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S4022 (s4022-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 500,000
Max Cl/Cd: 129.81 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4022-il-500000.txt
Download as CSV file: xf-s4022-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3047   0.10268   0.10047  -0.0537   0.9920   0.0166
  -9.250  -0.2935   0.09788   0.09568  -0.0580   0.9894   0.0167
  -9.000  -0.2935   0.09077   0.08859  -0.0626   0.9871   0.0173
  -8.750  -0.2785   0.08738   0.08520  -0.0660   0.9855   0.0178
  -8.500  -0.2619   0.08377   0.08158  -0.0703   0.9841   0.0183
  -8.250  -0.2528   0.08030   0.07812  -0.0731   0.9787   0.0190
  -8.000  -0.2393   0.07582   0.07365  -0.0784   0.9753   0.0200
  -7.750  -0.2244   0.07027   0.06811  -0.0859   0.9726   0.0208
  -7.500  -0.2215   0.06494   0.06279  -0.0913   0.9633   0.0213
  -5.250   0.0335   0.01680   0.01157  -0.1498   0.9255   0.0248
  -5.000   0.0727   0.01608   0.01073  -0.1522   0.9235   0.0241
  -4.750   0.1113   0.01439   0.00886  -0.1547   0.9215   0.0242
  -4.500   0.1416   0.01364   0.00803  -0.1553   0.9158   0.0239
  -4.250   0.1751   0.01200   0.00629  -0.1567   0.9112   0.0233
  -4.000   0.2133   0.01104   0.00523  -0.1591   0.9077   0.0233
  -3.750   0.2432   0.01045   0.00457  -0.1597   0.9008   0.0236
  -3.500   0.2785   0.00974   0.00375  -0.1615   0.8954   0.0249
  -3.250   0.3108   0.00931   0.00322  -0.1625   0.8889   0.0270
  -3.000   0.3425   0.00905   0.00290  -0.1634   0.8821   0.0296
  -2.750   0.3735   0.00887   0.00265  -0.1641   0.8752   0.0336
  -2.500   0.4055   0.00817   0.00237  -0.1655   0.8680   0.1622
  -2.250   0.4369   0.00737   0.00221  -0.1671   0.8607   0.3826
  -2.000   0.4672   0.00709   0.00222  -0.1678   0.8534   0.4974
  -1.750   0.4954   0.00706   0.00225  -0.1679   0.8455   0.5473
  -1.500   0.5250   0.00708   0.00227  -0.1682   0.8382   0.5893
  -1.250   0.5519   0.00710   0.00231  -0.1679   0.8299   0.6094
  -1.000   0.5811   0.00717   0.00235  -0.1680   0.8228   0.6356
  -0.750   0.6072   0.00721   0.00240  -0.1676   0.8141   0.6523
  -0.500   0.6355   0.00726   0.00240  -0.1676   0.8065   0.6630
  -0.250   0.6627   0.00730   0.00241  -0.1674   0.7981   0.6730
   0.000   0.6897   0.00734   0.00244  -0.1672   0.7897   0.6820
   0.250   0.7177   0.00740   0.00245  -0.1671   0.7816   0.6914
   0.500   0.7438   0.00743   0.00250  -0.1667   0.7724   0.7002
   0.750   0.7709   0.00748   0.00253  -0.1665   0.7637   0.7084
   1.000   0.7979   0.00755   0.00257  -0.1663   0.7545   0.7173
   1.250   0.8238   0.00758   0.00263  -0.1659   0.7447   0.7253
   1.500   0.8504   0.00765   0.00267  -0.1656   0.7351   0.7342
   1.750   0.8767   0.00772   0.00274  -0.1652   0.7249   0.7432
   2.000   0.9021   0.00778   0.00281  -0.1647   0.7135   0.7523
   2.250   0.9278   0.00785   0.00289  -0.1642   0.7020   0.7625
   2.500   0.9531   0.00793   0.00297  -0.1637   0.6904   0.7727
   2.750   0.9781   0.00801   0.00308  -0.1630   0.6781   0.7834
   3.000   1.0026   0.00810   0.00318  -0.1623   0.6645   0.7951
   3.250   1.0266   0.00821   0.00329  -0.1615   0.6498   0.8080
   3.500   1.0503   0.00831   0.00341  -0.1606   0.6351   0.8224
   3.750   1.0733   0.00843   0.00356  -0.1595   0.6198   0.8387
   4.000   1.0952   0.00856   0.00370  -0.1583   0.6028   0.8583
   4.250   1.1150   0.00868   0.00384  -0.1565   0.5854   0.8831
   4.500   1.1300   0.00874   0.00394  -0.1536   0.5682   0.9278
   4.750   1.1527   0.00888   0.00406  -0.1526   0.5478   1.0000
   5.250   1.1986   0.00947   0.00451  -0.1510   0.5038   1.0000
   5.500   1.2202   0.00981   0.00477  -0.1499   0.4799   1.0000
   5.750   1.2410   0.01019   0.00505  -0.1486   0.4546   1.0000
   6.000   1.2604   0.01062   0.00537  -0.1471   0.4238   1.0000
   6.250   1.2783   0.01114   0.00573  -0.1454   0.3886   1.0000
   6.500   1.2951   0.01171   0.00614  -0.1434   0.3519   1.0000
   6.750   1.3095   0.01237   0.00662  -0.1411   0.3118   1.0000
   7.000   1.3230   0.01311   0.00714  -0.1386   0.2706   1.0000
   7.250   1.3352   0.01394   0.00774  -0.1360   0.2275   1.0000
   7.500   1.3480   0.01477   0.00837  -0.1335   0.1900   1.0000
   7.750   1.3611   0.01558   0.00901  -0.1312   0.1584   1.0000
   8.000   1.3739   0.01640   0.00969  -0.1288   0.1306   1.0000
   8.250   1.3862   0.01726   0.01041  -0.1264   0.1054   1.0000
   8.500   1.3988   0.01810   0.01115  -0.1241   0.0852   1.0000
   8.750   1.4121   0.01890   0.01189  -0.1219   0.0711   1.0000
   9.000   1.4252   0.01970   0.01266  -0.1198   0.0591   1.0000
   9.250   1.4372   0.02060   0.01350  -0.1175   0.0465   1.0000
   9.500   1.4458   0.02173   0.01455  -0.1148   0.0296   1.0000
   9.750   1.4506   0.02319   0.01592  -0.1116   0.0168   1.0000
  10.000   1.4585   0.02445   0.01720  -0.1090   0.0135   1.0000
  10.250   1.4672   0.02569   0.01854  -0.1065   0.0118   1.0000
  10.500   1.4769   0.02687   0.01981  -0.1044   0.0110   1.0000
  10.750   1.4851   0.02820   0.02126  -0.1021   0.0103   1.0000
  11.000   1.4918   0.02968   0.02284  -0.0999   0.0097   1.0000
  11.250   1.4959   0.03143   0.02469  -0.0975   0.0092   1.0000
  11.500   1.4957   0.03362   0.02701  -0.0949   0.0087   1.0000
  11.750   1.4909   0.03634   0.02988  -0.0921   0.0084   1.0000
  12.000   1.4928   0.03855   0.03221  -0.0901   0.0081   1.0000
  12.250   1.4980   0.04050   0.03428  -0.0886   0.0079   1.0000
  12.500   1.5018   0.04265   0.03655  -0.0872   0.0076   1.0000
  12.750   1.5043   0.04503   0.03904  -0.0859   0.0073   1.0000
  13.000   1.5061   0.04758   0.04171  -0.0847   0.0070   1.0000
  13.250   1.5062   0.05039   0.04466  -0.0836   0.0068   1.0000
  13.500   1.5058   0.05340   0.04779  -0.0827   0.0066   1.0000
  13.750   1.5049   0.05657   0.05109  -0.0820   0.0065   1.0000
  14.000   1.5033   0.05994   0.05461  -0.0815   0.0063   1.0000
  14.250   1.5012   0.06349   0.05830  -0.0812   0.0062   1.0000
  14.500   1.4983   0.06727   0.06221  -0.0811   0.0061   1.0000
  14.750   1.4947   0.07129   0.06636  -0.0812   0.0060   1.0000
  15.000   1.4901   0.07556   0.07078  -0.0816   0.0059   1.0000
  15.250   1.4844   0.08014   0.07551  -0.0822   0.0058   1.0000
  15.500   1.4781   0.08498   0.08050  -0.0831   0.0057   1.0000
  15.750   1.4696   0.09029   0.08598  -0.0843   0.0056   1.0000
  16.000   1.4616   0.09566   0.09152  -0.0858   0.0055   1.0000
  16.250   1.4509   0.10167   0.09772  -0.0877   0.0055   1.0000
  16.500   1.4411   0.10770   0.10393  -0.0900   0.0055   1.0000
  16.750   1.4301   0.11408   0.11050  -0.0927   0.0054   1.0000
  17.000   1.4195   0.12055   0.11715  -0.0958   0.0054   1.0000
  17.250   1.4086   0.12728   0.12405  -0.0993   0.0054   1.0000
  17.500   1.3945   0.13488   0.13184  -0.1036   0.0054   1.0000
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