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ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: ARA-D 20% AIRFOIL (arad20-il)
Reynolds number: 50,000
Max Cl/Cd: 18.2 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-arad20-il-50000-n5.txt
Download as CSV file: xf-arad20-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: ARA-D 20% AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5631   0.09508   0.08768  -0.0258   1.0000   0.0773
 -11.750  -0.6338   0.07925   0.07156  -0.0368   1.0000   0.0766
 -11.500  -0.6810   0.07053   0.06255  -0.0413   1.0000   0.0764
 -11.250  -0.7176   0.06490   0.05663  -0.0415   1.0000   0.0766
 -11.000  -0.7462   0.06031   0.05167  -0.0400   1.0000   0.0773
 -10.750  -0.7417   0.05794   0.04927  -0.0391   1.0000   0.0789
 -10.500  -0.7351   0.05569   0.04696  -0.0382   1.0000   0.0808
 -10.250  -0.7336   0.05267   0.04366  -0.0371   1.0000   0.0830
 -10.000  -0.7291   0.04963   0.04028  -0.0361   1.0000   0.0854
  -9.750  -0.7113   0.04812   0.03885  -0.0356   1.0000   0.0880
  -9.500  -0.6980   0.04588   0.03638  -0.0349   1.0000   0.0914
  -9.250  -0.6804   0.04405   0.03450  -0.0344   1.0000   0.0946
  -9.000  -0.6613   0.04253   0.03297  -0.0340   1.0000   0.0985
  -8.750  -0.6426   0.04080   0.03114  -0.0336   1.0000   0.1027
  -8.500  -0.6084   0.03935   0.02969  -0.0359   0.9435   0.1082
  -8.250  -0.5713   0.03788   0.02807  -0.0381   0.8758   0.1146
  -8.000  -0.5429   0.03664   0.02647  -0.0382   0.8236   0.1217
  -7.750  -0.5194   0.03584   0.02558  -0.0373   0.7846   0.1278
  -7.500  -0.4967   0.03497   0.02447  -0.0362   0.7551   0.1351
  -7.250  -0.4735   0.03418   0.02344  -0.0352   0.7316   0.1439
  -7.000  -0.4499   0.03345   0.02267  -0.0344   0.7119   0.1527
  -6.750  -0.4258   0.03273   0.02184  -0.0337   0.6958   0.1634
  -6.500  -0.4012   0.03205   0.02106  -0.0331   0.6813   0.1760
  -6.250  -0.3760   0.03139   0.02036  -0.0327   0.6679   0.1907
  -6.000  -0.3511   0.03078   0.01971  -0.0322   0.6564   0.2078
  -5.750  -0.3252   0.03019   0.01917  -0.0321   0.6450   0.2282
  -5.500  -0.2995   0.02967   0.01864  -0.0318   0.6350   0.2525
  -5.250  -0.2735   0.02917   0.01823  -0.0316   0.6256   0.2801
  -5.000  -0.2471   0.02874   0.01789  -0.0314   0.6158   0.3120
  -4.750  -0.2212   0.02840   0.01762  -0.0310   0.6081   0.3465
  -4.500  -0.1940   0.02812   0.01749  -0.0309   0.5992   0.3845
  -4.250  -0.1676   0.02794   0.01740  -0.0305   0.5909   0.4239
  -4.000  -0.1415   0.02785   0.01732  -0.0297   0.5841   0.4634
  -3.750  -0.1148   0.02783   0.01748  -0.0292   0.5757   0.5013
  -3.500  -0.0884   0.02787   0.01759  -0.0284   0.5682   0.5384
  -3.250  -0.0625   0.02796   0.01763  -0.0274   0.5619   0.5749
  -3.000  -0.0364   0.02814   0.01790  -0.0265   0.5544   0.6075
  -2.750  -0.0102   0.02832   0.01811  -0.0256   0.5471   0.6398
  -2.500   0.0154   0.02850   0.01823  -0.0243   0.5409   0.6703
  -2.250   0.0405   0.02875   0.01844  -0.0229   0.5348   0.6979
  -2.000   0.0657   0.02902   0.01877  -0.0219   0.5272   0.7248
  -1.750   0.0906   0.02925   0.01894  -0.0205   0.5209   0.7509
  -1.500   0.1155   0.02943   0.01900  -0.0190   0.5157   0.7763
  -1.250   0.1405   0.02975   0.01933  -0.0181   0.5088   0.8009
  -1.000   0.1658   0.03002   0.01959  -0.0171   0.5018   0.8249
  -0.750   0.1920   0.03020   0.01966  -0.0161   0.4962   0.8486
  -0.500   0.2197   0.03037   0.01966  -0.0154   0.4914   0.8720
  -0.250   0.2495   0.03082   0.02019  -0.0160   0.4832   0.8942
   0.000   0.2839   0.03110   0.02039  -0.0170   0.4766   0.9151
   0.250   0.3230   0.03129   0.02039  -0.0189   0.4714   0.9347
   0.500   0.3644   0.03189   0.02099  -0.0221   0.4636   0.9527
   0.750   0.4089   0.03237   0.02141  -0.0259   0.4561   0.9689
   1.000   0.4567   0.03261   0.02146  -0.0299   0.4505   0.9831
   1.250   0.5017   0.03330   0.02214  -0.0343   0.4431   0.9978
   1.500   0.5180   0.03376   0.02259  -0.0337   0.4369   1.0000
   1.750   0.5326   0.03398   0.02269  -0.0322   0.4324   1.0000
   2.000   0.5510   0.03411   0.02264  -0.0309   0.4288   1.0000
   2.250   0.5673   0.03511   0.02368  -0.0304   0.4223   1.0000
   2.500   0.5874   0.03592   0.02447  -0.0302   0.4160   1.0000
   2.750   0.6120   0.03631   0.02474  -0.0301   0.4114   1.0000
   3.000   0.6393   0.03651   0.02474  -0.0300   0.4080   1.0000
   3.250   0.6551   0.03829   0.02669  -0.0302   0.4002   1.0000
   3.500   0.6776   0.03914   0.02751  -0.0302   0.3946   1.0000
   3.750   0.7047   0.03945   0.02769  -0.0302   0.3907   1.0000
   4.000   0.7283   0.04026   0.02844  -0.0302   0.3864   1.0000
   4.250   0.7382   0.04258   0.03095  -0.0300   0.3786   1.0000
   4.500   0.7614   0.04330   0.03162  -0.0299   0.3741   1.0000
   4.750   0.7903   0.04342   0.03160  -0.0298   0.3709   1.0000
   5.000   0.7909   0.04656   0.03495  -0.0292   0.3636   1.0000
   5.250   0.8000   0.04862   0.03708  -0.0287   0.3577   1.0000
   5.500   0.8254   0.04902   0.03740  -0.0285   0.3543   1.0000
   5.750   0.8580   0.04876   0.03701  -0.0285   0.3518   1.0000
   6.000   0.7887   0.05811   0.04680  -0.0262   0.3397   1.0000
   6.250   0.8102   0.05869   0.04733  -0.0257   0.3366   1.0000
   6.500   0.8456   0.05809   0.04662  -0.0255   0.3346   1.0000
   8.000   0.6869   0.09937   0.08834  -0.0338   0.2886   1.0000
   8.250   0.7052   0.10065   0.08960  -0.0337   0.2858   1.0000
   8.500   0.7295   0.10112   0.09003  -0.0332   0.2840   1.0000
   8.750   0.6849   0.11137   0.10040  -0.0369   0.2750   1.0000
   9.000   0.6969   0.11360   0.10262  -0.0372   0.2716   1.0000
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