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S3021-095-84 (s3021-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S3021-095-84 (s3021-il)
Reynolds number: 500,000
Max Cl/Cd: 91.64 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3021-il-500000-n5.txt
Download as CSV file: xf-s3021-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4111   0.08564   0.08342  -0.0283   1.0000   0.0061
  -8.750  -0.4162   0.08059   0.07841  -0.0305   1.0000   0.0064
  -8.500  -0.4197   0.07669   0.07454  -0.0322   1.0000   0.0062
  -8.250  -0.4278   0.07242   0.07033  -0.0340   1.0000   0.0063
  -8.000  -0.4425   0.06814   0.06610  -0.0357   1.0000   0.0064
  -7.750  -0.4487   0.06342   0.06140  -0.0393   0.9998   0.0061
  -7.500  -0.4367   0.05040   0.04820  -0.0541   0.9856   0.0063
  -7.250  -0.4360   0.03234   0.02938  -0.0634   0.9687   0.0065
  -7.000  -0.4226   0.02546   0.02176  -0.0648   0.9528   0.0064
  -6.750  -0.4023   0.02157   0.01727  -0.0650   0.9366   0.0065
  -6.500  -0.3793   0.01906   0.01429  -0.0647   0.9189   0.0065
  -6.000  -0.3323   0.01610   0.01062  -0.0633   0.8806   0.0067
  -5.750  -0.3101   0.01460   0.00882  -0.0623   0.8620   0.0070
  -5.500  -0.2864   0.01374   0.00775  -0.0615   0.8444   0.0073
  -5.250  -0.2617   0.01315   0.00702  -0.0609   0.8282   0.0077
  -5.000  -0.2366   0.01265   0.00637  -0.0603   0.8129   0.0082
  -4.750  -0.2113   0.01216   0.00574  -0.0597   0.7987   0.0087
  -4.500  -0.1858   0.01169   0.00512  -0.0592   0.7852   0.0093
  -4.000  -0.1342   0.01086   0.00406  -0.0582   0.7600   0.0111
  -3.750  -0.1080   0.01055   0.00367  -0.0579   0.7484   0.0124
  -3.500  -0.0815   0.01026   0.00328  -0.0575   0.7373   0.0136
  -3.250  -0.0549   0.01002   0.00292  -0.0571   0.7269   0.0152
  -3.000  -0.0283   0.00974   0.00258  -0.0568   0.7165   0.0188
  -2.750  -0.0014   0.00952   0.00233  -0.0565   0.7067   0.0266
  -2.500   0.0252   0.00929   0.00212  -0.0562   0.6972   0.0449
  -2.250   0.0518   0.00905   0.00194  -0.0560   0.6878   0.0760
  -2.000   0.0786   0.00884   0.00181  -0.0558   0.6786   0.1104
  -1.750   0.1050   0.00859   0.00169  -0.0556   0.6698   0.1620
  -1.500   0.1311   0.00828   0.00160  -0.0554   0.6606   0.2395
  -1.250   0.1576   0.00806   0.00152  -0.0552   0.6516   0.3021
  -1.000   0.1840   0.00787   0.00146  -0.0549   0.6428   0.3634
  -0.750   0.2099   0.00760   0.00142  -0.0546   0.6332   0.4493
  -0.500   0.2351   0.00730   0.00139  -0.0542   0.6238   0.5476
  -0.250   0.2592   0.00699   0.00137  -0.0534   0.6143   0.6562
   0.000   0.2820   0.00666   0.00139  -0.0521   0.6044   0.7715
   0.250   0.3060   0.00641   0.00146  -0.0508   0.5950   0.8896
   0.500   0.3474   0.00646   0.00149  -0.0534   0.5843   0.9537
   0.750   0.3855   0.00654   0.00149  -0.0555   0.5732   0.9750
   1.000   0.4228   0.00661   0.00149  -0.0575   0.5620   0.9862
   1.250   0.4605   0.00668   0.00149  -0.0597   0.5506   0.9942
   1.500   0.4988   0.00676   0.00149  -0.0621   0.5382   1.0000
   1.750   0.5236   0.00685   0.00152  -0.0614   0.5270   1.0000
   2.000   0.5484   0.00696   0.00157  -0.0608   0.5147   1.0000
   2.500   0.5980   0.00719   0.00168  -0.0595   0.4886   1.0000
   2.750   0.6227   0.00732   0.00175  -0.0589   0.4742   1.0000
   3.000   0.6474   0.00747   0.00185  -0.0582   0.4589   1.0000
   3.250   0.6720   0.00762   0.00195  -0.0576   0.4430   1.0000
   3.500   0.6965   0.00779   0.00206  -0.0569   0.4262   1.0000
   3.750   0.7208   0.00798   0.00218  -0.0563   0.4089   1.0000
   4.000   0.7450   0.00819   0.00234  -0.0556   0.3905   1.0000
   4.250   0.7693   0.00841   0.00249  -0.0549   0.3714   1.0000
   4.500   0.7934   0.00866   0.00266  -0.0543   0.3509   1.0000
   4.750   0.8174   0.00892   0.00285  -0.0536   0.3303   1.0000
   5.000   0.8413   0.00921   0.00308  -0.0529   0.3089   1.0000
   5.250   0.8651   0.00951   0.00330  -0.0523   0.2891   1.0000
   5.500   0.8890   0.00981   0.00354  -0.0517   0.2691   1.0000
   5.750   0.9127   0.01014   0.00381  -0.0510   0.2503   1.0000
   6.000   0.9364   0.01047   0.00409  -0.0504   0.2316   1.0000
   6.250   0.9599   0.01081   0.00438  -0.0497   0.2130   1.0000
   6.500   0.9829   0.01121   0.00471  -0.0490   0.1933   1.0000
   6.750   1.0060   0.01160   0.00504  -0.0484   0.1740   1.0000
   7.000   1.0287   0.01201   0.00540  -0.0476   0.1563   1.0000
   7.250   1.0512   0.01245   0.00580  -0.0469   0.1398   1.0000
   7.500   1.0733   0.01291   0.00621  -0.0461   0.1222   1.0000
   7.750   1.0938   0.01351   0.00669  -0.0451   0.0998   1.0000
   8.000   1.1142   0.01410   0.00719  -0.0441   0.0800   1.0000
   8.250   1.1343   0.01470   0.00772  -0.0431   0.0648   1.0000
   8.500   1.1543   0.01529   0.00829  -0.0421   0.0521   1.0000
   8.750   1.1737   0.01592   0.00887  -0.0409   0.0402   1.0000
   9.000   1.1925   0.01656   0.00949  -0.0397   0.0303   1.0000
   9.250   1.2101   0.01728   0.01018  -0.0384   0.0211   1.0000
   9.500   1.2258   0.01811   0.01098  -0.0368   0.0129   1.0000
   9.750   1.2420   0.01886   0.01176  -0.0353   0.0096   1.0000
  10.000   1.2567   0.01968   0.01261  -0.0335   0.0076   1.0000
  10.250   1.2720   0.02037   0.01340  -0.0318   0.0069   1.0000
  10.500   1.2841   0.02111   0.01425  -0.0296   0.0063   1.0000
  10.750   1.2940   0.02195   0.01516  -0.0272   0.0057   1.0000
  11.000   1.3015   0.02297   0.01627  -0.0246   0.0052   1.0000
  11.250   1.3069   0.02416   0.01757  -0.0220   0.0048   1.0000
  11.500   1.3150   0.02522   0.01874  -0.0200   0.0046   1.0000
  11.750   1.3216   0.02645   0.02008  -0.0180   0.0044   1.0000
  12.000   1.3268   0.02785   0.02160  -0.0162   0.0043   1.0000
  12.250   1.3308   0.02944   0.02330  -0.0146   0.0041   1.0000
  12.500   1.3354   0.03107   0.02505  -0.0133   0.0039   1.0000
  12.750   1.3366   0.03312   0.02722  -0.0121   0.0038   1.0000
  13.000   1.3390   0.03519   0.02940  -0.0113   0.0036   1.0000
  13.250   1.3390   0.03761   0.03196  -0.0106   0.0035   1.0000
  13.500   1.3390   0.04016   0.03462  -0.0103   0.0034   1.0000
  13.750   1.3390   0.04282   0.03739  -0.0102   0.0032   1.0000
  14.000   1.3323   0.04639   0.04108  -0.0104   0.0031   1.0000
  14.250   1.3224   0.05053   0.04536  -0.0110   0.0030   1.0000
  14.500   1.3141   0.05469   0.04965  -0.0119   0.0029   1.0000
  14.750   1.3058   0.05903   0.05414  -0.0130   0.0029   1.0000
  15.000   1.3030   0.06278   0.05801  -0.0142   0.0029   1.0000
  15.250   1.2939   0.06761   0.06298  -0.0160   0.0029   1.0000
  15.500   1.2852   0.07264   0.06815  -0.0179   0.0028   1.0000
  15.750   1.2764   0.07786   0.07351  -0.0201   0.0028   1.0000
  16.000   1.2644   0.08384   0.07963  -0.0228   0.0027   1.0000
  16.250   1.2554   0.08951   0.08544  -0.0254   0.0027   1.0000
  16.500   1.2439   0.09579   0.09185  -0.0285   0.0027   1.0000
  16.750   1.2324   0.10222   0.09842  -0.0316   0.0027   1.0000
  17.000   1.2207   0.10886   0.10518  -0.0350   0.0027   1.0000
  17.250   1.2084   0.11578   0.11223  -0.0386   0.0027   1.0000
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