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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 100,000
Max Cl/Cd: 55.06 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3021-il-100000-n5.txt
Download as CSV file: xf-s3021-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3021-095-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4035   0.08734   0.08250  -0.0330   1.0000   0.0351
  -8.250  -0.3995   0.08431   0.07950  -0.0324   1.0000   0.0338
  -8.000  -0.4011   0.08080   0.07607  -0.0334   1.0000   0.0326
  -7.750  -0.4070   0.07718   0.07254  -0.0347   1.0000   0.0316
  -7.500  -0.4126   0.07274   0.06816  -0.0374   1.0000   0.0304
  -7.250  -0.4271   0.06169   0.05696  -0.0462   1.0000   0.0269
  -7.000  -0.4279   0.05802   0.05327  -0.0460   1.0000   0.0266
  -6.750  -0.4276   0.05460   0.04976  -0.0454   1.0000   0.0264
  -6.500  -0.4286   0.05053   0.04548  -0.0448   1.0000   0.0266
  -6.250  -0.4286   0.04685   0.04150  -0.0436   1.0000   0.0269
  -5.750  -0.3834   0.03779   0.03161  -0.0488   0.9856   0.0274
  -5.500  -0.3521   0.03435   0.02755  -0.0510   0.9763   0.0269
  -5.250  -0.3207   0.03100   0.02371  -0.0531   0.9680   0.0268
  -5.000  -0.2885   0.02819   0.02042  -0.0547   0.9593   0.0268
  -4.750  -0.2562   0.02590   0.01768  -0.0559   0.9502   0.0269
  -4.500  -0.2212   0.02374   0.01517  -0.0575   0.9430   0.0272
  -4.250  -0.1907   0.02203   0.01325  -0.0582   0.9325   0.0277
  -4.000  -0.1588   0.02067   0.01175  -0.0590   0.9227   0.0286
  -3.750  -0.1251   0.01962   0.01061  -0.0601   0.9141   0.0310
  -3.500  -0.0947   0.01881   0.00967  -0.0605   0.9027   0.0341
  -3.250  -0.0648   0.01795   0.00866  -0.0607   0.8915   0.0362
  -3.000  -0.0352   0.01710   0.00772  -0.0609   0.8807   0.0393
  -2.750  -0.0044   0.01646   0.00693  -0.0612   0.8704   0.0452
  -2.500   0.0239   0.01574   0.00624  -0.0610   0.8588   0.0636
  -2.250   0.0499   0.01479   0.00581  -0.0608   0.8470   0.1794
  -2.000   0.0740   0.01374   0.00565  -0.0605   0.8357   0.3934
  -1.750   0.0949   0.01268   0.00560  -0.0585   0.8252   0.6541
  -1.500   0.1551   0.01210   0.00546  -0.0630   0.8173   0.9211
  -1.250   0.2135   0.01203   0.00510  -0.0688   0.8077   0.9887
  -1.000   0.2484   0.01202   0.00485  -0.0703   0.7963   1.0000
  -0.750   0.2730   0.01207   0.00467  -0.0695   0.7848   1.0000
  -0.500   0.2970   0.01215   0.00458  -0.0687   0.7727   1.0000
  -0.250   0.3211   0.01224   0.00451  -0.0679   0.7610   1.0000
   0.000   0.3454   0.01234   0.00445  -0.0670   0.7497   1.0000
   0.250   0.3698   0.01244   0.00441  -0.0662   0.7389   1.0000
   0.500   0.3943   0.01255   0.00438  -0.0654   0.7282   1.0000
   0.750   0.4184   0.01268   0.00441  -0.0646   0.7165   1.0000
   1.000   0.4426   0.01281   0.00444  -0.0638   0.7051   1.0000
   1.250   0.4671   0.01294   0.00448  -0.0630   0.6940   1.0000
   1.500   0.4917   0.01307   0.00451  -0.0622   0.6831   1.0000
   1.750   0.5161   0.01321   0.00459  -0.0614   0.6714   1.0000
   2.000   0.5405   0.01336   0.00469  -0.0606   0.6594   1.0000
   2.250   0.5650   0.01351   0.00480  -0.0598   0.6475   1.0000
   2.500   0.5896   0.01367   0.00491  -0.0591   0.6358   1.0000
   2.750   0.6142   0.01382   0.00505  -0.0583   0.6238   1.0000
   3.000   0.6389   0.01399   0.00517  -0.0576   0.6118   1.0000
   3.250   0.6635   0.01415   0.00532  -0.0568   0.5991   1.0000
   3.500   0.6878   0.01433   0.00550  -0.0560   0.5856   1.0000
   3.750   0.7122   0.01451   0.00571  -0.0553   0.5718   1.0000
   4.000   0.7365   0.01470   0.00590  -0.0545   0.5574   1.0000
   4.250   0.7607   0.01489   0.00610  -0.0537   0.5425   1.0000
   4.500   0.7847   0.01510   0.00632  -0.0529   0.5269   1.0000
   4.750   0.8084   0.01533   0.00661  -0.0520   0.5098   1.0000
   5.000   0.8320   0.01556   0.00687  -0.0511   0.4919   1.0000
   5.250   0.8553   0.01582   0.00714  -0.0502   0.4735   1.0000
   5.500   0.8783   0.01610   0.00744  -0.0493   0.4541   1.0000
   5.750   0.9010   0.01642   0.00781  -0.0483   0.4332   1.0000
   6.000   0.9232   0.01677   0.00816  -0.0473   0.4119   1.0000
   6.250   0.9449   0.01716   0.00856  -0.0462   0.3891   1.0000
   6.500   0.9662   0.01760   0.00901  -0.0451   0.3659   1.0000
   6.750   0.9868   0.01810   0.00948  -0.0440   0.3423   1.0000
   7.000   1.0070   0.01863   0.01006  -0.0428   0.3183   1.0000
   7.250   1.0267   0.01922   0.01065  -0.0416   0.2949   1.0000
   7.500   1.0454   0.01988   0.01129  -0.0402   0.2726   1.0000
   7.750   1.0640   0.02055   0.01200  -0.0390   0.2494   1.0000
   8.000   1.0809   0.02132   0.01274  -0.0375   0.2230   1.0000
   8.250   1.0964   0.02218   0.01353  -0.0360   0.1947   1.0000
   8.500   1.1109   0.02312   0.01443  -0.0344   0.1661   1.0000
   8.750   1.1246   0.02412   0.01536  -0.0327   0.1395   1.0000
   9.000   1.1366   0.02526   0.01639  -0.0310   0.1116   1.0000
   9.250   1.1461   0.02660   0.01754  -0.0290   0.0813   1.0000
   9.500   1.1539   0.02805   0.01888  -0.0269   0.0562   1.0000
  10.000   1.1590   0.03140   0.02214  -0.0213   0.0301   1.0000
  10.250   1.1608   0.03316   0.02400  -0.0187   0.0262   1.0000
  10.500   1.1623   0.03500   0.02599  -0.0165   0.0237   1.0000
  10.750   1.1621   0.03707   0.02823  -0.0146   0.0221   1.0000
  11.250   1.1580   0.04193   0.03338  -0.0118   0.0202   1.0000
  11.500   1.1577   0.04441   0.03606  -0.0109   0.0192   1.0000
  11.750   1.1562   0.04717   0.03898  -0.0104   0.0182   1.0000
  12.000   1.1549   0.05001   0.04199  -0.0101   0.0178   1.0000
  12.250   1.1522   0.05314   0.04525  -0.0102   0.0168   1.0000
  12.500   1.1485   0.05652   0.04876  -0.0105   0.0162   1.0000
  12.750   1.1451   0.05999   0.05237  -0.0109   0.0160   1.0000
  13.000   1.1382   0.06401   0.05651  -0.0117   0.0155   1.0000
  13.250   1.1346   0.06780   0.06045  -0.0124   0.0152   1.0000
  13.500   1.1315   0.07160   0.06443  -0.0131   0.0151   1.0000
  13.750   1.1279   0.07563   0.06863  -0.0141   0.0149   1.0000
  14.000   1.1234   0.07992   0.07311  -0.0153   0.0148   1.0000
  14.250   1.1181   0.08452   0.07790  -0.0169   0.0147   1.0000
  14.500   1.1106   0.08966   0.08326  -0.0188   0.0145   1.0000
  14.750   1.1031   0.09502   0.08881  -0.0211   0.0145   1.0000
  15.000   1.0930   0.10111   0.09510  -0.0240   0.0144   1.0000
  15.250   1.0823   0.10756   0.10174  -0.0274   0.0144   1.0000
  15.500   1.0704   0.11456   0.10893  -0.0312   0.0144   1.0000
  15.750   1.0566   0.12234   0.11688  -0.0356   0.0144   1.0000
  16.000   1.0427   0.13049   0.12520  -0.0404   0.0145   1.0000
  16.250   1.0282   0.13923   0.13408  -0.0456   0.0147   1.0000
  16.500   1.0117   0.14902   0.14400  -0.0514   0.0148   1.0000
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