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

SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD8040 (10%) (sd8040-il)
Reynolds number: 50,000
Max Cl/Cd: 32.6 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd8040-il-50000.txt
Download as CSV file: xf-sd8040-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8040 (10%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4093   0.11802   0.11089  -0.0182   1.0000   0.2127
  -9.250  -0.3809   0.11213   0.10495  -0.0164   1.0000   0.2216
  -9.000  -0.4081   0.11285   0.10585  -0.0193   1.0000   0.2281
  -8.750  -0.3733   0.10615   0.09909  -0.0170   1.0000   0.2378
  -8.500  -0.3886   0.10486   0.09795  -0.0185   1.0000   0.2453
  -8.250  -0.3714   0.10084   0.09393  -0.0173   1.0000   0.2571
  -8.000  -0.3648   0.09746   0.09060  -0.0168   1.0000   0.2663
  -7.750  -0.3915   0.09761   0.09096  -0.0175   1.0000   0.2763
  -7.500  -0.3751   0.09360   0.08697  -0.0159   1.0000   0.2914
  -7.250  -0.3624   0.09001   0.08342  -0.0144   1.0000   0.3056
  -7.000  -0.3572   0.08709   0.08058  -0.0129   1.0000   0.3198
  -6.750  -0.3559   0.08449   0.07807  -0.0112   1.0000   0.3337
  -6.250  -0.3679   0.08041   0.07425  -0.0063   1.0000   0.3617
  -5.750  -0.3776   0.07624   0.07032  -0.0003   1.0000   0.3940
  -5.000  -0.4090   0.05039   0.04311  -0.0382   1.0000   0.1483
  -4.750  -0.3921   0.04506   0.03721  -0.0394   1.0000   0.1344
  -4.500  -0.3744   0.04171   0.03363  -0.0390   1.0000   0.1304
  -4.250  -0.3547   0.03839   0.02992  -0.0389   1.0000   0.1279
  -4.000  -0.3332   0.03558   0.02662  -0.0387   1.0000   0.1289
  -3.750  -0.3100   0.03314   0.02362  -0.0384   1.0000   0.1316
  -3.500  -0.2858   0.03086   0.02085  -0.0379   1.0000   0.1345
  -3.250  -0.2638   0.02922   0.01917  -0.0372   1.0000   0.1432
  -3.000  -0.2395   0.02759   0.01730  -0.0365   1.0000   0.1540
  -2.750  -0.2161   0.02626   0.01589  -0.0357   1.0000   0.1711
  -2.500  -0.1924   0.02499   0.01459  -0.0348   1.0000   0.1985
  -2.250  -0.1697   0.02375   0.01353  -0.0338   1.0000   0.2455
  -2.000  -0.1456   0.02197   0.01260  -0.0330   1.0000   0.3678
  -1.750  -0.1424   0.01969   0.01260  -0.0256   1.0000   0.7394
  -1.500  -0.1073   0.01922   0.01191  -0.0264   1.0000   1.0000
  -1.250  -0.0870   0.01951   0.01173  -0.0263   1.0000   1.0000
  -1.000  -0.0673   0.01986   0.01172  -0.0261   1.0000   1.0000
  -0.750  -0.0480   0.02027   0.01183  -0.0259   1.0000   1.0000
  -0.500  -0.0292   0.02075   0.01204  -0.0257   1.0000   1.0000
  -0.250  -0.0106   0.02128   0.01233  -0.0256   1.0000   1.0000
   0.000   0.0076   0.02187   0.01272  -0.0254   1.0000   1.0000
   0.250   0.0254   0.02252   0.01320  -0.0254   1.0000   1.0000
   0.500   0.0814   0.02395   0.01438  -0.0322   0.9835   1.0000
   0.750   0.1333   0.02514   0.01539  -0.0381   0.9641   1.0000
   1.000   0.1876   0.02631   0.01640  -0.0440   0.9456   1.0000
   1.250   0.2324   0.02720   0.01719  -0.0481   0.9253   1.0000
   1.500   0.2770   0.02799   0.01791  -0.0518   0.9049   1.0000
   1.750   0.3246   0.02869   0.01856  -0.0556   0.8851   1.0000
   2.000   0.3755   0.02922   0.01907  -0.0597   0.8661   1.0000
   2.250   0.4091   0.02971   0.01956  -0.0609   0.8442   1.0000
   2.500   0.4524   0.03000   0.01987  -0.0632   0.8237   1.0000
   2.750   0.5035   0.02998   0.01991  -0.0662   0.8046   1.0000
   3.000   0.5515   0.02976   0.01975  -0.0682   0.7858   1.0000
   3.250   0.5809   0.02994   0.01997  -0.0677   0.7633   1.0000
   3.500   0.6226   0.02953   0.01965  -0.0682   0.7435   1.0000
   3.750   0.6661   0.02886   0.01904  -0.0684   0.7245   1.0000
   4.000   0.6946   0.02884   0.01909  -0.0671   0.7016   1.0000
   4.250   0.7298   0.02839   0.01869  -0.0662   0.6801   1.0000
   4.500   0.7664   0.02780   0.01811  -0.0652   0.6588   1.0000
   4.750   0.7916   0.02793   0.01830  -0.0634   0.6336   1.0000
   5.000   0.8234   0.02765   0.01800  -0.0620   0.6102   1.0000
   5.250   0.8490   0.02782   0.01817  -0.0603   0.5843   1.0000
   5.500   0.8744   0.02808   0.01841  -0.0586   0.5586   1.0000
   5.750   0.9032   0.02815   0.01841  -0.0571   0.5336   1.0000
   6.000   0.9245   0.02880   0.01909  -0.0554   0.5067   1.0000
   6.250   0.9490   0.02930   0.01953  -0.0539   0.4812   1.0000
   6.500   0.9734   0.02986   0.02005  -0.0524   0.4559   1.0000
   6.750   0.9940   0.03075   0.02096  -0.0507   0.4303   1.0000
   7.000   1.0202   0.03136   0.02140  -0.0495   0.4067   1.0000
   7.250   1.0375   0.03257   0.02276  -0.0478   0.3824   1.0000
   7.500   1.0625   0.03340   0.02344  -0.0466   0.3601   1.0000
   7.750   1.0792   0.03482   0.02501  -0.0449   0.3382   1.0000
   8.000   1.0993   0.03606   0.02627  -0.0435   0.3174   1.0000
   8.250   1.1230   0.03721   0.02730  -0.0424   0.2977   1.0000
   8.500   1.1383   0.03892   0.02917  -0.0407   0.2795   1.0000
   8.750   1.1539   0.04073   0.03114  -0.0391   0.2625   1.0000
   9.000   1.1692   0.04258   0.03311  -0.0375   0.2465   1.0000
   9.250   1.1842   0.04461   0.03527  -0.0359   0.2320   1.0000
   9.500   1.1992   0.04663   0.03739  -0.0344   0.2183   1.0000
   9.750   1.2168   0.04868   0.03945  -0.0332   0.2055   1.0000
  10.000   1.2154   0.05186   0.04309  -0.0307   0.1965   1.0000
  10.250   1.2206   0.05497   0.04642  -0.0289   0.1882   1.0000
  10.500   1.2439   0.05692   0.04826  -0.0282   0.1770   1.0000
  10.750   1.2205   0.06172   0.05362  -0.0251   0.1748   1.0000
  11.000   1.1933   0.06683   0.05911  -0.0226   0.1737   1.0000
  11.250   1.1593   0.07218   0.06466  -0.0204   0.1740   1.0000
  11.500   1.1204   0.07869   0.07131  -0.0201   0.1753   1.0000
  11.750   1.0829   0.08669   0.07938  -0.0222   0.1767   1.0000
<< Back to SD8040 (10%) (sd8040-il)

Polar data table (+)

Polar graphs


<< Back to SD8040 (10%) (sd8040-il)