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ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: ARA-D 20% AIRFOIL (arad20-il)
Reynolds number: 50,000
Max Cl/Cd: 9.72 at α=-0.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-arad20-il-50000.txt
Download as CSV file: xf-arad20-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3083   0.12117   0.11521   0.0066   1.0000   0.3397
  -9.500  -0.5388   0.08005   0.07378  -0.0304   1.0000   0.1713
  -9.250  -0.5550   0.07396   0.06766  -0.0316   1.0000   0.1700
  -9.000  -0.5773   0.06755   0.06112  -0.0327   1.0000   0.1688
  -8.750  -0.5954   0.06152   0.05484  -0.0332   1.0000   0.1686
  -8.500  -0.6059   0.05639   0.04939  -0.0333   1.0000   0.1696
  -8.250  -0.6352   0.05652   0.04971  -0.0300   0.9960   0.1691
  -8.000  -0.5847   0.05127   0.04410  -0.0382   0.9729   0.1767
  -7.750  -0.5388   0.04626   0.03829  -0.0454   0.9516   0.1863
  -7.500  -0.4848   0.04348   0.03549  -0.0509   0.9286   0.1983
  -7.250  -0.4456   0.04103   0.03281  -0.0538   0.9042   0.2100
  -7.000  -0.4149   0.03900   0.03041  -0.0548   0.8810   0.2227
  -6.750  -0.3869   0.03767   0.02884  -0.0548   0.8601   0.2370
  -6.500  -0.3605   0.03661   0.02780  -0.0540   0.8420   0.2525
  -6.250  -0.3355   0.03566   0.02682  -0.0534   0.8240   0.2702
  -6.000  -0.3104   0.03482   0.02594  -0.0528   0.8083   0.2917
  -5.750  -0.2858   0.03404   0.02511  -0.0516   0.7953   0.3171
  -5.500  -0.2604   0.03359   0.02491  -0.0510   0.7808   0.3453
  -5.250  -0.2358   0.03311   0.02447  -0.0499   0.7694   0.3806
  -5.000  -0.2111   0.03288   0.02443  -0.0490   0.7567   0.4196
  -4.750  -0.1874   0.03283   0.02458  -0.0471   0.7466   0.4609
  -4.500  -0.1632   0.03301   0.02499  -0.0457   0.7349   0.5043
  -4.250  -0.1412   0.03328   0.02538  -0.0426   0.7260   0.5471
  -4.000  -0.1183   0.03389   0.02618  -0.0409   0.7148   0.5878
  -3.750  -0.0971   0.03438   0.02671  -0.0377   0.7058   0.6276
  -3.500  -0.0765   0.03511   0.02747  -0.0350   0.6969   0.6657
  -3.250  -0.0566   0.03592   0.02835  -0.0317   0.6871   0.6984
  -3.000  -0.0371   0.03648   0.02882  -0.0276   0.6796   0.7330
  -2.750  -0.0175   0.03745   0.02982  -0.0255   0.6703   0.7647
  -2.500   0.0049   0.03820   0.03053  -0.0225   0.6614   0.7952
  -2.250   0.0275   0.03852   0.03067  -0.0192   0.6548   0.8295
  -2.000   0.0609   0.03992   0.03210  -0.0204   0.6439   0.8575
  -1.750   0.1077   0.04051   0.03251  -0.0220   0.6347   0.8881
  -1.500   0.1661   0.04176   0.03363  -0.0278   0.6239   0.9159
  -1.250   0.2487   0.04260   0.03424  -0.0374   0.6118   0.9404
  -1.000   0.3155   0.04372   0.03523  -0.0461   0.6008   0.9650
  -0.750   0.3903   0.04444   0.03579  -0.0561   0.5892   0.9868
  -0.500   0.4388   0.04514   0.03635  -0.0619   0.5808   1.0000
  -0.250   0.4419   0.04684   0.03812  -0.0627   0.5729   1.0000
   0.000   0.4465   0.04772   0.03893  -0.0616   0.5670   1.0000
   0.250   0.4545   0.04803   0.03908  -0.0594   0.5622   1.0000
   0.500   0.4429   0.05070   0.04183  -0.0586   0.5562   1.0000
   0.750   0.4154   0.05396   0.04517  -0.0565   0.5509   1.0000
   1.000   0.3811   0.05701   0.04824  -0.0529   0.5479   1.0000
   1.250   0.3399   0.06047   0.05168  -0.0489   0.5467   1.0000
   1.500   0.3014   0.06473   0.05590  -0.0465   0.5483   1.0000
   1.750   0.2843   0.06873   0.05985  -0.0461   0.5526   1.0000
   2.000   0.2902   0.07213   0.06317  -0.0470   0.5567   1.0000
   2.250   0.3107   0.07526   0.06621  -0.0486   0.5594   1.0000
   2.500   0.1893   0.08545   0.07676  -0.0524   0.6816   1.0000
   2.750   0.1912   0.08688   0.07809  -0.0510   0.6654   1.0000
   3.000   0.2407   0.09099   0.08205  -0.0547   0.6558   1.0000
   3.250   0.2295   0.09143   0.08244  -0.0519   0.6386   1.0000
   3.500   0.2798   0.09610   0.08697  -0.0556   0.6318   1.0000
   3.750   0.2610   0.09607   0.08689  -0.0523   0.6150   1.0000
   4.000   0.3136   0.10103   0.09173  -0.0559   0.6081   1.0000
   4.250   0.2896   0.10076   0.09142  -0.0526   0.5921   1.0000
   4.500   0.3328   0.10504   0.09560  -0.0551   0.5854   1.0000
   4.750   0.3134   0.10563   0.09617  -0.0527   0.5726   1.0000
   5.000   0.3467   0.10898   0.09944  -0.0542   0.5637   1.0000
   5.250   0.3472   0.11136   0.10177  -0.0538   0.5558   1.0000
   5.500   0.3578   0.11323   0.10358  -0.0536   0.5441   1.0000
   5.750   0.4003   0.11802   0.10830  -0.0559   0.5387   1.0000
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