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DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il)
Reynolds number: 100,000
Max Cl/Cd: 46.49 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-la203a-il-100000-n5.txt
Download as CSV file: xf-la203a-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.0242   0.09992   0.09377  -0.0971   0.8228   0.0778
  -9.000  -0.0166   0.09724   0.09108  -0.0986   0.8175   0.0793
  -8.750  -0.0122   0.09440   0.08822  -0.1009   0.8129   0.0813
  -8.500  -0.0175   0.09105   0.08487  -0.1059   0.8079   0.0827
  -8.250  -0.0205   0.08738   0.08122  -0.1107   0.8023   0.0831
  -8.000  -0.0002   0.08498   0.07881  -0.1082   0.7985   0.0841
  -7.750   0.0158   0.08294   0.07675  -0.1075   0.7946   0.0858
  -7.500   0.0253   0.08047   0.07426  -0.1086   0.7907   0.0877
  -7.000   0.0057   0.06478   0.05848  -0.1249   0.7802   0.0583
  -6.750   0.0155   0.06129   0.05495  -0.1285   0.7764   0.0574
  -6.500   0.0223   0.05673   0.05027  -0.1341   0.7724   0.0563
  -6.250   0.0277   0.05187   0.04523  -0.1393   0.7673   0.0551
  -6.000   0.0378   0.04692   0.03994  -0.1440   0.7629   0.0542
  -5.750   0.0557   0.04335   0.03602  -0.1470   0.7595   0.0542
  -5.500   0.0762   0.04089   0.03331  -0.1489   0.7559   0.0552
  -5.250   0.0961   0.03855   0.03069  -0.1504   0.7512   0.0561
  -5.000   0.1201   0.03615   0.02792  -0.1520   0.7473   0.0566
  -4.750   0.1471   0.03393   0.02531  -0.1536   0.7441   0.0567
  -4.500   0.1754   0.03203   0.02302  -0.1549   0.7410   0.0571
  -4.250   0.1992   0.03067   0.02139  -0.1552   0.7360   0.0576
  -4.000   0.2269   0.02935   0.01974  -0.1559   0.7322   0.0584
  -3.750   0.2554   0.02840   0.01864  -0.1565   0.7291   0.0598
  -3.500   0.2837   0.02772   0.01790  -0.1569   0.7261   0.0614
  -3.250   0.3078   0.02715   0.01724  -0.1567   0.7212   0.0630
  -3.000   0.3354   0.02639   0.01631  -0.1568   0.7175   0.0642
  -2.750   0.3646   0.02564   0.01538  -0.1570   0.7146   0.0655
  -2.500   0.3945   0.02493   0.01459  -0.1574   0.7122   0.0668
  -2.250   0.4177   0.02469   0.01442  -0.1569   0.7074   0.0688
  -2.000   0.4441   0.02438   0.01409  -0.1568   0.7034   0.0718
  -1.750   0.4727   0.02396   0.01361  -0.1568   0.7003   0.0745
  -1.500   0.5023   0.02347   0.01317  -0.1571   0.6978   0.0770
  -1.250   0.5279   0.02329   0.01303  -0.1569   0.6938   0.0800
  -1.000   0.5523   0.02324   0.01302  -0.1566   0.6889   0.0843
  -0.750   0.5811   0.02302   0.01284  -0.1569   0.6854   0.0901
  -0.500   0.6128   0.02272   0.01252  -0.1577   0.6826   0.0964
  -0.250   0.6431   0.02255   0.01238  -0.1584   0.6793   0.1069
   0.000   0.6670   0.02269   0.01266  -0.1584   0.6736   0.1236
   0.250   0.7003   0.02218   0.01259  -0.1602   0.6698   0.2222
   0.500   0.7308   0.02148   0.01323  -0.1607   0.6668   0.6501
   0.750   0.7562   0.02159   0.01335  -0.1593   0.6644   0.7033
   1.000   0.7689   0.02229   0.01419  -0.1565   0.6579   0.7391
   1.250   0.7839   0.02260   0.01456  -0.1533   0.6536   0.7730
   1.500   0.8045   0.02268   0.01461  -0.1511   0.6504   0.7967
   1.750   0.8309   0.02264   0.01450  -0.1503   0.6479   0.8133
   2.000   0.8427   0.02325   0.01519  -0.1477   0.6414   0.8244
   2.250   0.8661   0.02349   0.01541  -0.1471   0.6369   0.8344
   2.500   0.8937   0.02348   0.01535  -0.1469   0.6336   0.8418
   2.750   0.9257   0.02340   0.01519  -0.1475   0.6311   0.8499
   3.000   0.9391   0.02405   0.01593  -0.1455   0.6247   0.8587
   3.250   0.9619   0.02437   0.01626  -0.1450   0.6197   0.8679
   3.500   0.9877   0.02434   0.01621  -0.1444   0.6163   0.8771
   3.750   1.0167   0.02419   0.01602  -0.1443   0.6138   0.8876
   4.000   1.0265   0.02499   0.01694  -0.1419   0.6070   0.9014
   4.250   1.0442   0.02526   0.01725  -0.1404   0.6019   0.9167
   4.500   1.0683   0.02513   0.01712  -0.1394   0.5986   0.9367
   4.750   1.0971   0.02483   0.01679  -0.1393   0.5961   0.9958
   5.000   1.1118   0.02617   0.01824  -0.1389   0.5880   0.9999
   5.250   1.1418   0.02647   0.01854  -0.1398   0.5835   0.9999
   5.500   1.1776   0.02642   0.01846  -0.1412   0.5804   0.9999
   5.750   1.2163   0.02624   0.01823  -0.1429   0.5781   0.9999
   6.000   1.2160   0.02805   0.02020  -0.1402   0.5685   0.9999
   6.250   1.2470   0.02813   0.02027  -0.1408   0.5646   0.9999
   6.500   1.2844   0.02786   0.01999  -0.1421   0.5618   0.9999
   6.750   1.2815   0.02961   0.02185  -0.1388   0.5529   0.9999
   7.000   1.3072   0.02984   0.02211  -0.1387   0.5479   0.9999
   7.250   1.3457   0.02939   0.02165  -0.1399   0.5447   0.9999
   7.500   1.3391   0.03136   0.02374  -0.1363   0.5352   0.9999
   7.750   1.3664   0.03136   0.02376  -0.1361   0.5299   0.9999
   8.000   1.4110   0.03035   0.02274  -0.1377   0.5263   0.9999
   8.250   1.3914   0.03311   0.02565  -0.1331   0.5147   0.9999
   8.500   1.4346   0.03189   0.02440  -0.1340   0.5097   0.9999
   8.750   1.4204   0.03454   0.02718  -0.1304   0.4981   0.9999
   9.000   1.4651   0.03294   0.02553  -0.1311   0.4915   0.9999
   9.250   1.4493   0.03589   0.02861  -0.1277   0.4791   0.9999
   9.500   1.4628   0.03664   0.02939  -0.1264   0.4687   0.9999
   9.750   1.4827   0.03681   0.02955  -0.1253   0.4578   0.9999
  10.000   1.4755   0.03948   0.03232  -0.1230   0.4449   0.9999
  10.250   1.4839   0.04078   0.03365  -0.1216   0.4326   0.9999
  10.500   1.4994   0.04137   0.03424  -0.1203   0.4200   0.9999
  10.750   1.5034   0.04311   0.03601  -0.1187   0.4063   0.9999
  11.000   1.5016   0.04552   0.03847  -0.1170   0.3919   0.9999
  11.250   1.5028   0.04764   0.04062  -0.1154   0.3770   0.9999
  11.500   1.5047   0.04972   0.04271  -0.1139   0.3614   0.9999
  11.750   1.5058   0.05188   0.04488  -0.1125   0.3446   0.9999
  12.000   1.5059   0.05421   0.04718  -0.1110   0.3265   0.9999
  12.250   1.5051   0.05669   0.04961  -0.1096   0.3071   0.9999
  12.500   1.5035   0.05929   0.05212  -0.1083   0.2864   0.9999
  12.750   1.4995   0.06228   0.05503  -0.1071   0.2652   0.9999
  13.000   1.4942   0.06549   0.05814  -0.1059   0.2443   0.9999
  13.250   1.4877   0.06895   0.06150  -0.1049   0.2247   0.9999
  13.500   1.4806   0.07257   0.06505  -0.1041   0.2068   0.9999
  13.750   1.4735   0.07630   0.06871  -0.1033   0.1903   0.9999
  14.000   1.4667   0.08010   0.07246  -0.1028   0.1750   0.9999
  14.250   1.4608   0.08389   0.07621  -0.1024   0.1612   0.9999
  14.500   1.4556   0.08762   0.07992  -0.1021   0.1488   0.9999
  14.750   1.4508   0.09136   0.08363  -0.1019   0.1378   0.9999
  15.000   1.4460   0.09516   0.08740  -0.1019   0.1281   0.9999
  15.250   1.4427   0.09877   0.09103  -0.1019   0.1190   0.9999
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