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S4022 (s4022-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 500,000
Max Cl/Cd: 113.52 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4022-il-500000-n5.txt
Download as CSV file: xf-s4022-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4022                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2431   0.08206   0.07971  -0.0781   0.9760   0.0088
  -8.750  -0.2357   0.07652   0.07418  -0.0834   0.9731   0.0089
  -8.500  -0.2360   0.07159   0.06928  -0.0866   0.9655   0.0089
  -8.250  -0.2319   0.06471   0.06241  -0.0939   0.9607   0.0091
  -8.000  -0.2385   0.05723   0.05495  -0.1008   0.9493   0.0091
  -7.750  -0.2406   0.03802   0.03529  -0.1267   0.9357   0.0089
  -7.500  -0.2264   0.03023   0.02697  -0.1331   0.9274   0.0094
  -7.250  -0.1978   0.02492   0.02106  -0.1382   0.9232   0.0100
  -7.000  -0.1624   0.02142   0.01704  -0.1425   0.9207   0.0104
  -6.750  -0.1338   0.01964   0.01494  -0.1439   0.9145   0.0107
  -6.500  -0.0976   0.01823   0.01324  -0.1466   0.9108   0.0110
  -6.250  -0.0600   0.01649   0.01119  -0.1496   0.9075   0.0113
  -6.000  -0.0297   0.01482   0.00930  -0.1510   0.9013   0.0117
  -5.750   0.0044   0.01377   0.00811  -0.1529   0.8959   0.0120
  -5.500   0.0376   0.01310   0.00735  -0.1545   0.8902   0.0127
  -5.250   0.0690   0.01250   0.00666  -0.1556   0.8833   0.0133
  -5.000   0.1012   0.01182   0.00587  -0.1568   0.8769   0.0135
  -4.750   0.1312   0.01124   0.00520  -0.1575   0.8695   0.0137
  -4.500   0.1621   0.01074   0.00460  -0.1584   0.8626   0.0140
  -4.250   0.1918   0.01033   0.00409  -0.1590   0.8549   0.0144
  -4.000   0.2217   0.00997   0.00365  -0.1596   0.8477   0.0151
  -3.750   0.2511   0.00969   0.00329  -0.1601   0.8400   0.0157
  -3.500   0.2801   0.00948   0.00299  -0.1604   0.8326   0.0164
  -3.250   0.3092   0.00928   0.00270  -0.1608   0.8249   0.0170
  -3.000   0.3377   0.00910   0.00244  -0.1610   0.8172   0.0182
  -2.750   0.3666   0.00896   0.00224  -0.1613   0.8097   0.0207
  -2.500   0.3945   0.00885   0.00209  -0.1613   0.8016   0.0233
  -2.250   0.4233   0.00865   0.00193  -0.1617   0.7941   0.0540
  -2.000   0.4521   0.00826   0.00181  -0.1623   0.7858   0.1468
  -1.750   0.4811   0.00791   0.00172  -0.1630   0.7781   0.2497
  -1.500   0.5106   0.00739   0.00170  -0.1640   0.7699   0.4252
  -1.250   0.5387   0.00727   0.00174  -0.1641   0.7620   0.4969
  -1.000   0.5663   0.00725   0.00180  -0.1641   0.7538   0.5522
  -0.750   0.5937   0.00727   0.00185  -0.1640   0.7454   0.5831
  -0.500   0.6210   0.00732   0.00187  -0.1639   0.7372   0.5960
  -0.250   0.6481   0.00737   0.00189  -0.1637   0.7281   0.6068
   0.000   0.6752   0.00743   0.00192  -0.1635   0.7193   0.6173
   0.250   0.7020   0.00749   0.00196  -0.1633   0.7101   0.6266
   0.500   0.7288   0.00755   0.00200  -0.1631   0.7001   0.6354
   0.750   0.7554   0.00763   0.00205  -0.1628   0.6901   0.6439
   1.000   0.7818   0.00771   0.00211  -0.1625   0.6798   0.6514
   1.250   0.8080   0.00780   0.00217  -0.1622   0.6687   0.6594
   1.500   0.8340   0.00789   0.00225  -0.1618   0.6568   0.6669
   2.000   0.8853   0.00811   0.00243  -0.1609   0.6306   0.6830
   2.250   0.9105   0.00824   0.00253  -0.1604   0.6164   0.6913
   2.500   0.9355   0.00838   0.00265  -0.1598   0.6020   0.6997
   2.750   0.9602   0.00853   0.00279  -0.1592   0.5871   0.7080
   3.000   0.9844   0.00871   0.00293  -0.1585   0.5703   0.7172
   3.250   1.0082   0.00889   0.00308  -0.1577   0.5517   0.7263
   3.500   1.0319   0.00909   0.00325  -0.1569   0.5333   0.7361
   4.000   1.0781   0.00954   0.00366  -0.1551   0.4941   0.7581
   4.250   1.1000   0.00982   0.00388  -0.1540   0.4707   0.7703
   4.500   1.1216   0.01011   0.00412  -0.1528   0.4459   0.7835
   4.750   1.1425   0.01044   0.00439  -0.1515   0.4198   0.7985
   5.000   1.1626   0.01079   0.00468  -0.1501   0.3926   0.8159
   5.250   1.1819   0.01116   0.00501  -0.1485   0.3647   0.8356
   5.750   1.2136   0.01191   0.00567  -0.1439   0.3049   0.9013
   6.000   1.2280   0.01232   0.00598  -0.1414   0.2736   1.0000
   6.250   1.2442   0.01298   0.00645  -0.1394   0.2356   1.0000
   6.500   1.2599   0.01367   0.00695  -0.1374   0.2008   1.0000
   6.750   1.2753   0.01437   0.00747  -0.1354   0.1678   1.0000
   7.000   1.2910   0.01504   0.00803  -0.1334   0.1406   1.0000
   7.250   1.3064   0.01574   0.00860  -0.1315   0.1157   1.0000
   7.500   1.3210   0.01647   0.00920  -0.1294   0.0934   1.0000
   7.750   1.3372   0.01709   0.00977  -0.1276   0.0790   1.0000
   8.000   1.3531   0.01774   0.01037  -0.1257   0.0664   1.0000
   8.250   1.3682   0.01842   0.01101  -0.1238   0.0550   1.0000
   8.500   1.3823   0.01917   0.01172  -0.1218   0.0435   1.0000
   8.750   1.3965   0.01991   0.01244  -0.1198   0.0350   1.0000
   9.000   1.4103   0.02069   0.01320  -0.1178   0.0272   1.0000
   9.250   1.4218   0.02162   0.01411  -0.1155   0.0182   1.0000
   9.500   1.4322   0.02266   0.01512  -0.1132   0.0113   1.0000
   9.750   1.4433   0.02366   0.01615  -0.1110   0.0088   1.0000
  10.000   1.4556   0.02460   0.01716  -0.1090   0.0078   1.0000
  10.250   1.4674   0.02558   0.01822  -0.1070   0.0071   1.0000
  10.500   1.4781   0.02667   0.01939  -0.1050   0.0065   1.0000
  10.750   1.4874   0.02790   0.02072  -0.1029   0.0059   1.0000
  11.000   1.4954   0.02928   0.02220  -0.1008   0.0054   1.0000
  11.250   1.5028   0.03074   0.02377  -0.0987   0.0052   1.0000
  11.500   1.5117   0.03211   0.02524  -0.0970   0.0050   1.0000
  11.750   1.5192   0.03363   0.02687  -0.0952   0.0049   1.0000
  12.000   1.5257   0.03528   0.02863  -0.0934   0.0047   1.0000
  12.250   1.5317   0.03704   0.03050  -0.0918   0.0045   1.0000
  12.500   1.5370   0.03892   0.03248  -0.0902   0.0043   1.0000
  12.750   1.5415   0.04092   0.03460  -0.0888   0.0042   1.0000
  13.000   1.5453   0.04306   0.03684  -0.0874   0.0040   1.0000
  13.250   1.5483   0.04536   0.03925  -0.0862   0.0038   1.0000
  13.500   1.5505   0.04782   0.04185  -0.0852   0.0036   1.0000
  13.750   1.5509   0.05058   0.04473  -0.0843   0.0035   1.0000
  14.000   1.5486   0.05379   0.04806  -0.0835   0.0034   1.0000
  14.250   1.5435   0.05748   0.05189  -0.0829   0.0032   1.0000
  14.500   1.5357   0.06170   0.05626  -0.0826   0.0031   1.0000
  14.750   1.5289   0.06596   0.06067  -0.0827   0.0031   1.0000
  15.000   1.5266   0.06977   0.06462  -0.0829   0.0030   1.0000
  15.250   1.5235   0.07381   0.06879  -0.0834   0.0030   1.0000
  15.500   1.5193   0.07816   0.07329  -0.0842   0.0029   1.0000
  15.750   1.5145   0.08274   0.07801  -0.0853   0.0029   1.0000
  16.000   1.5081   0.08772   0.08315  -0.0866   0.0029   1.0000
  16.250   1.5016   0.09288   0.08845  -0.0882   0.0028   1.0000
  16.500   1.4936   0.09843   0.09416  -0.0902   0.0028   1.0000
  16.750   1.4856   0.10414   0.10002  -0.0924   0.0028   1.0000
  17.000   1.4770   0.11007   0.10610  -0.0949   0.0027   1.0000
  17.250   1.4678   0.11627   0.11245  -0.0977   0.0027   1.0000
  17.500   1.4588   0.12254   0.11888  -0.1007   0.0027   1.0000
  17.750   1.4492   0.12903   0.12552  -0.1041   0.0026   1.0000
  18.000   1.4395   0.13567   0.13231  -0.1077   0.0026   1.0000
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