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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 50,000
Max Cl/Cd: 37.55 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3021-il-50000-n5.txt
Download as CSV file: xf-s3021-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3998   0.09050   0.08374  -0.0316   1.0000   0.0580
  -8.000  -0.3987   0.08698   0.08029  -0.0323   1.0000   0.0561
  -7.750  -0.4019   0.08339   0.07681  -0.0336   1.0000   0.0544
  -7.500  -0.4054   0.07925   0.07276  -0.0360   1.0000   0.0525
  -7.000  -0.4193   0.06739   0.06076  -0.0449   1.0000   0.0470
  -6.750  -0.4158   0.06411   0.05749  -0.0444   1.0000   0.0465
  -6.500  -0.4133   0.06061   0.05395  -0.0441   1.0000   0.0460
  -6.250  -0.4104   0.05710   0.05035  -0.0438   1.0000   0.0455
  -6.000  -0.4067   0.05365   0.04675  -0.0432   1.0000   0.0450
  -5.750  -0.4019   0.05027   0.04318  -0.0424   1.0000   0.0446
  -5.500  -0.3954   0.04709   0.03974  -0.0413   1.0000   0.0442
  -5.250  -0.3872   0.04406   0.03642  -0.0402   1.0000   0.0439
  -5.000  -0.3771   0.04120   0.03321  -0.0389   1.0000   0.0438
  -4.750  -0.3649   0.03860   0.03020  -0.0377   1.0000   0.0444
  -4.500  -0.3507   0.03630   0.02744  -0.0364   1.0000   0.0456
  -4.250  -0.3139   0.03359   0.02400  -0.0389   0.9915   0.0474
  -4.000  -0.2779   0.03103   0.02108  -0.0414   0.9833   0.0491
  -3.750  -0.2422   0.02905   0.01877  -0.0431   0.9742   0.0507
  -3.500  -0.2061   0.02742   0.01684  -0.0447   0.9652   0.0530
  -3.250  -0.1677   0.02600   0.01513  -0.0465   0.9572   0.0563
  -2.750  -0.0963   0.02388   0.01260  -0.0495   0.9378   0.0745
  -2.500  -0.0580   0.02267   0.01148  -0.0516   0.9295   0.1040
  -2.250  -0.0278   0.02079   0.01088  -0.0531   0.9196   0.3154
  -2.000  -0.0035   0.01892   0.01087  -0.0510   0.9123   0.7123
  -1.750   0.0871   0.01847   0.01008  -0.0619   0.9113   1.0000
  -1.500   0.1246   0.01850   0.00968  -0.0639   0.9006   1.0000
  -1.250   0.1568   0.01857   0.00939  -0.0649   0.8883   1.0000
  -1.000   0.1883   0.01866   0.00918  -0.0657   0.8762   1.0000
  -0.750   0.2194   0.01876   0.00901  -0.0663   0.8645   1.0000
  -0.500   0.2508   0.01885   0.00886  -0.0669   0.8532   1.0000
  -0.250   0.2829   0.01893   0.00872  -0.0676   0.8428   1.0000
   0.000   0.3094   0.01910   0.00871  -0.0673   0.8303   1.0000
   0.250   0.3358   0.01927   0.00873  -0.0669   0.8181   1.0000
   0.500   0.3623   0.01945   0.00877  -0.0666   0.8062   1.0000
   0.750   0.3892   0.01963   0.00882  -0.0662   0.7948   1.0000
   1.000   0.4174   0.01977   0.00884  -0.0660   0.7840   1.0000
   1.250   0.4432   0.01997   0.00896  -0.0654   0.7720   1.0000
   1.500   0.4678   0.02021   0.00913  -0.0647   0.7596   1.0000
   1.750   0.4927   0.02045   0.00931  -0.0639   0.7473   1.0000
   2.000   0.5178   0.02067   0.00950  -0.0632   0.7350   1.0000
   2.250   0.5432   0.02088   0.00967  -0.0625   0.7229   1.0000
   2.500   0.5690   0.02108   0.00984  -0.0617   0.7108   1.0000
   2.750   0.5950   0.02125   0.01001  -0.0610   0.6988   1.0000
   3.000   0.6189   0.02150   0.01028  -0.0600   0.6854   1.0000
   3.250   0.6429   0.02176   0.01055  -0.0591   0.6719   1.0000
   3.500   0.6669   0.02201   0.01083  -0.0581   0.6581   1.0000
   3.750   0.6909   0.02226   0.01111  -0.0571   0.6442   1.0000
   4.000   0.7148   0.02250   0.01144  -0.0561   0.6300   1.0000
   4.250   0.7388   0.02274   0.01174  -0.0551   0.6155   1.0000
   4.500   0.7626   0.02298   0.01203  -0.0540   0.6006   1.0000
   4.750   0.7866   0.02320   0.01232  -0.0529   0.5853   1.0000
   5.000   0.8099   0.02344   0.01268  -0.0518   0.5692   1.0000
   5.250   0.8317   0.02377   0.01311  -0.0505   0.5515   1.0000
   5.500   0.8541   0.02405   0.01349  -0.0493   0.5336   1.0000
   5.750   0.8771   0.02428   0.01380  -0.0480   0.5155   1.0000
   6.000   0.8991   0.02457   0.01424  -0.0467   0.4963   1.0000
   6.250   0.9201   0.02493   0.01470  -0.0453   0.4756   1.0000
   6.500   0.9419   0.02523   0.01506  -0.0439   0.4553   1.0000
   6.750   0.9616   0.02569   0.01563  -0.0424   0.4327   1.0000
   7.000   0.9816   0.02614   0.01614  -0.0409   0.4104   1.0000
   7.250   1.0006   0.02666   0.01679  -0.0393   0.3872   1.0000
   7.500   1.0183   0.02731   0.01752  -0.0376   0.3633   1.0000
   7.750   1.0354   0.02801   0.01825  -0.0359   0.3398   1.0000
   8.000   1.0514   0.02880   0.01908  -0.0342   0.3164   1.0000
   8.250   1.0661   0.02973   0.02009  -0.0324   0.2931   1.0000
   8.500   1.0799   0.03071   0.02109  -0.0306   0.2713   1.0000
   8.750   1.0923   0.03184   0.02237  -0.0287   0.2496   1.0000
   9.000   1.1030   0.03303   0.02359  -0.0267   0.2291   1.0000
   9.250   1.1120   0.03436   0.02503  -0.0246   0.2088   1.0000
   9.500   1.1184   0.03576   0.02643  -0.0223   0.1901   1.0000
   9.750   1.1217   0.03731   0.02807  -0.0199   0.1717   1.0000
  10.000   1.1206   0.03901   0.02982  -0.0173   0.1534   1.0000
  10.250   1.1153   0.04101   0.03175  -0.0151   0.1357   1.0000
  10.500   1.1092   0.04341   0.03418  -0.0136   0.1153   1.0000
  10.750   1.1022   0.04620   0.03691  -0.0129   0.0977   1.0000
  11.000   1.0960   0.04935   0.04002  -0.0125   0.0821   1.0000
  11.250   1.0897   0.05281   0.04347  -0.0123   0.0710   1.0000
  11.500   1.0849   0.05638   0.04715  -0.0121   0.0619   1.0000
  11.750   1.0790   0.06025   0.05109  -0.0121   0.0551   1.0000
  12.000   1.0754   0.06391   0.05483  -0.0123   0.0510   1.0000
  12.250   1.0705   0.06787   0.05890  -0.0127   0.0472   1.0000
  12.500   1.0687   0.07169   0.06295  -0.0130   0.0438   1.0000
  12.750   1.0659   0.07559   0.06701  -0.0137   0.0415   1.0000
  13.000   1.0613   0.07974   0.07121  -0.0147   0.0394   1.0000
  13.250   1.0565   0.08423   0.07583  -0.0159   0.0375   1.0000
  13.500   1.0517   0.08906   0.08096  -0.0173   0.0364   1.0000
  13.750   1.0443   0.09450   0.08666  -0.0193   0.0354   1.0000
  14.000   1.0348   0.10050   0.09291  -0.0218   0.0347   1.0000
  14.250   1.0236   0.10717   0.09981  -0.0250   0.0344   1.0000
  14.500   1.0092   0.11488   0.10774  -0.0290   0.0343   1.0000
  14.750   0.9926   0.12368   0.11674  -0.0338   0.0347   1.0000
  15.000   0.9728   0.13401   0.12721  -0.0396   0.0354   1.0000
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