01485  -0.1910   0.7961   0.0601
  -8.500  -0.0309   0.02176   0.01437  -0.1897   0.7901   0.0613
  -8.250  -0.0077   0.02125   0.01378  -0.1893   0.7849   0.0627
  -8.000   0.0204   0.02069   0.01308  -0.1898   0.7809   0.0645
  -7.750   0.0478   0.02021   0.01244  -0.1901   0.7769   0.0664
  -7.500   0.0674   0.01978   0.01204  -0.1890   0.7714   0.0681
  -7.250   0.0923   0.01938   0.01159  -0.1888   0.7668   0.0701
  -7.000   0.1214   0.01896   0.01106  -0.1893   0.7631   0.0725
  -6.750   0.1482   0.01862   0.01060  -0.1894   0.7589   0.0750
  -6.500   0.1693   0.01829   0.01029  -0.1884   0.7534   0.0775
  -6.250   0.1952   0.01799   0.00992  -0.1883   0.7490   0.0809
  -6.000   0.2249   0.01769   0.00950  -0.1889   0.7455   0.0847
  -5.750   0.2522   0.01736   0.00914  -0.1891   0.7417   0.0889
  -5.500   0.2741   0.01716   0.00892  -0.1881   0.7365   0.0939
  -5.250   0.2999   0.01689   0.00861  -0.1880   0.7319   0.1000
  -5.000   0.3294   0.01662   0.00827  -0.1885   0.7283   0.1084
  -4.750   0.3587   0.01635   0.00799  -0.1890   0.7250   0.1201
  -4.500   0.3803   0.01624   0.00797  -0.1880   0.7199   0.1349
  -4.250   0.4059   0.01622   0.00801  -0.1877   0.7154   0.1541
  -4.000   0.4352   0.01625   0.00797  -0.1880   0.7116   0.1714
  -3.750   0.4673   0.01627   0.00788  -0.1889   0.7086   0.1838
  -3.500   0.4883   0.01638   0.00792  -0.1876   0.7034   0.1927
  -3.250   0.5126   0.01641   0.00794  -0.1870   0.6982   0.1996
  -3.000   0.5416   0.01641   0.00782  -0.1873   0.6936   0.2071
  -2.750   0.5680   0.01641   0.00773  -0.1870   0.6886   0.2130
  -2.500   0.5888   0.01642   0.00777  -0.1858   0.6822   0.2184
  -2.250   0.6160   0.01641   0.00767  -0.1857   0.6768   0.2249
  -2.000   0.6424   0.01644   0.00759  -0.1855   0.6715   0.2309
  -1.750   0.6620   0.01642   0.00763  -0.1840   0.6648   0.2361
  -1.500   0.6885   0.01639   0.00753  -0.1838   0.6589   0.2414
  -1.250   0.7118   0.01644   0.00752  -0.1830   0.6531   0.2469
  -1.000   0.7320   0.01646   0.00754  -0.1817   0.6472   0.2517
  -0.750   0.7575   0.01643   0.00751  -0.1813   0.6425   0.2560
  -0.500   0.7840   0.01643   0.00746  -0.1812   0.6381   0.2589
  -0.250   0.8017   0.01652   0.00756  -0.1794   0.6327   0.2615
   0.000   0.8245   0.01657   0.00760  -0.1785   0.6277   0.2650
   0.250   0.8510   0.01661   0.00756  -0.1784   0.6234   0.2687
   0.500   0.8725   0.01669   0.00768  -0.1774   0.6185   0.2720
   0.750   0.8931   0.01682   0.00785  -0.1762   0.6130   0.2758
   1.000   0.9173   0.01690   0.00792  -0.1757   0.6078   0.2804
   1.250   0.9415   0.01701   0.00800  -0.1752   0.6028   0.2858
   1.500   0.9603   0.01721   0.00826  -0.1738   0.5964   0.2915
   1.750   0.9830   0.01734   0.00840  -0.1731   0.5905   0.2998
   2.000   1.0052   0.01750   0.00858  -0.1723   0.5847   0.3100
   2.250   1.0235   0.01775   0.00889  -0.1708   0.5779   0.3235
   2.500   1.0457   0.01791   0.00907  -0.1700   0.5718   0.3423
   2.750   1.0651   0.01816   0.00938  -0.1688   0.5653   0.3636
   3.000   1.0836   0.01842   0.00971  -0.1675   0.5581   0.3859
   3.250   1.1044   0.01863   0.00993  -0.1665   0.5515   0.4092
   3.500   1.1209   0.01896   0.01036  -0.1649   0.5435   0.4321
   3.750   1.1400   0.01922   0.01065  -0.1637   0.5360   0.4598
   4.000   1.1562   0.01956   0.01114  -0.1621   0.5274   0.4978
   4.250   1.1739   0.01978   0.01154  -0.1607   0.5189   0.5804
   4.500   1.1806   0.01954   0.01196  -0.1568   0.5099   1.0000
   4.750   1.1964   0.02005   0.01238  -0.1552   0.5005   1.0000
   5.000   1.2104   0.02066   0.01295  -0.1533   0.4899   1.0000
   5.250   1.2245   0.02130   0.01351  -0.1515   0.4794   1.0000
   5.500   1.2370   0.02201   0.01414  -0.1496   0.4686   1.0000
   5.750   1.2501   0.02275   0.01483  -0.1478   0.4577   1.0000
   6.000   1.2621   0.02355   0.01556  -0.1458   0.4477   1.0000
   6.250   1.2744   0.02438   0.01633  -0.1440   0.4377   1.0000
   6.500   1.2868   0.02523   0.01712  -0.1423   0.4290   1.0000
   6.750   1.2990   0.02612   0.01796  -0.1405   0.4205   1.0000
   7.000   1.3120   0.02700   0.01880  -0.1390   0.4132   1.0000
   7.250   1.3250   0.02790   0.01967  -0.1375   0.4060   1.0000
   7.500   1.3377   0.02883   0.02052  -0.1359   0.3999   1.0000
   7.750   1.3522   0.02969   0.02140  -0.1347   0.3942   1.0000
   8.000   1.3664   0.03059   0.02228  -0.1335   0.3889   1.0000
   8.250   1.3803   0.03149   0.02314  -0.1322   0.3843   1.0000
   8.500   1.3953   0.03236   0.02401  -0.1311   0.3800   1.0000
   8.750   1.4096   0.03329   0.02497  -0.1300   0.3751   1.0000
   9.000   1.4228   0.03428   0.02594  -0.1287   0.3703   1.0000
   9.250   1.4363   0.03524   0.02684  -0.1275   0.3660   1.0000
   9.500   1.4505   0.03622   0.02787  -0.1265   0.3620   1.0000
   9.750   1.4648   0.03719   0.02888  -0.1255   0.3582   1.0000
  10.000   1.4788   0.03818   0.02989  -0.1245   0.3546   1.0000
  10.250   1.4929   0.03915   0.03085  -0.1235   0.3514   1.0000
  10.500   1.5084   0.04000   0.03166  -0.1226   0.3485   1.0000
  10.750   1.5229   0.04100   0.03274  -0.1218   0.3458   1.0000
  11.000   1.5370   0.04202   0.03384  -0.1209   0.3433   1.0000
  11.250   1.5507   0.04308   0.03496  -0.1200   0.3406   1.0000
  11.500   1.5637   0.04419   0.03612  -0.1191   0.3375   1.0000
  11.750   1.5766   0.04529   0.03724  -0.1182   0.3344   1.0000
  12.000   1.5914   0.04620   0.03813  -0.1174   0.3315   1.0000
  12.250   1.6031   0.04745   0.03945  -0.1164   0.3287   1.0000
  12.500   1.6120   0.04896   0.04109  -0.1154   0.3253   1.0000
  12.750   1.6201   0.05055   0.04276  -0.1143   0.3215   1.0000
  13.000   1.6289   0.05203   0.04427  -0.1132   0.3173   1.0000
  13.250   1.6399   0.05327   0.04546  -0.1123   0.3130   1.0000
  13.500   1.6437   0.05537   0.04773  -0.1112   0.3089   1.0000
  13.750   1.6481   0.05742   0.04989  -0.1101   0.3044   1.0000
  14.000   1.6542   0.05925   0.05176  -0.1091   0.2999   1.0000
  14.250   1.6630   0.06076   0.05325  -0.1082   0.2959   1.0000
  14.500   1.6653   0.06314   0.05580  -0.1072   0.2917   1.0000
  14.750   1.6672   0.06555   0.05833  -0.1063   0.2866   1.0000
  15.000   1.6698   0.06784   0.06066  -0.1053   0.2813   1.0000
  15.250   1.6703   0.07046   0.06339  -0.1045   0.2758   1.0000
  15.500   1.6693   0.07332   0.06637  -0.1036   0.2695   1.0000
  15.750   1.6688   0.07606   0.06914  -0.1028   0.2633   1.0000
  16.000   1.6659   0.07922   0.07247  -0.1021   0.2560   1.0000
  16.250   1.6602   0.08270   0.07601  -0.1014   0.2470   1.0000
  16.500   1.6520   0.08655   0.07994  -0.1007   0.2347   1.0000
  16.750   1.6413   0.09075   0.08418  -0.1001   0.2175   1.0000
  17.000   1.6179   0.09655   0.08988  -0.0994   0.1922   1.0000
  17.250   1.5892   0.10312   0.09637  -0.0990   0.1763   1.0000
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