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

S3021-095-84 (s3021-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 50,000
Max Cl/Cd: 32.24 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3021-il-50000.txt
Download as CSV file: xf-s3021-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3930   0.10745   0.10070  -0.0162   1.0000   0.2196
  -8.500  -0.3823   0.10336   0.09665  -0.0159   1.0000   0.2269
  -8.250  -0.3995   0.10277   0.09622  -0.0176   1.0000   0.2356
  -8.000  -0.3765   0.09764   0.09107  -0.0161   1.0000   0.2460
  -7.750  -0.3752   0.09467   0.08820  -0.0161   1.0000   0.2551
  -7.500  -0.3980   0.09433   0.08805  -0.0167   1.0000   0.2650
  -7.250  -0.3811   0.09012   0.08385  -0.0153   1.0000   0.2783
  -7.000  -0.3718   0.08663   0.08042  -0.0141   1.0000   0.2905
  -6.750  -0.3705   0.08386   0.07775  -0.0127   1.0000   0.3035
  -6.500  -0.3723   0.08143   0.07541  -0.0110   1.0000   0.3183
  -6.250  -0.3776   0.07932   0.07344  -0.0092   1.0000   0.3356
  -6.000  -0.3922   0.07787   0.07216  -0.0079   1.0000   0.3529
  -5.750  -0.3732   0.07412   0.06844  -0.0042   1.0000   0.3749
  -5.500  -0.3801   0.07213   0.06660  -0.0009   1.0000   0.4003
  -5.250  -0.3893   0.07073   0.06533   0.0028   1.0000   0.4263
  -4.500  -0.3736   0.04814   0.04118  -0.0345   1.0000   0.1480
  -4.250  -0.3576   0.04396   0.03649  -0.0347   1.0000   0.1335
  -4.000  -0.3427   0.04095   0.03330  -0.0339   1.0000   0.1292
  -3.750  -0.3213   0.03755   0.02898  -0.0339   1.0000   0.1196
  -3.500  -0.3023   0.03503   0.02619  -0.0332   1.0000   0.1173
  -3.250  -0.2812   0.03276   0.02351  -0.0325   1.0000   0.1156
  -3.000  -0.2590   0.03090   0.02123  -0.0318   1.0000   0.1154
  -2.750  -0.2361   0.02932   0.01922  -0.0310   1.0000   0.1174
  -2.500  -0.2144   0.02801   0.01769  -0.0302   1.0000   0.1235
  -2.250  -0.1928   0.02706   0.01650  -0.0294   1.0000   0.1336
  -2.000  -0.1707   0.02597   0.01537  -0.0285   1.0000   0.1472
  -1.750  -0.1469   0.02486   0.01437  -0.0278   1.0000   0.1804
  -1.500  -0.1069   0.01997   0.01294  -0.0274   1.0000   1.0000
  -1.250  -0.0887   0.02038   0.01273  -0.0268   1.0000   1.0000
  -1.000  -0.0711   0.02084   0.01272  -0.0262   1.0000   1.0000
  -0.750  -0.0537   0.02133   0.01285  -0.0257   1.0000   1.0000
  -0.500  -0.0174   0.02218   0.01328  -0.0288   0.9925   1.0000
  -0.250   0.0284   0.02317   0.01386  -0.0335   0.9798   1.0000
   0.000   0.0723   0.02411   0.01449  -0.0379   0.9668   1.0000
   0.250   0.1148   0.02502   0.01514  -0.0418   0.9538   1.0000
   0.500   0.1564   0.02588   0.01577  -0.0454   0.9406   1.0000
   0.750   0.1977   0.02671   0.01641  -0.0489   0.9273   1.0000
   1.000   0.2384   0.02750   0.01706  -0.0522   0.9138   1.0000
   1.250   0.2768   0.02824   0.01768  -0.0549   0.9000   1.0000
   1.500   0.3129   0.02895   0.01831  -0.0571   0.8858   1.0000
   1.750   0.3486   0.02965   0.01895  -0.0591   0.8715   1.0000
   2.000   0.3843   0.03032   0.01958  -0.0610   0.8570   1.0000
   2.250   0.4203   0.03096   0.02021  -0.0628   0.8423   1.0000
   2.500   0.4568   0.03155   0.02081  -0.0645   0.8275   1.0000
   2.750   0.4927   0.03210   0.02139  -0.0659   0.8125   1.0000
   3.000   0.5215   0.03276   0.02208  -0.0663   0.7965   1.0000
   3.250   0.5510   0.03337   0.02274  -0.0666   0.7802   1.0000
   3.500   0.5811   0.03393   0.02339  -0.0668   0.7638   1.0000
   3.750   0.6118   0.03442   0.02395  -0.0669   0.7476   1.0000
   4.000   0.6437   0.03478   0.02441  -0.0668   0.7311   1.0000
   4.250   0.6773   0.03498   0.02475  -0.0667   0.7147   1.0000
   4.500   0.7121   0.03500   0.02489  -0.0664   0.6985   1.0000
   4.750   0.7476   0.03485   0.02487  -0.0659   0.6823   1.0000
   5.000   0.7639   0.03571   0.02583  -0.0639   0.6623   1.0000
   5.250   0.7928   0.03577   0.02606  -0.0626   0.6438   1.0000
   5.500   0.8274   0.03532   0.02576  -0.0614   0.6262   1.0000
   5.750   0.8553   0.03525   0.02582  -0.0597   0.6068   1.0000
   6.000   0.8792   0.03539   0.02611  -0.0578   0.5858   1.0000
   6.250   0.9179   0.03429   0.02516  -0.0563   0.5666   1.0000
   6.500   0.9360   0.03482   0.02585  -0.0541   0.5432   1.0000
   6.750   0.9691   0.03404   0.02516  -0.0522   0.5210   1.0000
   7.000   0.9961   0.03374   0.02500  -0.0502   0.4965   1.0000
   7.250   1.0193   0.03377   0.02514  -0.0481   0.4706   1.0000
   7.500   1.0443   0.03367   0.02511  -0.0460   0.4436   1.0000
   7.750   1.0685   0.03372   0.02520  -0.0439   0.4156   1.0000
   8.000   1.0911   0.03398   0.02546  -0.0418   0.3865   1.0000
   8.250   1.1121   0.03449   0.02600  -0.0397   0.3570   1.0000
   8.500   1.1316   0.03528   0.02676  -0.0376   0.3277   1.0000
   8.750   1.1498   0.03625   0.02769  -0.0355   0.2984   1.0000
   9.000   1.1665   0.03740   0.02876  -0.0333   0.2688   1.0000
   9.250   1.1829   0.03868   0.02984  -0.0312   0.2380   1.0000
   9.500   1.1901   0.04035   0.03157  -0.0283   0.2081   1.0000
   9.750   1.1887   0.04150   0.03266  -0.0247   0.1769   1.0000
  10.000   1.1849   0.04294   0.03395  -0.0212   0.1487   1.0000
  10.250   1.1845   0.04537   0.03623  -0.0182   0.1243   1.0000
  10.500   1.1876   0.04828   0.03920  -0.0157   0.1076   1.0000
  10.750   1.1961   0.05197   0.04306  -0.0139   0.0973   1.0000
  11.000   1.2107   0.05560   0.04663  -0.0129   0.0889   1.0000
  11.250   1.2008   0.05912   0.05067  -0.0100   0.0866   1.0000
  11.500   1.1892   0.06277   0.05469  -0.0075   0.0850   1.0000
  11.750   1.1749   0.06644   0.05865  -0.0056   0.0832   1.0000
  12.000   1.1575   0.07069   0.06318  -0.0045   0.0827   1.0000
  12.250   1.1335   0.07583   0.06861  -0.0046   0.0837   1.0000
  12.500   1.1062   0.08172   0.07473  -0.0061   0.0846   1.0000
  12.750   1.0805   0.08845   0.08164  -0.0087   0.0865   1.0000
  13.000   1.0581   0.09557   0.08887  -0.0118   0.0880   1.0000
  13.250   1.0355   0.10335   0.09673  -0.0157   0.0890   1.0000
<< Back to S3021-095-84 (s3021-il)

Polar data table (+)

Polar graphs


<< Back to S3021-095-84 (s3021-il)