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=5


Details Polar file
Airfoil: SD8040 (10%) (sd8040-il)
Reynolds number: 50,000
Max Cl/Cd: 36.73 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8040-il-50000-n5.txt
Download as CSV file: xf-sd8040-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4173   0.08724   0.08013  -0.0378   1.0000   0.0511
  -8.250  -0.4181   0.08379   0.07677  -0.0385   1.0000   0.0506
  -8.000  -0.4234   0.08012   0.07320  -0.0396   1.0000   0.0500
  -7.750  -0.4287   0.07604   0.06920  -0.0416   1.0000   0.0494
  -7.500  -0.4351   0.07179   0.06499  -0.0432   1.0000   0.0488
  -7.250  -0.4419   0.06760   0.06080  -0.0442   1.0000   0.0482
  -7.000  -0.4478   0.06346   0.05661  -0.0448   1.0000   0.0477
  -6.750  -0.4523   0.05936   0.05239  -0.0451   1.0000   0.0475
  -6.500  -0.4536   0.05541   0.04826  -0.0450   1.0000   0.0475
  -6.250  -0.4515   0.05159   0.04418  -0.0448   1.0000   0.0479
  -6.000  -0.4460   0.04785   0.04008  -0.0444   1.0000   0.0487
  -5.750  -0.4369   0.04431   0.03612  -0.0439   1.0000   0.0494
  -5.500  -0.4244   0.04099   0.03231  -0.0433   1.0000   0.0503
  -5.250  -0.4090   0.03799   0.02879  -0.0425   1.0000   0.0509
  -5.000  -0.3912   0.03531   0.02561  -0.0416   1.0000   0.0516
  -4.750  -0.3730   0.03333   0.02345  -0.0408   1.0000   0.0528
  -4.500  -0.3539   0.03179   0.02175  -0.0399   1.0000   0.0554
  -4.250  -0.3334   0.03025   0.01989  -0.0389   1.0000   0.0591
  -4.000  -0.3121   0.02871   0.01806  -0.0380   1.0000   0.0627
  -3.750  -0.2915   0.02756   0.01684  -0.0370   1.0000   0.0666
  -3.500  -0.2697   0.02649   0.01553  -0.0359   1.0000   0.0735
  -3.250  -0.2453   0.02557   0.01460  -0.0357   0.9984   0.0821
  -3.000  -0.2079   0.02460   0.01350  -0.0377   0.9911   0.0984
  -2.750  -0.1700   0.02367   0.01264  -0.0400   0.9839   0.1259
  -2.500  -0.1333   0.02265   0.01187  -0.0423   0.9757   0.1794
  -2.250  -0.0978   0.02154   0.01139  -0.0445   0.9676   0.2948
  -2.000  -0.0648   0.02050   0.01137  -0.0457   0.9596   0.5035
  -1.750  -0.0419   0.01992   0.01151  -0.0434   0.9492   0.6982
  -1.500   0.0060   0.01963   0.01148  -0.0450   0.9429   0.9159
  -1.250   0.0601   0.01963   0.01109  -0.0504   0.9330   1.0000
  -1.000   0.0968   0.01976   0.01090  -0.0525   0.9210   1.0000
  -0.750   0.1364   0.01989   0.01075  -0.0550   0.9100   1.0000
  -0.500   0.1766   0.01999   0.01060  -0.0574   0.8990   1.0000
  -0.250   0.2100   0.02009   0.01051  -0.0585   0.8856   1.0000
   0.000   0.2432   0.02017   0.01042  -0.0595   0.8724   1.0000
   0.250   0.2770   0.02023   0.01033  -0.0604   0.8593   1.0000
   0.500   0.3112   0.02024   0.01022  -0.0613   0.8464   1.0000
   0.750   0.3456   0.02022   0.01008  -0.0621   0.8335   1.0000
   1.000   0.3751   0.02024   0.01002  -0.0620   0.8184   1.0000
   1.250   0.4046   0.02025   0.00995  -0.0618   0.8031   1.0000
   1.500   0.4339   0.02025   0.00989  -0.0616   0.7875   1.0000
   1.750   0.4630   0.02024   0.00982  -0.0612   0.7715   1.0000
   2.000   0.4919   0.02023   0.00976  -0.0608   0.7550   1.0000
   2.250   0.5207   0.02022   0.00970  -0.0602   0.7382   1.0000
   2.500   0.5471   0.02029   0.00973  -0.0594   0.7194   1.0000
   2.750   0.5736   0.02036   0.00977  -0.0586   0.7000   1.0000
   3.000   0.6005   0.02043   0.00981  -0.0578   0.6805   1.0000
   3.250   0.6278   0.02050   0.00983  -0.0569   0.6608   1.0000
   3.500   0.6541   0.02063   0.00990  -0.0560   0.6402   1.0000
   3.750   0.6790   0.02083   0.01010  -0.0550   0.6178   1.0000
   4.000   0.7049   0.02102   0.01022  -0.0541   0.5963   1.0000
   4.250   0.7294   0.02129   0.01046  -0.0531   0.5736   1.0000
   4.500   0.7537   0.02159   0.01072  -0.0520   0.5507   1.0000
   4.750   0.7780   0.02193   0.01101  -0.0510   0.5281   1.0000
   5.000   0.8012   0.02233   0.01139  -0.0499   0.5046   1.0000
   5.250   0.8250   0.02273   0.01171  -0.0489   0.4822   1.0000
   5.500   0.8472   0.02322   0.01224  -0.0478   0.4586   1.0000
   5.750   0.8700   0.02371   0.01267  -0.0467   0.4364   1.0000
   6.000   0.8917   0.02428   0.01324  -0.0457   0.4137   1.0000
   6.250   0.9134   0.02487   0.01381  -0.0446   0.3917   1.0000
   6.500   0.9348   0.02550   0.01441  -0.0435   0.3707   1.0000
   6.750   0.9553   0.02620   0.01515  -0.0423   0.3492   1.0000
   7.000   0.9756   0.02693   0.01587  -0.0412   0.3290   1.0000
   7.250   0.9956   0.02769   0.01662  -0.0400   0.3100   1.0000
   7.500   1.0149   0.02853   0.01750  -0.0389   0.2910   1.0000
   7.750   1.0336   0.02942   0.01844  -0.0377   0.2725   1.0000
   8.000   1.0519   0.03035   0.01942  -0.0365   0.2554   1.0000
   8.250   1.0694   0.03134   0.02046  -0.0352   0.2389   1.0000
   8.500   1.0867   0.03239   0.02156  -0.0340   0.2236   1.0000
   8.750   1.1028   0.03350   0.02272  -0.0326   0.2089   1.0000
   9.000   1.1185   0.03469   0.02398  -0.0313   0.1953   1.0000
   9.250   1.1331   0.03593   0.02530  -0.0299   0.1825   1.0000
   9.500   1.1473   0.03722   0.02662  -0.0285   0.1710   1.0000
   9.750   1.1600   0.03855   0.02800  -0.0270   0.1600   1.0000
  10.000   1.1715   0.04012   0.02976  -0.0255   0.1495   1.0000
  10.250   1.1819   0.04169   0.03145  -0.0239   0.1403   1.0000
  10.500   1.1915   0.04318   0.03295  -0.0222   0.1323   1.0000
  10.750   1.1975   0.04511   0.03513  -0.0204   0.1246   1.0000
  11.000   1.2063   0.04667   0.03664  -0.0189   0.1182   1.0000
  11.250   1.2086   0.04907   0.03937  -0.0171   0.1120   1.0000
  11.500   1.2140   0.05097   0.04135  -0.0157   0.1066   1.0000
  11.750   1.2155   0.05355   0.04414  -0.0144   0.1020   1.0000
  12.000   1.2135   0.05644   0.04729  -0.0133   0.0978   1.0000
  12.250   1.2171   0.05869   0.04958  -0.0124   0.0939   1.0000
  12.500   1.2135   0.06196   0.05305  -0.0118   0.0908   1.0000
  12.750   1.1995   0.06639   0.05783  -0.0118   0.0885   1.0000
  13.000   1.1856   0.07112   0.06283  -0.0125   0.0866   1.0000
  13.250   1.1709   0.07625   0.06818  -0.0139   0.0849   1.0000
  13.500   1.1577   0.08143   0.07352  -0.0156   0.0833   1.0000
  13.750   1.1637   0.08395   0.07600  -0.0157   0.0805   1.0000
  14.000   1.1327   0.09251   0.08482  -0.0201   0.0804   1.0000
  14.250   1.0962   0.10316   0.09568  -0.0264   0.0806   1.0000
<< Back to SD8040 (10%) (sd8040-il)

Polar data table (+)

Polar graphs


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