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

SD8020-010-88 (sd8020-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD8020-010-88 (sd8020-il)
Reynolds number: 50,000
Max Cl/Cd: 26.6 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8020-il-50000-n5.txt
Download as CSV file: xf-sd8020-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8020-010-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.7519   0.08448   0.07720  -0.0238   1.0000   0.0531
 -11.250  -0.7731   0.07740   0.07007  -0.0284   1.0000   0.0527
 -11.000  -0.7957   0.07133   0.06391  -0.0317   1.0000   0.0524
 -10.750  -0.8180   0.06633   0.05875  -0.0331   1.0000   0.0522
 -10.500  -0.8388   0.06219   0.05442  -0.0325   1.0000   0.0523
 -10.250  -0.8577   0.05839   0.05033  -0.0306   1.0000   0.0527
 -10.000  -0.8702   0.05453   0.04606  -0.0287   1.0000   0.0533
  -9.750  -0.8662   0.05160   0.04307  -0.0273   1.0000   0.0548
  -9.500  -0.8616   0.04880   0.04008  -0.0257   1.0000   0.0565
  -9.250  -0.8556   0.04596   0.03692  -0.0240   1.0000   0.0586
  -9.000  -0.8481   0.04319   0.03375  -0.0222   1.0000   0.0620
  -8.750  -0.8382   0.04059   0.03076  -0.0205   1.0000   0.0664
  -8.500  -0.8239   0.03884   0.02897  -0.0191   1.0000   0.0712
  -8.250  -0.8081   0.03647   0.02617  -0.0176   1.0000   0.0769
  -8.000  -0.7921   0.03480   0.02450  -0.0162   1.0000   0.0836
  -7.750  -0.7754   0.03310   0.02259  -0.0147   1.0000   0.0932
  -7.500  -0.7579   0.03162   0.02090  -0.0132   1.0000   0.1045
  -7.250  -0.7408   0.03029   0.01948  -0.0118   1.0000   0.1174
  -7.000  -0.7233   0.02905   0.01821  -0.0103   1.0000   0.1324
  -6.750  -0.7053   0.02787   0.01705  -0.0089   1.0000   0.1483
  -6.500  -0.6873   0.02679   0.01598  -0.0074   1.0000   0.1669
  -6.250  -0.6681   0.02576   0.01487  -0.0060   1.0000   0.1879
  -6.000  -0.6498   0.02480   0.01400  -0.0045   1.0000   0.2102
  -5.750  -0.6309   0.02390   0.01310  -0.0031   1.0000   0.2355
  -5.500  -0.6121   0.02307   0.01233  -0.0016   1.0000   0.2642
  -5.250  -0.5930   0.02230   0.01163  -0.0001   1.0000   0.2955
  -5.000  -0.5740   0.02160   0.01099   0.0014   1.0000   0.3306
  -4.750  -0.5552   0.02094   0.01046   0.0031   1.0000   0.3674
  -4.500  -0.5362   0.02035   0.00994   0.0047   1.0000   0.4072
  -4.250  -0.5170   0.01981   0.00953   0.0065   1.0000   0.4489
  -4.000  -0.4983   0.01934   0.00919   0.0084   1.0000   0.4916
  -3.750  -0.4797   0.01893   0.00891   0.0105   1.0000   0.5350
  -3.500  -0.4606   0.01858   0.00868   0.0126   1.0000   0.5786
  -3.250  -0.4412   0.01829   0.00848   0.0148   1.0000   0.6220
  -3.000  -0.4210   0.01806   0.00835   0.0169   1.0000   0.6651
  -2.750  -0.3996   0.01790   0.00827   0.0189   1.0000   0.7072
  -2.500  -0.3760   0.01781   0.00824   0.0205   1.0000   0.7482
  -2.250  -0.3492   0.01779   0.00822   0.0216   1.0000   0.7883
  -2.000  -0.3183   0.01783   0.00825   0.0217   1.0000   0.8269
  -1.750  -0.2789   0.01797   0.00833   0.0202   1.0000   0.8614
  -1.500  -0.2350   0.01813   0.00838   0.0175   1.0000   0.8927
  -1.250  -0.1866   0.01827   0.00841   0.0137   1.0000   0.9198
  -1.000  -0.1359   0.01834   0.00838   0.0091   1.0000   0.9441
  -0.750  -0.0852   0.01833   0.00830   0.0042   1.0000   0.9671
  -0.500  -0.0324   0.01822   0.00813  -0.0014   1.0000   0.9881
  -0.250   0.0008   0.01808   0.00798  -0.0038   1.0000   1.0000
   0.000   0.0000   0.01803   0.00794   0.0000   1.0000   1.0000
   0.250  -0.0008   0.01808   0.00798   0.0038   1.0000   1.0000
   0.500   0.0325   0.01822   0.00813   0.0014   0.9880   1.0000
   0.750   0.0852   0.01833   0.00829  -0.0042   0.9671   1.0000
   1.000   0.1360   0.01834   0.00838  -0.0091   0.9441   1.0000
   1.250   0.1865   0.01827   0.00841  -0.0137   0.9198   1.0000
   1.500   0.2350   0.01813   0.00837  -0.0175   0.8927   1.0000
   1.750   0.2789   0.01797   0.00833  -0.0202   0.8615   1.0000
   2.000   0.3183   0.01783   0.00824  -0.0217   0.8269   1.0000
   2.250   0.3492   0.01779   0.00822  -0.0215   0.7884   1.0000
   2.500   0.3760   0.01781   0.00824  -0.0205   0.7484   1.0000
   2.750   0.3996   0.01790   0.00827  -0.0189   0.7073   1.0000
   3.000   0.4210   0.01806   0.00835  -0.0169   0.6653   1.0000
   3.250   0.4412   0.01829   0.00848  -0.0148   0.6221   1.0000
   3.500   0.4606   0.01858   0.00868  -0.0127   0.5788   1.0000
   3.750   0.4797   0.01893   0.00891  -0.0105   0.5351   1.0000
   4.000   0.4983   0.01934   0.00918  -0.0084   0.4917   1.0000
   4.250   0.5170   0.01981   0.00953  -0.0065   0.4489   1.0000
   4.500   0.5361   0.02035   0.00994  -0.0047   0.4071   1.0000
   4.750   0.5552   0.02094   0.01046  -0.0031   0.3675   1.0000
   5.000   0.5739   0.02160   0.01098  -0.0014   0.3307   1.0000
   5.250   0.5931   0.02230   0.01163   0.0001   0.2957   1.0000
   5.500   0.6121   0.02307   0.01233   0.0016   0.2642   1.0000
   5.750   0.6309   0.02390   0.01309   0.0031   0.2354   1.0000
   6.250   0.6681   0.02576   0.01486   0.0060   0.1876   1.0000
   6.500   0.6872   0.02679   0.01598   0.0074   0.1665   1.0000
   6.750   0.7052   0.02787   0.01704   0.0089   0.1481   1.0000
   7.000   0.7232   0.02905   0.01821   0.0103   0.1322   1.0000
   7.250   0.7408   0.03030   0.01949   0.0118   0.1173   1.0000
   7.500   0.7580   0.03162   0.02091   0.0132   0.1046   1.0000
   7.750   0.7755   0.03311   0.02260   0.0147   0.0933   1.0000
   8.000   0.7923   0.03481   0.02452   0.0162   0.0838   1.0000
   8.250   0.8082   0.03647   0.02616   0.0175   0.0769   1.0000
   8.500   0.8241   0.03885   0.02897   0.0191   0.0714   1.0000
   8.750   0.8384   0.04064   0.03082   0.0205   0.0666   1.0000
   9.000   0.8483   0.04320   0.03376   0.0222   0.0621   1.0000
   9.250   0.8558   0.04597   0.03692   0.0240   0.0588   1.0000
   9.500   0.8617   0.04883   0.04011   0.0257   0.0566   1.0000
   9.750   0.8661   0.05165   0.04314   0.0273   0.0550   1.0000
  10.000   0.8699   0.05453   0.04612   0.0287   0.0535   1.0000
  10.250   0.8591   0.05834   0.05027   0.0305   0.0528   1.0000
  10.500   0.8401   0.06217   0.05439   0.0324   0.0523   1.0000
  10.750   0.8186   0.06634   0.05876   0.0331   0.0523   1.0000
  11.000   0.7957   0.07140   0.06398   0.0316   0.0524   1.0000
  11.250   0.7742   0.07736   0.07004   0.0283   0.0528   1.0000
  11.500   0.7518   0.08462   0.07735   0.0236   0.0531   1.0000
<< Back to SD8020-010-88 (sd8020-il)

Polar data table (+)

Polar graphs


<< Back to SD8020-010-88 (sd8020-il)