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DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il)
Reynolds number: 200,000
Max Cl/Cd: 82.36 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-la203a-il-200000.txt
Download as CSV file: xf-la203a-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DOUGLAS LA203A AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.0291   0.10144   0.09694  -0.0971   0.8436   0.0618
  -9.500  -0.0216   0.09881   0.09431  -0.0985   0.8382   0.0633
  -9.250  -0.0451   0.09458   0.09006  -0.1086   0.8325   0.0661
  -9.000  -0.0258   0.09179   0.08724  -0.1062   0.8286   0.0665
  -8.750  -0.0090   0.08963   0.08509  -0.1050   0.8238   0.0672
  -8.500   0.0038   0.08742   0.08288  -0.1051   0.8192   0.0681
  -8.250   0.0137   0.08503   0.08047  -0.1061   0.8149   0.0694
  -8.000   0.0212   0.08240   0.07779  -0.1078   0.8111   0.0712
  -7.750  -0.0029   0.07522   0.07070  -0.1222   0.8051   0.0743
  -7.500   0.0173   0.07385   0.06932  -0.1183   0.8011   0.0749
  -7.250   0.0333   0.07215   0.06761  -0.1169   0.7972   0.0756
  -7.000   0.0464   0.07011   0.06554  -0.1172   0.7938   0.0768
  -6.750   0.0556   0.06760   0.06304  -0.1190   0.7900   0.0786
  -6.500   0.0404   0.05693   0.05215  -0.1432   0.7839   0.0837
  -6.250   0.0588   0.05530   0.05061  -0.1413   0.7801   0.0845
  -6.000   0.0766   0.05364   0.04894  -0.1410   0.7767   0.0857
  -5.750   0.0938   0.05144   0.04666  -0.1430   0.7734   0.0883
  -5.500   0.1069   0.04645   0.04134  -0.1510   0.7687   0.0947
  -5.250   0.1265   0.04488   0.03983  -0.1508   0.7648   0.0964
  -5.000   0.1509   0.04196   0.03639  -0.1561   0.7611   0.1054
  -4.750   0.1734   0.03987   0.03436  -0.1562   0.7583   0.1070
  -4.500   0.1946   0.03848   0.03299  -0.1565   0.7542   0.1100
  -4.250   0.2202   0.03644   0.03066  -0.1591   0.7500   0.1196
  -4.000   0.2446   0.03496   0.02920  -0.1594   0.7465   0.1230
  -3.750   0.2909   0.02838   0.02116  -0.1644   0.7438   0.0839
  -3.500   0.3192   0.02675   0.01946  -0.1649   0.7408   0.0805
  -3.250   0.3499   0.02499   0.01711  -0.1654   0.7362   0.0739
  -3.000   0.3783   0.02378   0.01578  -0.1658   0.7326   0.0736
  -2.750   0.4087   0.02282   0.01464  -0.1662   0.7295   0.0737
  -2.500   0.4401   0.02209   0.01370  -0.1667   0.7270   0.0742
  -2.250   0.4643   0.02134   0.01307  -0.1665   0.7223   0.0761
  -2.000   0.4917   0.02092   0.01268  -0.1665   0.7184   0.0784
  -1.750   0.5216   0.02040   0.01208  -0.1667   0.7153   0.0803
  -1.500   0.5527   0.01992   0.01150  -0.1670   0.7128   0.0822
  -1.250   0.5789   0.01955   0.01120  -0.1669   0.7087   0.0844
  -1.000   0.6061   0.01929   0.01105  -0.1670   0.7044   0.0884
  -0.750   0.6364   0.01904   0.01076  -0.1674   0.7010   0.0931
  -0.500   0.6695   0.01851   0.01031  -0.1685   0.6983   0.0993
  -0.250   0.7011   0.01830   0.01015  -0.1695   0.6951   0.1079
   0.000   0.7295   0.01825   0.01024  -0.1700   0.6900   0.1240
   0.250   0.7741   0.01691   0.01056  -0.1745   0.6863   0.6433
   0.500   0.7997   0.01711   0.01080  -0.1732   0.6832   0.7035
   0.750   0.8259   0.01735   0.01099  -0.1720   0.6807   0.7360
   1.000   0.8438   0.01781   0.01159  -0.1700   0.6749   0.7581
   1.250   0.8635   0.01803   0.01186  -0.1677   0.6706   0.7796
   1.500   0.8852   0.01812   0.01195  -0.1657   0.6674   0.7993
   1.750   0.9091   0.01819   0.01196  -0.1641   0.6648   0.8166
   2.000   0.9279   0.01856   0.01242  -0.1625   0.6593   0.8299
   2.250   0.9496   0.01866   0.01255  -0.1611   0.6547   0.8384
   2.500   0.9795   0.01865   0.01249  -0.1614   0.6514   0.8477
   2.750   1.0064   0.01856   0.01235  -0.1608   0.6487   0.8556
   3.000   1.0303   0.01884   0.01267  -0.1604   0.6438   0.8645
   3.250   1.0526   0.01900   0.01288  -0.1595   0.6386   0.8714
   3.500   1.0806   0.01899   0.01285  -0.1594   0.6350   0.8790
   3.750   1.1100   0.01889   0.01271  -0.1595   0.6321   0.8868
   4.000   1.1344   0.01900   0.01284  -0.1589   0.6282   0.8962
   4.250   1.1519   0.01927   0.01322  -0.1572   0.6221   0.9062
   4.500   1.1779   0.01925   0.01319  -0.1568   0.6182   0.9168
   4.750   1.2035   0.01909   0.01301  -0.1561   0.6151   0.9296
   5.000   1.2249   0.01901   0.01293  -0.1546   0.6117   0.9462
   5.250   1.2370   0.01925   0.01332  -0.1521   0.6050   0.9810
   5.500   1.2745   0.01928   0.01334  -0.1543   0.6006   0.9999
   5.750   1.3148   0.01920   0.01320  -0.1569   0.5972   0.9999
   6.000   1.3461   0.01955   0.01360  -0.1582   0.5916   0.9999
   6.250   1.3764   0.01980   0.01389  -0.1592   0.5854   0.9999
   6.500   1.4132   0.01963   0.01368  -0.1608   0.5808   0.9999
   6.750   1.4441   0.01974   0.01379  -0.1616   0.5749   0.9999
   7.000   1.4704   0.01985   0.01395  -0.1616   0.5671   0.9999
   7.250   1.5083   0.01941   0.01337  -0.1631   0.5609   0.9999
   7.500   1.5268   0.01965   0.01373  -0.1617   0.5508   0.9999
   7.750   1.5598   0.01930   0.01326  -0.1624   0.5426   0.9999
   8.000   1.5774   0.01952   0.01359  -0.1608   0.5320   0.9999
   8.250   1.6030   0.01952   0.01356  -0.1604   0.5229   0.9999
   8.500   1.6221   0.01974   0.01382  -0.1590   0.5128   0.9999
   8.750   1.6420   0.01998   0.01408  -0.1577   0.5030   0.9999
   9.000   1.6621   0.02018   0.01428  -0.1564   0.4929   0.9999
   9.250   1.6745   0.02065   0.01484  -0.1541   0.4820   0.9999
   9.500   1.6897   0.02098   0.01514  -0.1520   0.4714   0.9999
   9.750   1.6985   0.02156   0.01576  -0.1491   0.4596   0.9999
  10.000   1.7058   0.02229   0.01654  -0.1463   0.4474   0.9999
  10.250   1.7133   0.02309   0.01734  -0.1435   0.4349   0.9999
  10.500   1.7186   0.02408   0.01831  -0.1407   0.4211   0.9999
  10.750   1.7205   0.02539   0.01963  -0.1378   0.4061   0.9999
  11.000   1.7208   0.02695   0.02120  -0.1351   0.3900   0.9999
  11.250   1.7194   0.02877   0.02302  -0.1324   0.3724   0.9999
  11.500   1.7154   0.03092   0.02511  -0.1297   0.3532   0.9999
  11.750   1.7093   0.03338   0.02755  -0.1272   0.3316   0.9999
  12.000   1.6994   0.03624   0.03034  -0.1245   0.3080   0.9999
  12.250   1.6860   0.03951   0.03349  -0.1219   0.2837   0.9999
  12.500   1.6707   0.04310   0.03697  -0.1193   0.2586   0.9999
  12.750   1.6536   0.04704   0.04078  -0.1170   0.2356   0.9999
  13.000   1.6386   0.05100   0.04463  -0.1150   0.2128   0.9999
  13.250   1.6228   0.05520   0.04872  -0.1132   0.1920   0.9999
  13.750   1.5951   0.06364   0.05698  -0.1104   0.1562   0.9999
  14.000   1.5833   0.06781   0.06107  -0.1093   0.1413   0.9999
  14.250   1.5722   0.07199   0.06518  -0.1084   0.1291   0.9999
  14.500   1.5639   0.07591   0.06907  -0.1076   0.1184   0.9999
  14.750   1.5584   0.07956   0.07270  -0.1070   0.1092   0.9999
  15.000   1.5515   0.08340   0.07651  -0.1064   0.1021   0.9999
  15.250   1.5475   0.08693   0.08003  -0.1059   0.0955   0.9999
  15.500   1.5443   0.09034   0.08344  -0.1055   0.0902   0.9999
  15.750   1.5429   0.09358   0.08671  -0.1052   0.0853   0.9999
  16.000   1.5408   0.09681   0.08990  -0.1048   0.0813   0.9999
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