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DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DAE-11 AIRFOIL (dae11-il)
Reynolds number: 200,000
Max Cl/Cd: 83.44 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dae11-il-200000-n5.txt
Download as CSV file: xf-dae11-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-11 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0500   0.09315   0.08837  -0.0736   0.7134   0.0288
  -8.500  -0.0498   0.09040   0.08564  -0.0765   0.7116   0.0312
  -8.250  -0.0471   0.08746   0.08271  -0.0788   0.7099   0.0314
  -8.000  -0.0471   0.08427   0.07953  -0.0817   0.7083   0.0316
  -7.500  -0.0401   0.07812   0.07347  -0.0851   0.7042   0.0317
  -7.250  -0.0301   0.07542   0.07079  -0.0848   0.7020   0.0320
  -7.000  -0.0226   0.07306   0.06845  -0.0852   0.6999   0.0323
  -6.750  -0.0151   0.07021   0.06562  -0.0873   0.6979   0.0324
  -6.500  -0.0116   0.06417   0.05957  -0.0936   0.6959   0.0266
  -6.000   0.0114   0.05398   0.04923  -0.1035   0.6924   0.0217
  -5.750   0.0287   0.04994   0.04509  -0.1077   0.6908   0.0214
  -5.500   0.0484   0.04409   0.03909  -0.1136   0.6885   0.0214
  -5.250   0.0693   0.03439   0.02873  -0.1206   0.6863   0.0218
  -5.000   0.0925   0.03016   0.02400  -0.1228   0.6842   0.0218
  -4.750   0.1174   0.02682   0.02010  -0.1241   0.6820   0.0218
  -4.500   0.1434   0.02452   0.01737  -0.1248   0.6801   0.0221
  -4.250   0.1701   0.02308   0.01567  -0.1251   0.6783   0.0225
  -4.000   0.1973   0.02191   0.01423  -0.1254   0.6768   0.0230
  -3.750   0.2249   0.02086   0.01292  -0.1255   0.6754   0.0237
  -3.500   0.2524   0.02001   0.01189  -0.1257   0.6728   0.0247
  -3.250   0.2803   0.01929   0.01091  -0.1258   0.6702   0.0264
  -3.000   0.3076   0.01862   0.01022  -0.1259   0.6679   0.0275
  -2.750   0.3353   0.01805   0.00957  -0.1260   0.6658   0.0286
  -2.500   0.3631   0.01751   0.00894  -0.1260   0.6637   0.0299
  -2.250   0.3912   0.01703   0.00833  -0.1259   0.6619   0.0316
  -2.000   0.4191   0.01665   0.00795  -0.1261   0.6604   0.0344
  -1.750   0.4469   0.01640   0.00765  -0.1261   0.6583   0.0377
  -1.500   0.4742   0.01614   0.00744  -0.1263   0.6553   0.0410
  -1.250   0.5019   0.01594   0.00723  -0.1264   0.6526   0.0473
  -1.000   0.5298   0.01573   0.00702  -0.1264   0.6502   0.0566
  -0.750   0.5579   0.01549   0.00682  -0.1266   0.6482   0.0761
  -0.500   0.5860   0.01518   0.00666  -0.1267   0.6463   0.1263
  -0.250   0.6138   0.01477   0.00656  -0.1270   0.6446   0.2373
   0.000   0.6398   0.01449   0.00673  -0.1271   0.6417   0.3820
   0.250   0.6645   0.01421   0.00693  -0.1268   0.6385   0.5340
   0.500   0.6858   0.01371   0.00702  -0.1253   0.6357   0.7307
   1.000   0.7510   0.01338   0.00680  -0.1268   0.6312   1.0000
   1.250   0.7797   0.01342   0.00669  -0.1269   0.6293   1.0000
   1.500   0.8061   0.01364   0.00689  -0.1269   0.6256   1.0000
   1.750   0.8329   0.01381   0.00702  -0.1269   0.6220   1.0000
   2.000   0.8605   0.01391   0.00705  -0.1269   0.6190   1.0000
   2.250   0.8886   0.01395   0.00702  -0.1270   0.6165   1.0000
   2.500   0.9172   0.01397   0.00696  -0.1271   0.6143   1.0000
   2.750   0.9430   0.01421   0.00721  -0.1270   0.6105   1.0000
   3.000   0.9691   0.01440   0.00740  -0.1269   0.6064   1.0000
   3.250   0.9964   0.01448   0.00745  -0.1269   0.6033   1.0000
   3.500   1.0246   0.01450   0.00742  -0.1269   0.6005   1.0000
   3.750   1.0514   0.01462   0.00753  -0.1269   0.5971   1.0000
   4.000   1.0762   0.01487   0.00782  -0.1267   0.5922   1.0000
   4.250   1.1029   0.01495   0.00790  -0.1266   0.5883   1.0000
   4.500   1.1309   0.01495   0.00787  -0.1266   0.5852   1.0000
   4.750   1.1556   0.01518   0.00814  -0.1264   0.5803   1.0000
   5.000   1.1806   0.01535   0.00836  -0.1261   0.5753   1.0000
   5.250   1.2077   0.01538   0.00839  -0.1260   0.5713   1.0000
   5.500   1.2328   0.01555   0.00859  -0.1258   0.5664   1.0000
   5.750   1.2566   0.01576   0.00885  -0.1254   0.5605   1.0000
   6.000   1.2835   0.01578   0.00885  -0.1252   0.5559   1.0000
   6.250   1.3062   0.01606   0.00922  -0.1247   0.5495   1.0000
   6.500   1.3306   0.01620   0.00938  -0.1243   0.5434   1.0000
   6.750   1.3547   0.01636   0.00957  -0.1239   0.5372   1.0000
   7.000   1.3769   0.01661   0.00988  -0.1232   0.5299   1.0000
   7.250   1.4002   0.01678   0.01007  -0.1226   0.5229   1.0000
   7.500   1.4209   0.01706   0.01040  -0.1217   0.5145   1.0000
   7.750   1.4413   0.01735   0.01072  -0.1208   0.5061   1.0000
   8.000   1.4615   0.01763   0.01101  -0.1198   0.4972   1.0000
   8.250   1.4775   0.01807   0.01151  -0.1183   0.4872   1.0000
   8.500   1.4938   0.01847   0.01193  -0.1168   0.4774   1.0000
   8.750   1.5058   0.01895   0.01241  -0.1146   0.4666   1.0000
   9.000   1.5129   0.01967   0.01317  -0.1119   0.4552   1.0000
   9.250   1.5204   0.02049   0.01401  -0.1096   0.4434   1.0000
   9.500   1.5275   0.02143   0.01494  -0.1074   0.4309   1.0000
   9.750   1.5336   0.02251   0.01601  -0.1053   0.4175   1.0000
  10.000   1.5387   0.02372   0.01721  -0.1032   0.4037   1.0000
  10.250   1.5427   0.02507   0.01854  -0.1011   0.3892   1.0000
  10.500   1.5458   0.02655   0.01999  -0.0991   0.3744   1.0000
  10.750   1.5484   0.02813   0.02155  -0.0971   0.3595   1.0000
  11.000   1.5499   0.02983   0.02323  -0.0952   0.3443   1.0000
  11.250   1.5508   0.03165   0.02503  -0.0933   0.3287   1.0000
  11.500   1.5510   0.03357   0.02692  -0.0915   0.3131   1.0000
  11.750   1.5507   0.03558   0.02891  -0.0898   0.2977   1.0000
  12.000   1.5495   0.03773   0.03102  -0.0881   0.2821   1.0000
  12.250   1.5488   0.03993   0.03320  -0.0866   0.2671   1.0000
  12.500   1.5480   0.04225   0.03550  -0.0852   0.2519   1.0000
  12.750   1.5469   0.04469   0.03792  -0.0839   0.2370   1.0000
  13.000   1.5455   0.04725   0.04046  -0.0828   0.2220   1.0000
  13.250   1.5444   0.04985   0.04305  -0.0818   0.2077   1.0000
  13.500   1.5430   0.05258   0.04576  -0.0808   0.1937   1.0000
  13.750   1.5413   0.05542   0.04859  -0.0800   0.1801   1.0000
  14.000   1.5398   0.05834   0.05149  -0.0793   0.1671   1.0000
  14.250   1.5378   0.06136   0.05450  -0.0787   0.1544   1.0000
  14.500   1.5354   0.06452   0.05765  -0.0783   0.1426   1.0000
  14.750   1.5333   0.06772   0.06086  -0.0779   0.1307   1.0000
  15.000   1.5319   0.07090   0.06406  -0.0776   0.1196   1.0000
  15.250   1.5302   0.07419   0.06737  -0.0775   0.1095   1.0000
  15.500   1.5279   0.07762   0.07081  -0.0774   0.1002   1.0000
  15.750   1.5248   0.08124   0.07445  -0.0775   0.0915   1.0000
  16.000   1.5224   0.08482   0.07807  -0.0777   0.0832   1.0000
  16.250   1.5207   0.08834   0.08164  -0.0779   0.0761   1.0000
  16.500   1.5168   0.09226   0.08560  -0.0783   0.0697   1.0000
  16.750   1.5151   0.09592   0.08933  -0.0788   0.0637   1.0000
  17.000   1.5119   0.09985   0.09331  -0.0794   0.0586   1.0000
  17.250   1.5093   0.10373   0.09726  -0.0801   0.0537   1.0000
  17.500   1.5056   0.10781   0.10141  -0.0810   0.0499   1.0000
  17.750   1.5035   0.11173   0.10541  -0.0819   0.0459   1.0000
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