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DOUGLAS LA203A AIRFOIL (la203a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: DOUGLAS LA203A AIRFOIL (la203a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 160.47 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-la203a-il-1000000.txt
Download as CSV file: xf-la203a-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0814   0.09880   0.09570  -0.0891   0.7292   0.0287
 -10.000  -0.0727   0.09621   0.09309  -0.0904   0.7260   0.0291
  -9.750  -0.0645   0.09347   0.09036  -0.0919   0.7228   0.0297
  -9.500  -0.0062   0.07358   0.07053  -0.1019   0.7105   0.0319
  -9.250   0.0017   0.07104   0.06800  -0.1025   0.7080   0.0321
  -9.000   0.0098   0.06848   0.06544  -0.1032   0.7053   0.0322
  -8.750   0.0175   0.06592   0.06287  -0.1040   0.7025   0.0324
  -8.500   0.0247   0.06324   0.06016  -0.1049   0.6996   0.0326
  -8.250  -0.1498   0.03637   0.03281  -0.1470   0.7061   0.0322
  -8.000  -0.1310   0.03453   0.03087  -0.1491   0.7032   0.0323
  -7.750  -0.1361   0.02010   0.01514  -0.1588   0.7004   0.0307
  -7.500  -0.1098   0.01841   0.01315  -0.1599   0.6970   0.0310
  -7.250  -0.0820   0.01736   0.01192  -0.1607   0.6947   0.0313
  -7.000  -0.0532   0.01685   0.01131  -0.1613   0.6922   0.0316
  -6.750  -0.0256   0.01537   0.00963  -0.1622   0.6897   0.0321
  -6.500   0.0028   0.01461   0.00880  -0.1628   0.6871   0.0324
  -6.250   0.0315   0.01416   0.00830  -0.1633   0.6843   0.0327
  -6.000   0.0605   0.01381   0.00789  -0.1637   0.6811   0.0330
  -5.750   0.0898   0.01340   0.00745  -0.1642   0.6790   0.0334
  -5.500   0.1191   0.01300   0.00702  -0.1646   0.6767   0.0338
  -5.250   0.1485   0.01262   0.00661  -0.1650   0.6741   0.0342
  -5.000   0.1779   0.01225   0.00620  -0.1655   0.6713   0.0346
  -4.750   0.2074   0.01191   0.00582  -0.1659   0.6686   0.0350
  -4.500   0.2369   0.01165   0.00549  -0.1662   0.6657   0.0355
  -4.250   0.2667   0.01142   0.00522  -0.1667   0.6631   0.0359
  -4.000   0.2967   0.01101   0.00480  -0.1672   0.6606   0.0364
  -3.750   0.3270   0.01056   0.00436  -0.1679   0.6577   0.0372
  -3.500   0.3571   0.01035   0.00416  -0.1684   0.6548   0.0378
  -3.250   0.3870   0.01020   0.00400  -0.1688   0.6518   0.0386
  -3.000   0.4169   0.01008   0.00384  -0.1692   0.6484   0.0395
  -2.750   0.4473   0.00992   0.00368  -0.1698   0.6458   0.0403
  -2.500   0.4776   0.00978   0.00353  -0.1702   0.6430   0.0409
  -2.250   0.5092   0.00944   0.00321  -0.1712   0.6399   0.0421
  -2.000   0.5398   0.00930   0.00307  -0.1717   0.6368   0.0432
  -1.750   0.5700   0.00921   0.00297  -0.1722   0.6335   0.0444
  -1.500   0.6002   0.00917   0.00289  -0.1727   0.6298   0.0457
  -1.250   0.6313   0.00900   0.00274  -0.1734   0.6272   0.0472
  -1.000   0.6622   0.00888   0.00265  -0.1740   0.6240   0.0494
  -0.750   0.6926   0.00881   0.00259  -0.1745   0.6205   0.0515
  -0.500   0.7232   0.00873   0.00249  -0.1751   0.6170   0.0543
  -0.250   0.7533   0.00872   0.00245  -0.1756   0.6130   0.0577
   0.000   0.7842   0.00862   0.00241  -0.1762   0.6101   0.0638
   0.250   0.8151   0.00853   0.00239  -0.1768   0.6067   0.0767
   0.750   0.8893   0.00757   0.00237  -0.1818   0.5992   0.4543
   1.000   0.9224   0.00744   0.00250  -0.1831   0.5950   0.5795
   1.250   0.9530   0.00742   0.00258  -0.1836   0.5919   0.6159
   1.500   0.9829   0.00745   0.00265  -0.1840   0.5883   0.6369
   1.750   1.0123   0.00751   0.00273  -0.1842   0.5845   0.6536
   2.000   1.0411   0.00760   0.00280  -0.1844   0.5802   0.6667
   2.250   1.0701   0.00769   0.00289  -0.1845   0.5763   0.6782
   2.500   1.0995   0.00772   0.00298  -0.1848   0.5726   0.6907
   2.750   1.1285   0.00780   0.00305  -0.1849   0.5686   0.7001
   3.000   1.1570   0.00788   0.00314  -0.1851   0.5644   0.7068
   3.250   1.1853   0.00800   0.00324  -0.1851   0.5599   0.7118
   3.500   1.2145   0.00805   0.00331  -0.1854   0.5560   0.7167
   3.750   1.2432   0.00812   0.00340  -0.1856   0.5514   0.7221
   4.000   1.2711   0.00823   0.00350  -0.1856   0.5465   0.7276
   4.250   1.2991   0.00835   0.00362  -0.1856   0.5416   0.7336
   4.500   1.3277   0.00842   0.00371  -0.1858   0.5361   0.7400
   4.750   1.3549   0.00854   0.00383  -0.1857   0.5291   0.7466
   5.000   1.3825   0.00866   0.00396  -0.1857   0.5218   0.7529
   5.250   1.4095   0.00880   0.00408  -0.1855   0.5128   0.7590
   5.500   1.4362   0.00895   0.00423  -0.1854   0.5030   0.7656
   5.750   1.4614   0.00918   0.00441  -0.1849   0.4910   0.7725
   6.000   1.4877   0.00935   0.00458  -0.1847   0.4786   0.7793
   6.250   1.5131   0.00956   0.00478  -0.1843   0.4669   0.7872
   6.750   1.5629   0.01004   0.00523  -0.1834   0.4447   0.8038
   7.000   1.5873   0.01030   0.00547  -0.1829   0.4341   0.8129
   7.250   1.6100   0.01062   0.00577  -0.1821   0.4220   0.8222
   7.500   1.6332   0.01091   0.00605  -0.1814   0.4088   0.8326
   7.750   1.6544   0.01128   0.00639  -0.1803   0.3938   0.8445
   8.000   1.6740   0.01170   0.00678  -0.1789   0.3772   0.8572
   8.250   1.6912   0.01221   0.00723  -0.1772   0.3583   0.8715
   8.500   1.7044   0.01283   0.00778  -0.1747   0.3369   0.8887
   8.750   1.7101   0.01351   0.00840  -0.1708   0.3115   0.9139
   9.000   1.7027   0.01420   0.00904  -0.1644   0.2878   0.9999
   9.250   1.7018   0.01557   0.01021  -0.1602   0.2544   0.9999
   9.500   1.7016   0.01705   0.01153  -0.1565   0.2260   0.9999
   9.750   1.7011   0.01873   0.01307  -0.1531   0.2017   0.9999
  10.000   1.7017   0.02052   0.01475  -0.1503   0.1794   0.9999
  10.250   1.7018   0.02250   0.01663  -0.1477   0.1598   0.9999
  10.500   1.7033   0.02448   0.01854  -0.1455   0.1435   0.9999
  10.750   1.7054   0.02648   0.02048  -0.1434   0.1291   0.9999
  11.000   1.7071   0.02855   0.02249  -0.1414   0.1163   0.9999
  11.250   1.7087   0.03064   0.02454  -0.1395   0.1052   0.9999
  11.500   1.7111   0.03269   0.02657  -0.1377   0.0957   0.9999
  11.750   1.7131   0.03478   0.02864  -0.1359   0.0874   0.9999
  12.000   1.7145   0.03696   0.03081  -0.1341   0.0802   0.9999
  12.250   1.7155   0.03924   0.03307  -0.1324   0.0736   0.9999
  12.500   1.7185   0.04137   0.03521  -0.1309   0.0683   0.9999
  12.750   1.7203   0.04364   0.03747  -0.1294   0.0633   0.9999
  13.000   1.7231   0.04587   0.03973  -0.1281   0.0590   0.9999
  13.250   1.7255   0.04820   0.04207  -0.1268   0.0553   0.9999
  13.500   1.7289   0.05043   0.04432  -0.1256   0.0521   0.9999
  13.750   1.7303   0.05293   0.04683  -0.1244   0.0491   0.9999
  14.000   1.7348   0.05512   0.04905  -0.1234   0.0467   0.9999
  14.250   1.7357   0.05775   0.05170  -0.1223   0.0444   0.9999
  14.500   1.7395   0.06006   0.05405  -0.1214   0.0426   0.9999
  14.750   1.7420   0.06255   0.05659  -0.1205   0.0408   0.9999
  15.000   1.7435   0.06516   0.05921  -0.1196   0.0389   0.9999
  15.250   1.7442   0.06792   0.06202  -0.1187   0.0376   0.9999
  15.500   1.7488   0.07025   0.06439  -0.1180   0.0363   0.9999
  15.750   1.7500   0.07300   0.06719  -0.1173   0.0351   0.9999
  16.000   1.7506   0.07579   0.07001  -0.1167   0.0339   0.9999
  16.250   1.7495   0.07885   0.07312  -0.1160   0.0328   0.9999
  16.500   1.7530   0.08135   0.07569  -0.1155   0.0320   0.9999
  16.750   1.7543   0.08417   0.07856  -0.1151   0.0312   0.9999
  17.000   1.7549   0.08706   0.08150  -0.1146   0.0303   0.9999
  17.250   1.7535   0.09023   0.08471  -0.1143   0.0295   0.9999
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