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DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DAE-31 AIRFOIL (dae31-il)
Reynolds number: 200,000
Max Cl/Cd: 91.28 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae31-il-200000.txt
Download as CSV file: xf-dae31-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-31 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250   0.0565   0.09494   0.09102  -0.1137   0.9217   0.0371
  -9.000   0.0594   0.09305   0.08913  -0.1156   0.9163   0.0379
  -8.750   0.0598   0.09115   0.08723  -0.1181   0.9117   0.0383
  -8.500   0.0755   0.08816   0.08425  -0.1169   0.9083   0.0389
  -8.250   0.0834   0.08613   0.08223  -0.1171   0.9035   0.0395
  -8.000   0.0910   0.08411   0.08022  -0.1175   0.8991   0.0404
  -7.750   0.0965   0.08209   0.07818  -0.1183   0.8951   0.0418
  -7.500   0.0864   0.08103   0.07719  -0.1205   0.8871   0.0429
  -7.250   0.0908   0.07870   0.07488  -0.1207   0.8823   0.0432
  -7.000   0.1084   0.07622   0.07238  -0.1194   0.8799   0.0443
  -6.750   0.1134   0.07456   0.07073  -0.1192   0.8756   0.0458
  -6.500   0.1095   0.07342   0.06965  -0.1191   0.8686   0.0473
  -6.250   0.1076   0.07102   0.06725  -0.1264   0.8619   0.0484
  -6.000   0.1211   0.06884   0.06506  -0.1228   0.8598   0.0491
  -5.750   0.1274   0.06738   0.06364  -0.1224   0.8538   0.0501
  -5.500   0.1367   0.06541   0.06167  -0.1237   0.8483   0.0516
  -5.250   0.1570   0.06087   0.05702  -0.1359   0.8431   0.0544
  -5.000   0.1688   0.05920   0.05536  -0.1328   0.8409   0.0552
  -4.750   0.1742   0.05806   0.05427  -0.1318   0.8329   0.0562
  -4.250   0.2222   0.05118   0.04719  -0.1416   0.8252   0.0621
  -4.000   0.2447   0.04908   0.04504  -0.1426   0.8230   0.0648
  -3.750   0.2632   0.04586   0.04165  -0.1472   0.8138   0.0694
  -3.500   0.2972   0.04272   0.03811  -0.1521   0.8100   0.0773
  -3.250   0.3178   0.04068   0.03620  -0.1514   0.8076   0.0789
  -3.000   0.3503   0.03809   0.03334  -0.1542   0.8055   0.0882
  -2.250   0.4387   0.02747   0.02085  -0.1574   0.7911   0.0542
  -2.000   0.4696   0.02541   0.01870  -0.1578   0.7889   0.0523
  -1.750   0.5026   0.02367   0.01657  -0.1581   0.7871   0.0509
  -1.500   0.5204   0.02348   0.01621  -0.1567   0.7793   0.0528
  -1.250   0.5488   0.02262   0.01510  -0.1563   0.7752   0.0546
  -1.000   0.5796   0.02163   0.01409  -0.1564   0.7725   0.0568
  -0.750   0.6117   0.02079   0.01314  -0.1565   0.7703   0.0603
  -0.500   0.6438   0.02002   0.01238  -0.1567   0.7684   0.0675
  -0.250   0.6601   0.02011   0.01259  -0.1551   0.7594   0.0734
   0.000   0.6901   0.01946   0.01199  -0.1551   0.7559   0.0893
   0.250   0.7222   0.01855   0.01133  -0.1555   0.7534   0.1531
   0.500   0.7524   0.01727   0.01106  -0.1558   0.7514   0.4837
   0.750   0.7745   0.01656   0.01133  -0.1546   0.7440   1.0000
   1.000   0.8033   0.01645   0.01105  -0.1544   0.7394   1.0000
   1.250   0.8354   0.01615   0.01059  -0.1546   0.7364   1.0000
   1.500   0.8688   0.01581   0.01009  -0.1550   0.7340   1.0000
   1.750   0.8888   0.01616   0.01041  -0.1538   0.7255   1.0000
   2.000   0.9191   0.01592   0.01007  -0.1538   0.7212   1.0000
   2.250   0.9522   0.01555   0.00958  -0.1542   0.7180   1.0000
   2.500   0.9761   0.01567   0.00967  -0.1534   0.7109   1.0000
   2.750   1.0045   0.01551   0.00945  -0.1532   0.7050   1.0000
   3.000   1.0373   0.01514   0.00898  -0.1535   0.7011   1.0000
   3.250   1.0611   0.01524   0.00907  -0.1527   0.6932   1.0000
   3.500   1.0900   0.01506   0.00884  -0.1526   0.6870   1.0000
   3.750   1.1233   0.01473   0.00840  -0.1531   0.6825   1.0000
   4.000   1.1442   0.01492   0.00863  -0.1518   0.6726   1.0000
   4.250   1.1764   0.01463   0.00826  -0.1522   0.6668   1.0000
   4.500   1.1983   0.01477   0.00843  -0.1511   0.6566   1.0000
   4.750   1.2297   0.01454   0.00811  -0.1513   0.6497   1.0000
   5.000   1.2512   0.01470   0.00829  -0.1501   0.6385   1.0000
   5.250   1.2781   0.01468   0.00824  -0.1497   0.6293   1.0000
   5.500   1.3032   0.01471   0.00825  -0.1491   0.6186   1.0000
   5.750   1.3260   0.01486   0.00840  -0.1481   0.6068   1.0000
   6.000   1.3513   0.01494   0.00843  -0.1475   0.5958   1.0000
   6.250   1.3756   0.01507   0.00853  -0.1468   0.5837   1.0000
   6.500   1.3961   0.01532   0.00879  -0.1455   0.5703   1.0000
   6.750   1.4174   0.01557   0.00902  -0.1443   0.5569   1.0000
   7.000   1.4388   0.01584   0.00926  -0.1431   0.5434   1.0000
   7.250   1.4594   0.01615   0.00951  -0.1419   0.5294   1.0000
   7.500   1.4787   0.01651   0.00981  -0.1404   0.5150   1.0000
   7.750   1.4947   0.01692   0.01022  -0.1385   0.4998   1.0000
   8.000   1.5098   0.01738   0.01067  -0.1364   0.4847   1.0000
   8.250   1.5236   0.01786   0.01114  -0.1341   0.4697   1.0000
   8.500   1.5343   0.01839   0.01163  -0.1313   0.4551   1.0000
   8.750   1.5440   0.01897   0.01219  -0.1284   0.4406   1.0000
   9.000   1.5530   0.01964   0.01282  -0.1256   0.4260   1.0000
   9.250   1.5614   0.02038   0.01351  -0.1228   0.4112   1.0000
   9.500   1.5685   0.02120   0.01431  -0.1200   0.3962   1.0000
   9.750   1.5753   0.02210   0.01520  -0.1172   0.3810   1.0000
  10.000   1.5819   0.02308   0.01616  -0.1146   0.3660   1.0000
  10.250   1.5882   0.02413   0.01721  -0.1121   0.3511   1.0000
  10.500   1.5942   0.02526   0.01832  -0.1096   0.3365   1.0000
  10.750   1.5997   0.02647   0.01951  -0.1072   0.3220   1.0000
  11.000   1.6048   0.02777   0.02077  -0.1049   0.3079   1.0000
  11.250   1.6092   0.02917   0.02213  -0.1026   0.2942   1.0000
  11.500   1.6137   0.03061   0.02356  -0.1004   0.2806   1.0000
  11.750   1.6182   0.03211   0.02507  -0.0984   0.2672   1.0000
  12.000   1.6224   0.03368   0.02666  -0.0964   0.2544   1.0000
  12.250   1.6260   0.03535   0.02832  -0.0944   0.2424   1.0000
  12.500   1.6282   0.03718   0.03009  -0.0925   0.2311   1.0000
  12.750   1.6320   0.03895   0.03191  -0.0909   0.2195   1.0000
  13.000   1.6354   0.04083   0.03382  -0.0893   0.2085   1.0000
  13.250   1.6376   0.04287   0.03585  -0.0877   0.1988   1.0000
  13.500   1.6400   0.04497   0.03797  -0.0863   0.1889   1.0000
  13.750   1.6434   0.04706   0.04013  -0.0851   0.1795   1.0000
  14.000   1.6447   0.04938   0.04242  -0.0838   0.1713   1.0000
  14.250   1.6475   0.05166   0.04479  -0.0828   0.1626   1.0000
  14.500   1.6492   0.05410   0.04728  -0.0818   0.1547   1.0000
  14.750   1.6497   0.05673   0.04991  -0.0809   0.1473   1.0000
  15.000   1.6516   0.05930   0.05259  -0.0802   0.1396   1.0000
  15.250   1.6501   0.06227   0.05552  -0.0794   0.1329   1.0000
  15.500   1.6508   0.06516   0.05855  -0.0790   0.1254   1.0000
  15.750   1.6489   0.06836   0.06179  -0.0786   0.1186   1.0000
  16.000   1.6465   0.07175   0.06524  -0.0785   0.1119   1.0000
  16.250   1.6446   0.07516   0.06875  -0.0784   0.1053   1.0000
  16.500   1.6395   0.07902   0.07257  -0.0785   0.0995   1.0000
  16.750   1.6374   0.08267   0.07639  -0.0788   0.0932   1.0000
  17.000   1.6326   0.08668   0.08043  -0.0792   0.0878   1.0000
  17.250   1.6279   0.09079   0.08463  -0.0798   0.0825   1.0000
  17.500   1.6233   0.09495   0.08888  -0.0804   0.0774   1.0000
  17.750   1.6170   0.09938   0.09331  -0.0813   0.0732   1.0000
  18.000   1.6123   0.10369   0.09778  -0.0823   0.0685   1.0000
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