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S4022 (s4022-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 200,000
Max Cl/Cd: 93.42 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4022-il-200000.txt
Download as CSV file: xf-s4022-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3589   0.11288   0.10959  -0.0327   1.0000   0.0389
  -9.000  -0.3644   0.11075   0.10751  -0.0316   1.0000   0.0400
  -8.750  -0.3713   0.10866   0.10548  -0.0305   1.0000   0.0411
  -8.500  -0.2724   0.09072   0.08777  -0.0513   0.9850   0.0467
  -8.250  -0.2468   0.08829   0.08531  -0.0501   0.9827   0.0501
  -8.000  -0.2399   0.08438   0.08141  -0.0523   0.9780   0.0526
  -7.750  -0.2334   0.07951   0.07654  -0.0565   0.9745   0.0551
  -7.500  -0.3666   0.08639   0.08338  -0.0581   0.9792   0.0462
  -7.250  -0.3391   0.08583   0.08279  -0.0505   0.9801   0.0496
  -7.000  -0.3275   0.08231   0.07927  -0.0546   0.9744   0.0521
  -6.750  -0.3171   0.07700   0.07398  -0.0624   0.9659   0.0553
  -6.500  -0.2928   0.06467   0.06106  -0.0928   0.9517   0.0586
  -6.250  -0.2784   0.05829   0.05493  -0.0933   0.9497   0.0608
  -6.000  -0.2501   0.05535   0.05199  -0.0962   0.9476   0.0637
  -5.750  -0.2329   0.05115   0.04757  -0.1004   0.9388   0.0685
  -5.500  -0.1980   0.04495   0.04098  -0.1091   0.9356   0.0754
  -5.250  -0.1727   0.04232   0.03820  -0.1112   0.9302   0.0807
  -5.000  -0.1409   0.03853   0.03411  -0.1155   0.9255   0.0906
  -4.750  -0.0855   0.03034   0.02447  -0.1223   0.9240   0.0603
  -4.500  -0.0408   0.02710   0.02059  -0.1247   0.9226   0.0461
  -4.250  -0.0005   0.02378   0.01699  -0.1276   0.9215   0.0426
  -4.000   0.0280   0.02214   0.01510  -0.1277   0.9159   0.0411
  -3.750   0.0633   0.02071   0.01346  -0.1291   0.9124   0.0403
  -3.500   0.1024   0.01944   0.01209  -0.1311   0.9101   0.0411
  -3.250   0.1433   0.01837   0.01096  -0.1336   0.9084   0.0426
  -3.000   0.1862   0.01748   0.01001  -0.1365   0.9071   0.0453
  -2.750   0.2118   0.01690   0.00943  -0.1365   0.8993   0.0520
  -2.500   0.2537   0.01610   0.00858  -0.1393   0.8969   0.0664
  -2.250   0.3015   0.01402   0.00818  -0.1448   0.8961   0.5038
  -2.000   0.3429   0.01376   0.00806  -0.1470   0.8944   0.5977
  -1.750   0.3704   0.01379   0.00810  -0.1466   0.8879   0.6361
  -1.500   0.4039   0.01376   0.00815  -0.1469   0.8837   0.6839
  -1.250   0.4430   0.01357   0.00795  -0.1485   0.8812   0.7107
  -1.000   0.4761   0.01343   0.00777  -0.1492   0.8763   0.7273
  -0.750   0.5065   0.01331   0.00763  -0.1495   0.8700   0.7417
  -0.500   0.5461   0.01303   0.00731  -0.1515   0.8667   0.7554
  -0.250   0.5727   0.01299   0.00725  -0.1510   0.8590   0.7676
   0.000   0.6085   0.01277   0.00701  -0.1523   0.8540   0.7798
   0.250   0.6391   0.01267   0.00689  -0.1527   0.8472   0.7914
   0.500   0.6710   0.01253   0.00674  -0.1533   0.8404   0.8027
   0.750   0.6996   0.01244   0.00665  -0.1532   0.8329   0.8134
   1.000   0.7303   0.01231   0.00652  -0.1536   0.8256   0.8245
   1.250   0.7563   0.01228   0.00650  -0.1530   0.8168   0.8364
   1.500   0.7888   0.01214   0.00634  -0.1537   0.8099   0.8487
   1.750   0.8110   0.01213   0.00637  -0.1524   0.7997   0.8622
   2.000   0.8368   0.01205   0.00632  -0.1517   0.7909   0.8767
   2.250   0.8628   0.01193   0.00621  -0.1510   0.7822   0.8928
   2.500   0.8821   0.01186   0.00618  -0.1490   0.7714   0.9142
   2.750   0.9036   0.01170   0.00607  -0.1474   0.7612   0.9467
   3.000   0.9412   0.01161   0.00599  -0.1495   0.7511   1.0000
   3.250   0.9753   0.01169   0.00602  -0.1510   0.7396   1.0000
   3.500   1.0056   0.01179   0.00611  -0.1517   0.7271   1.0000
   3.750   1.0348   0.01190   0.00620  -0.1521   0.7143   1.0000
   4.000   1.0629   0.01201   0.00632  -0.1522   0.7006   1.0000
   4.250   1.0901   0.01212   0.00641  -0.1521   0.6861   1.0000
   4.500   1.1165   0.01225   0.00652  -0.1517   0.6711   1.0000
   4.750   1.1424   0.01240   0.00664  -0.1513   0.6555   1.0000
   5.000   1.1668   0.01257   0.00679  -0.1505   0.6382   1.0000
   5.250   1.1896   0.01276   0.00702  -0.1494   0.6191   1.0000
   5.500   1.2126   0.01298   0.00720  -0.1484   0.5995   1.0000
   5.750   1.2342   0.01323   0.00744  -0.1471   0.5783   1.0000
   6.000   1.2553   0.01353   0.00769  -0.1457   0.5564   1.0000
   6.250   1.2748   0.01386   0.00800  -0.1441   0.5325   1.0000
   6.500   1.2936   0.01423   0.00834  -0.1423   0.5074   1.0000
   6.750   1.3109   0.01466   0.00874  -0.1403   0.4805   1.0000
   7.000   1.3267   0.01515   0.00917  -0.1380   0.4513   1.0000
   7.250   1.3405   0.01571   0.00965  -0.1354   0.4193   1.0000
   7.500   1.3516   0.01637   0.01019  -0.1324   0.3855   1.0000
   7.750   1.3603   0.01709   0.01080  -0.1290   0.3491   1.0000
   8.000   1.3659   0.01800   0.01153  -0.1252   0.3079   1.0000
   8.250   1.3691   0.01913   0.01241  -0.1212   0.2629   1.0000
   8.500   1.3711   0.02044   0.01345  -0.1173   0.2181   1.0000
   8.750   1.3745   0.02180   0.01461  -0.1138   0.1788   1.0000
   9.000   1.3788   0.02319   0.01583  -0.1106   0.1486   1.0000
   9.250   1.3850   0.02454   0.01707  -0.1078   0.1246   1.0000
   9.500   1.3910   0.02594   0.01838  -0.1050   0.1061   1.0000
   9.750   1.3985   0.02729   0.01972  -0.1026   0.0914   1.0000
  10.000   1.4055   0.02872   0.02115  -0.1003   0.0776   1.0000
  10.250   1.4113   0.03030   0.02270  -0.0979   0.0620   1.0000
  10.500   1.4100   0.03255   0.02485  -0.0950   0.0445   1.0000
  10.750   1.4058   0.03520   0.02750  -0.0918   0.0333   1.0000
  11.000   1.4071   0.03743   0.02982  -0.0895   0.0286   1.0000
  11.250   1.3990   0.04066   0.03311  -0.0867   0.0259   1.0000
  11.500   1.4025   0.04294   0.03558  -0.0849   0.0244   1.0000
  11.750   1.4057   0.04537   0.03815  -0.0832   0.0230   1.0000
  12.000   1.4092   0.04784   0.04074  -0.0817   0.0217   1.0000
  12.250   1.4127   0.05030   0.04330  -0.0804   0.0205   1.0000
  12.500   1.4143   0.05311   0.04618  -0.0793   0.0192   1.0000
  12.750   1.4164   0.05668   0.04985  -0.0777   0.0180   1.0000
  13.000   1.4227   0.05924   0.05262  -0.0768   0.0176   1.0000
  13.250   1.4284   0.06212   0.05570  -0.0758   0.0172   1.0000
  13.500   1.4326   0.06530   0.05911  -0.0749   0.0168   1.0000
  13.750   1.4346   0.06882   0.06288  -0.0742   0.0165   1.0000
  14.000   1.4335   0.07275   0.06706  -0.0736   0.0163   1.0000
  14.250   1.4292   0.07712   0.07171  -0.0734   0.0161   1.0000
  14.500   1.4215   0.08197   0.07684  -0.0735   0.0161   1.0000
  14.750   1.4109   0.08730   0.08245  -0.0742   0.0160   1.0000
  15.000   1.3979   0.09310   0.08852  -0.0754   0.0160   1.0000
  15.250   1.3828   0.09942   0.09511  -0.0773   0.0161   1.0000
  15.500   1.3663   0.10619   0.10213  -0.0799   0.0162   1.0000
  15.750   1.3485   0.11348   0.10968  -0.0832   0.0163   1.0000
  16.000   1.3300   0.12128   0.11771  -0.0874   0.0164   1.0000
  16.250   1.3110   0.12964   0.12628  -0.0923   0.0166   1.0000
  16.500   1.2911   0.13872   0.13557  -0.0982   0.0167   1.0000
  16.750   1.2708   0.14848   0.14551  -0.1049   0.0169   1.0000
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