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SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: SD2083 (9.0%) (sd2083-il)
Reynolds number: 500,000
Max Cl/Cd: 108.95 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2083-il-500000.txt
Download as CSV file: xf-sd2083-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2083 (9.0%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3889   0.08432   0.08215  -0.0404   1.0000   0.0191
  -8.500  -0.3925   0.08021   0.07809  -0.0424   1.0000   0.0191
  -8.250  -0.4035   0.07754   0.07550  -0.0420   1.0000   0.0191
  -8.000  -0.4123   0.06892   0.06693  -0.0516   0.9917   0.0195
  -7.750  -0.3969   0.06389   0.06185  -0.0582   0.9867   0.0203
  -7.500  -0.3733   0.05867   0.05656  -0.0661   0.9835   0.0209
  -7.250  -0.3528   0.05377   0.05156  -0.0723   0.9766   0.0218
  -7.000  -0.3299   0.04790   0.04551  -0.0789   0.9710   0.0233
  -6.750  -0.3130   0.04232   0.03964  -0.0820   0.9609   0.0254
  -6.500  -0.3062   0.03615   0.03285  -0.0823   0.9494   0.0273
  -6.250  -0.2944   0.03278   0.02938  -0.0820   0.9425   0.0284
  -6.000  -0.2769   0.03138   0.02792  -0.0813   0.9352   0.0295
  -5.750  -0.2587   0.02985   0.02624  -0.0804   0.9294   0.0315
  -5.500  -0.2312   0.03082   0.02688  -0.0790   0.9229   0.0363
  -5.250  -0.2236   0.02472   0.02028  -0.0778   0.9162   0.0384
  -5.000  -0.2030   0.01934   0.01431  -0.0755   0.9102   0.0249
  -4.750  -0.1819   0.01533   0.00966  -0.0735   0.9047   0.0210
  -4.500  -0.1574   0.01407   0.00819  -0.0725   0.9004   0.0208
  -4.250  -0.1323   0.01311   0.00711  -0.0719   0.8948   0.0210
  -4.000  -0.1073   0.01236   0.00627  -0.0712   0.8899   0.0215
  -3.750  -0.0820   0.01180   0.00564  -0.0706   0.8856   0.0226
  -3.500  -0.0567   0.01115   0.00491  -0.0700   0.8799   0.0228
  -3.250  -0.0312   0.01060   0.00428  -0.0693   0.8752   0.0233
  -3.000  -0.0054   0.01017   0.00379  -0.0688   0.8704   0.0244
  -2.750   0.0210   0.00983   0.00337  -0.0684   0.8648   0.0259
  -2.500   0.0474   0.00948   0.00293  -0.0679   0.8601   0.0288
  -2.250   0.0740   0.00919   0.00266  -0.0675   0.8548   0.0391
  -2.000   0.0990   0.00858   0.00242  -0.0671   0.8490   0.1365
  -1.750   0.1239   0.00805   0.00226  -0.0667   0.8442   0.2566
  -1.500   0.1481   0.00748   0.00218  -0.0663   0.8376   0.4067
  -1.250   0.1718   0.00698   0.00210  -0.0655   0.8318   0.5485
  -1.000   0.1928   0.00641   0.00210  -0.0640   0.8252   0.7145
  -0.750   0.2173   0.00588   0.00215  -0.0624   0.8190   0.9133
  -0.500   0.2664   0.00586   0.00208  -0.0666   0.8138   0.9681
  -0.250   0.3225   0.00584   0.00199  -0.0726   0.8071   0.9916
   0.000   0.3661   0.00581   0.00187  -0.0760   0.8005   1.0000
   0.250   0.3904   0.00581   0.00181  -0.0752   0.7914   1.0000
   0.500   0.4149   0.00582   0.00176  -0.0745   0.7826   1.0000
   0.750   0.4396   0.00583   0.00170  -0.0737   0.7737   1.0000
   1.000   0.4645   0.00585   0.00169  -0.0731   0.7638   1.0000
   1.250   0.4895   0.00589   0.00167  -0.0725   0.7545   1.0000
   1.500   0.5146   0.00593   0.00166  -0.0718   0.7451   1.0000
   1.750   0.5399   0.00597   0.00168  -0.0712   0.7343   1.0000
   2.000   0.5651   0.00602   0.00170  -0.0707   0.7232   1.0000
   2.250   0.5904   0.00608   0.00173  -0.0701   0.7113   1.0000
   2.500   0.6155   0.00616   0.00178  -0.0695   0.6983   1.0000
   2.750   0.6406   0.00624   0.00182  -0.0688   0.6834   1.0000
   3.000   0.6655   0.00634   0.00188  -0.0682   0.6668   1.0000
   3.250   0.6902   0.00646   0.00194  -0.0675   0.6480   1.0000
   3.500   0.7147   0.00660   0.00204  -0.0667   0.6262   1.0000
   3.750   0.7387   0.00678   0.00214  -0.0659   0.6009   1.0000
   4.000   0.7623   0.00700   0.00227  -0.0651   0.5714   1.0000
   4.250   0.7854   0.00727   0.00242  -0.0642   0.5370   1.0000
   4.500   0.8078   0.00761   0.00262  -0.0632   0.4971   1.0000
   4.750   0.8295   0.00802   0.00285  -0.0621   0.4522   1.0000
   5.000   0.8506   0.00850   0.00313  -0.0610   0.4063   1.0000
   5.250   0.8717   0.00900   0.00343  -0.0599   0.3597   1.0000
   5.500   0.8930   0.00950   0.00375  -0.0589   0.3184   1.0000
   5.750   0.9131   0.01010   0.00413  -0.0578   0.2684   1.0000
   6.000   0.9342   0.01063   0.00448  -0.0568   0.2303   1.0000
   6.250   0.9560   0.01111   0.00484  -0.0559   0.2005   1.0000
   6.500   0.9771   0.01164   0.00523  -0.0549   0.1689   1.0000
   6.750   0.9977   0.01221   0.00566  -0.0539   0.1367   1.0000
   7.000   1.0168   0.01292   0.00615  -0.0527   0.0999   1.0000
   7.250   1.0359   0.01362   0.00669  -0.0515   0.0688   1.0000
   7.500   1.0503   0.01477   0.00752  -0.0495   0.0260   1.0000
   7.750   1.0671   0.01571   0.00841  -0.0478   0.0146   1.0000
   8.000   1.0867   0.01635   0.00912  -0.0465   0.0129   1.0000
   8.250   1.1045   0.01713   0.00999  -0.0449   0.0116   1.0000
   8.500   1.1182   0.01824   0.01121  -0.0427   0.0107   1.0000
   8.750   1.1319   0.01925   0.01234  -0.0406   0.0104   1.0000
   9.000   1.1468   0.02010   0.01328  -0.0387   0.0101   1.0000
   9.250   1.1588   0.02102   0.01428  -0.0363   0.0098   1.0000
   9.500   1.1707   0.02185   0.01520  -0.0340   0.0092   1.0000
   9.750   1.1807   0.02286   0.01629  -0.0315   0.0089   1.0000
  10.000   1.1882   0.02417   0.01773  -0.0288   0.0089   1.0000
  10.250   1.1974   0.02540   0.01907  -0.0264   0.0087   1.0000
  10.500   1.2066   0.02666   0.02042  -0.0243   0.0084   1.0000
  10.750   1.2144   0.02822   0.02211  -0.0221   0.0083   1.0000
  11.000   1.2224   0.02974   0.02374  -0.0201   0.0081   1.0000
  11.250   1.2298   0.03149   0.02562  -0.0182   0.0081   1.0000
  11.500   1.2359   0.03340   0.02768  -0.0162   0.0080   1.0000
  11.750   1.2396   0.03568   0.03008  -0.0143   0.0077   1.0000
  12.000   1.2434   0.03794   0.03253  -0.0126   0.0077   1.0000
  12.250   1.2450   0.04042   0.03522  -0.0108   0.0077   1.0000
  12.500   1.2422   0.04347   0.03845  -0.0091   0.0076   1.0000
  12.750   1.2382   0.04648   0.04175  -0.0076   0.0078   1.0000
  13.000   1.2260   0.05092   0.04653  -0.0062   0.0082   1.0000
  13.250   1.1969   0.05757   0.05364  -0.0054   0.0087   1.0000
  13.500   1.1736   0.06361   0.05997  -0.0060   0.0089   1.0000
  13.750   1.1551   0.06927   0.06584  -0.0075   0.0092   1.0000
  14.000   1.1335   0.07590   0.07267  -0.0100   0.0093   1.0000
  14.250   1.1129   0.08299   0.07995  -0.0135   0.0095   1.0000
  14.500   1.0942   0.09040   0.08752  -0.0178   0.0095   1.0000
  14.750   1.0736   0.09899   0.09627  -0.0231   0.0096   1.0000
  15.000   1.0537   0.10825   0.10568  -0.0291   0.0096   1.0000
  15.250   1.0321   0.11876   0.11633  -0.0359   0.0096   1.0000
  15.500   1.0129   0.12928   0.12696  -0.0426   0.0097   1.0000
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