Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S4022 (s4022-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 1,000,000
Max Cl/Cd: 128.12 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4022-il-1000000-n5.txt
Download as CSV file: xf-s4022-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2467   0.08961   0.08787  -0.0792   0.9848   0.0054
  -9.750  -0.2500   0.08286   0.08113  -0.0832   0.9823   0.0060
  -9.250  -0.3717   0.03330   0.03118  -0.1286   0.9499   0.0063
  -9.000  -0.3607   0.02614   0.02345  -0.1365   0.9419   0.0065
  -8.750  -0.3328   0.02315   0.02011  -0.1405   0.9376   0.0066
  -8.500  -0.2986   0.02101   0.01769  -0.1445   0.9350   0.0067
  -8.250  -0.2690   0.01752   0.01374  -0.1484   0.9295   0.0071
  -8.000  -0.2321   0.01651   0.01261  -0.1515   0.9253   0.0074
  -7.750  -0.1935   0.01580   0.01179  -0.1547   0.9214   0.0077
  -7.500  -0.1605   0.01504   0.01091  -0.1566   0.9148   0.0080
  -7.250  -0.1262   0.01429   0.01000  -0.1587   0.9080   0.0083
  -7.000  -0.0959   0.01350   0.00906  -0.1598   0.8995   0.0085
  -6.750  -0.0653   0.01287   0.00829  -0.1609   0.8913   0.0089
  -6.500  -0.0371   0.01217   0.00746  -0.1614   0.8820   0.0091
  -6.250  -0.0092   0.01160   0.00676  -0.1618   0.8732   0.0093
  -6.000   0.0185   0.01106   0.00610  -0.1621   0.8644   0.0096
  -5.750   0.0455   0.01055   0.00548  -0.1622   0.8555   0.0097
  -5.500   0.0727   0.01012   0.00495  -0.1623   0.8473   0.0099
  -5.250   0.1000   0.00981   0.00455  -0.1624   0.8388   0.0103
  -5.000   0.1273   0.00950   0.00417  -0.1624   0.8308   0.0105
  -4.750   0.1546   0.00915   0.00373  -0.1625   0.8229   0.0106
  -4.500   0.1822   0.00884   0.00335  -0.1626   0.8149   0.0108
  -4.250   0.2098   0.00861   0.00304  -0.1627   0.8073   0.0109
  -4.000   0.2374   0.00842   0.00280  -0.1628   0.7992   0.0111
  -3.750   0.2655   0.00804   0.00231  -0.1630   0.7916   0.0120
  -3.500   0.2932   0.00785   0.00205  -0.1631   0.7835   0.0130
  -3.250   0.3210   0.00773   0.00188  -0.1632   0.7757   0.0136
  -3.000   0.3484   0.00764   0.00173  -0.1631   0.7676   0.0142
  -2.750   0.3762   0.00756   0.00161  -0.1632   0.7595   0.0147
  -2.500   0.4037   0.00750   0.00150  -0.1631   0.7517   0.0153
  -2.250   0.4313   0.00745   0.00140  -0.1631   0.7435   0.0162
  -2.000   0.4588   0.00741   0.00132  -0.1631   0.7357   0.0181
  -1.750   0.4867   0.00728   0.00125  -0.1632   0.7273   0.0471
  -1.500   0.5153   0.00701   0.00118  -0.1637   0.7191   0.1288
  -1.250   0.5439   0.00665   0.00113  -0.1643   0.7105   0.2529
  -1.000   0.5725   0.00640   0.00112  -0.1648   0.7016   0.3495
  -0.750   0.6008   0.00620   0.00114  -0.1652   0.6927   0.4454
  -0.500   0.6282   0.00614   0.00119  -0.1652   0.6828   0.5068
  -0.250   0.6557   0.00613   0.00125  -0.1652   0.6727   0.5518
   0.000   0.6827   0.00618   0.00129  -0.1650   0.6623   0.5686
   0.250   0.7094   0.00626   0.00133  -0.1648   0.6513   0.5788
   0.500   0.7359   0.00635   0.00138  -0.1646   0.6395   0.5884
   0.750   0.7625   0.00643   0.00144  -0.1643   0.6270   0.5975
   1.000   0.7888   0.00653   0.00151  -0.1640   0.6135   0.6057
   1.250   0.8148   0.00665   0.00158  -0.1637   0.5992   0.6137
   1.500   0.8407   0.00677   0.00166  -0.1633   0.5843   0.6207
   1.750   0.8666   0.00690   0.00175  -0.1630   0.5699   0.6278
   2.000   0.8924   0.00704   0.00185  -0.1626   0.5553   0.6345
   2.250   0.9179   0.00719   0.00195  -0.1622   0.5386   0.6419
   2.500   0.9430   0.00737   0.00207  -0.1617   0.5187   0.6490
   2.750   0.9679   0.00756   0.00222  -0.1611   0.4999   0.6567
   3.000   0.9929   0.00775   0.00235  -0.1606   0.4816   0.6640
   3.250   1.0176   0.00796   0.00250  -0.1601   0.4613   0.6718
   3.500   1.0415   0.00821   0.00268  -0.1594   0.4380   0.6794
   3.750   1.0652   0.00849   0.00287  -0.1587   0.4136   0.6877
   4.000   1.0885   0.00878   0.00309  -0.1579   0.3875   0.6958
   4.250   1.1114   0.00911   0.00332  -0.1570   0.3597   0.7048
   4.500   1.1339   0.00946   0.00357  -0.1561   0.3315   0.7142
   4.750   1.1557   0.00984   0.00385  -0.1551   0.3017   0.7240
   5.000   1.1768   0.01028   0.00416  -0.1540   0.2697   0.7347
   5.250   1.1965   0.01081   0.00454  -0.1526   0.2316   0.7463
   5.500   1.2144   0.01145   0.00497  -0.1509   0.1885   0.7587
   5.750   1.2341   0.01193   0.00535  -0.1496   0.1598   0.7728
   6.000   1.2546   0.01235   0.00572  -0.1483   0.1380   0.7886
   6.250   1.2738   0.01283   0.00612  -0.1469   0.1151   0.8060
   6.500   1.2916   0.01330   0.00653  -0.1451   0.0947   0.8272
   6.750   1.3078   0.01376   0.00698  -0.1430   0.0748   0.8551
   7.000   1.3222   0.01413   0.00738  -0.1405   0.0613   0.8993
   7.250   1.3353   0.01439   0.00770  -0.1376   0.0524   1.0000
   7.500   1.3536   0.01486   0.00813  -0.1360   0.0439   1.0000
   7.750   1.3713   0.01536   0.00859  -0.1344   0.0356   1.0000
   8.000   1.3879   0.01591   0.00909  -0.1326   0.0270   1.0000
   8.250   1.4032   0.01654   0.00967  -0.1305   0.0184   1.0000
   8.500   1.4163   0.01732   0.01041  -0.1282   0.0088   1.0000
   8.750   1.4324   0.01789   0.01099  -0.1263   0.0070   1.0000
   9.000   1.4481   0.01850   0.01163  -0.1245   0.0058   1.0000
   9.250   1.4640   0.01910   0.01227  -0.1227   0.0051   1.0000
   9.500   1.4798   0.01969   0.01291  -0.1209   0.0048   1.0000
   9.750   1.4951   0.02033   0.01360  -0.1191   0.0045   1.0000
  10.000   1.5093   0.02103   0.01435  -0.1172   0.0042   1.0000
  10.250   1.5228   0.02180   0.01519  -0.1153   0.0039   1.0000
  10.500   1.5354   0.02265   0.01608  -0.1132   0.0036   1.0000
  10.750   1.5464   0.02362   0.01712  -0.1111   0.0033   1.0000
  11.000   1.5557   0.02475   0.01833  -0.1088   0.0031   1.0000
  11.250   1.5682   0.02565   0.01930  -0.1070   0.0030   1.0000
  11.500   1.5799   0.02664   0.02034  -0.1052   0.0029   1.0000
  11.750   1.5906   0.02771   0.02149  -0.1034   0.0028   1.0000
  12.000   1.6005   0.02888   0.02273  -0.1015   0.0028   1.0000
  12.250   1.6099   0.03012   0.02405  -0.0997   0.0027   1.0000
  12.500   1.6186   0.03147   0.02547  -0.0980   0.0026   1.0000
  12.750   1.6264   0.03292   0.02702  -0.0963   0.0025   1.0000
  13.000   1.6337   0.03446   0.02864  -0.0946   0.0024   1.0000
  13.250   1.6402   0.03612   0.03038  -0.0930   0.0023   1.0000
  13.500   1.6465   0.03785   0.03219  -0.0916   0.0022   1.0000
  13.750   1.6517   0.03973   0.03416  -0.0902   0.0021   1.0000
  14.000   1.6562   0.04175   0.03626  -0.0889   0.0020   1.0000
  14.250   1.6598   0.04393   0.03854  -0.0877   0.0020   1.0000
  14.500   1.6624   0.04631   0.04101  -0.0866   0.0019   1.0000
  14.750   1.6638   0.04889   0.04368  -0.0857   0.0018   1.0000
  15.000   1.6635   0.05178   0.04669  -0.0849   0.0018   1.0000
  15.250   1.6603   0.05515   0.05018  -0.0842   0.0017   1.0000
  15.500   1.6548   0.05897   0.05413  -0.0838   0.0016   1.0000
  15.750   1.6462   0.06337   0.05868  -0.0838   0.0016   1.0000
  16.000   1.6441   0.06703   0.06246  -0.0839   0.0016   1.0000
  16.250   1.6412   0.07094   0.06649  -0.0844   0.0016   1.0000
  16.500   1.6365   0.07525   0.07093  -0.0851   0.0015   1.0000
  16.750   1.6320   0.07967   0.07547  -0.0860   0.0015   1.0000
  17.000   1.6253   0.08459   0.08051  -0.0872   0.0015   1.0000
  17.250   1.6177   0.08983   0.08589  -0.0888   0.0015   1.0000
  17.500   1.6099   0.09523   0.09142  -0.0906   0.0015   1.0000
  17.750   1.6002   0.10111   0.09743  -0.0929   0.0015   1.0000
  18.000   1.5891   0.10742   0.10388  -0.0955   0.0015   1.0000
  18.250   1.5771   0.11405   0.11065  -0.0985   0.0015   1.0000
  18.500   1.5663   0.12057   0.11730  -0.1016   0.0014   1.0000
  18.750   1.5522   0.12788   0.12476  -0.1054   0.0014   1.0000
  19.000   1.5405   0.13480   0.13181  -0.1091   0.0014   1.0000
<< Back to S4022 (s4022-il)

Polar data table (+)

Polar graphs


<< Back to S4022 (s4022-il)