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DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DAE-21 AIRFOIL (dae21-il)
Reynolds number: 200,000
Max Cl/Cd: 86.26 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae21-il-200000.txt
Download as CSV file: xf-dae21-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAE-21 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0228   0.09547   0.09143  -0.0829   0.8254   0.0370
  -8.500  -0.0169   0.09313   0.08910  -0.0844   0.8217   0.0386
  -8.250  -0.0215   0.09159   0.08757  -0.0878   0.8179   0.0395
  -8.000  -0.0211   0.08902   0.08502  -0.0901   0.8147   0.0399
  -7.750   0.0001   0.08565   0.08165  -0.0885   0.8120   0.0407
  -7.500   0.0104   0.08331   0.07933  -0.0890   0.8081   0.0416
  -7.250   0.0181   0.08105   0.07708  -0.0899   0.8045   0.0427
  -7.000   0.0236   0.07880   0.07484  -0.0908   0.8012   0.0438
  -6.750   0.0242   0.07689   0.07293  -0.0921   0.7981   0.0451
  -6.500   0.0237   0.07447   0.07058  -0.1022   0.7920   0.0462
  -6.250   0.0337   0.07112   0.06725  -0.1022   0.7886   0.0467
  -6.000   0.0464   0.06896   0.06508  -0.1001   0.7859   0.0476
  -5.750   0.0592   0.06673   0.06283  -0.1008   0.7833   0.0487
  -5.500   0.0731   0.06425   0.06033  -0.1036   0.7800   0.0506
  -5.250   0.1020   0.05814   0.05404  -0.1210   0.7741   0.0543
  -5.000   0.1127   0.05632   0.05231  -0.1178   0.7710   0.0551
  -4.750   0.1284   0.05448   0.05046  -0.1173   0.7682   0.0566
  -4.500   0.1667   0.04922   0.04465  -0.1293   0.7655   0.0635
  -4.250   0.1806   0.04684   0.04245  -0.1280   0.7620   0.0646
  -4.000   0.1986   0.04559   0.04128  -0.1278   0.7574   0.0669
  -3.750   0.2305   0.04182   0.03714  -0.1331   0.7539   0.0757
  -3.500   0.2509   0.04025   0.03562  -0.1326   0.7511   0.0785
  -3.250   0.2825   0.03735   0.03227  -0.1357   0.7489   0.0886
  -3.000   0.3052   0.03576   0.03072  -0.1357   0.7463   0.0920
  -2.750   0.3322   0.03410   0.02881  -0.1376   0.7406   0.1037
  -2.500   0.3571   0.03271   0.02741  -0.1377   0.7370   0.1095
  -2.250   0.4020   0.02556   0.01862  -0.1389   0.7348   0.0531
  -2.000   0.4310   0.02413   0.01687  -0.1388   0.7325   0.0530
  -1.750   0.4601   0.02276   0.01522  -0.1385   0.7306   0.0524
  -1.500   0.4849   0.02231   0.01465  -0.1384   0.7247   0.0527
  -1.250   0.5123   0.02179   0.01396  -0.1381   0.7208   0.0540
  -1.000   0.5401   0.02092   0.01314  -0.1380   0.7180   0.0583
  -0.750   0.5689   0.02030   0.01244  -0.1377   0.7157   0.0619
  -0.500   0.5977   0.01959   0.01174  -0.1374   0.7138   0.0673
  -0.250   0.6204   0.01974   0.01199  -0.1372   0.7072   0.0772
   0.000   0.6481   0.01932   0.01165  -0.1371   0.7034   0.1020
   0.250   0.6738   0.01785   0.01150  -0.1371   0.7007   0.4969
   0.750   0.7330   0.01664   0.01100  -0.1364   0.6961   1.0000
   1.000   0.7556   0.01720   0.01152  -0.1361   0.6890   1.0000
   1.250   0.7841   0.01718   0.01136  -0.1360   0.6856   1.0000
   1.500   0.8139   0.01704   0.01109  -0.1359   0.6831   1.0000
   1.750   0.8443   0.01689   0.01080  -0.1359   0.6810   1.0000
   2.000   0.8661   0.01746   0.01138  -0.1355   0.6738   1.0000
   2.250   0.8942   0.01745   0.01130  -0.1353   0.6699   1.0000
   2.500   0.9243   0.01726   0.01101  -0.1353   0.6671   1.0000
   2.750   0.9553   0.01705   0.01068  -0.1354   0.6649   1.0000
   3.000   0.9765   0.01757   0.01126  -0.1348   0.6573   1.0000
   3.250   1.0052   0.01747   0.01111  -0.1347   0.6533   1.0000
   3.500   1.0361   0.01721   0.01076  -0.1348   0.6505   1.0000
   3.750   1.0622   0.01734   0.01088  -0.1345   0.6454   1.0000
   4.000   1.0874   0.01747   0.01103  -0.1341   0.6393   1.0000
   4.250   1.1178   0.01721   0.01072  -0.1342   0.6356   1.0000
   4.500   1.1486   0.01699   0.01042  -0.1343   0.6322   1.0000
   4.750   1.1701   0.01732   0.01085  -0.1336   0.6242   1.0000
   5.000   1.2003   0.01707   0.01055  -0.1336   0.6198   1.0000
   5.250   1.2276   0.01706   0.01053  -0.1334   0.6144   1.0000
   5.500   1.2524   0.01713   0.01064  -0.1329   0.6072   1.0000
   5.750   1.2836   0.01685   0.01031  -0.1331   0.6026   1.0000
   6.000   1.3057   0.01710   0.01064  -0.1324   0.5945   1.0000
   6.250   1.3346   0.01693   0.01044  -0.1323   0.5884   1.0000
   6.500   1.3585   0.01706   0.01064  -0.1317   0.5805   1.0000
   6.750   1.3858   0.01698   0.01054  -0.1315   0.5731   1.0000
   7.000   1.4090   0.01711   0.01073  -0.1307   0.5643   1.0000
   7.250   1.4363   0.01703   0.01062  -0.1305   0.5561   1.0000
   7.500   1.4571   0.01725   0.01092  -0.1295   0.5457   1.0000
   7.750   1.4818   0.01731   0.01097  -0.1289   0.5362   1.0000
   8.000   1.5044   0.01744   0.01111  -0.1280   0.5254   1.0000
   8.250   1.5232   0.01772   0.01147  -0.1267   0.5131   1.0000
   8.500   1.5427   0.01798   0.01175  -0.1254   0.5008   1.0000
   8.750   1.5615   0.01828   0.01204  -0.1241   0.4879   1.0000
   9.000   1.5786   0.01864   0.01240  -0.1225   0.4744   1.0000
   9.250   1.5933   0.01909   0.01283  -0.1206   0.4603   1.0000
   9.500   1.6044   0.01964   0.01337  -0.1182   0.4458   1.0000
   9.750   1.6096   0.02031   0.01405  -0.1149   0.4314   1.0000
  10.000   1.6137   0.02113   0.01488  -0.1118   0.4168   1.0000
  10.250   1.6172   0.02211   0.01585  -0.1089   0.4018   1.0000
  10.500   1.6203   0.02322   0.01695  -0.1061   0.3865   1.0000
  10.750   1.6226   0.02449   0.01819  -0.1035   0.3707   1.0000
  11.000   1.6242   0.02589   0.01956  -0.1010   0.3548   1.0000
  11.250   1.6253   0.02742   0.02108  -0.0986   0.3389   1.0000
  11.500   1.6257   0.02909   0.02271  -0.0963   0.3230   1.0000
  11.750   1.6255   0.03089   0.02448  -0.0941   0.3071   1.0000
  12.000   1.6247   0.03280   0.02637  -0.0920   0.2915   1.0000
  12.250   1.6235   0.03484   0.02837  -0.0901   0.2761   1.0000
  12.500   1.6217   0.03701   0.03052  -0.0882   0.2608   1.0000
  12.750   1.6195   0.03929   0.03279  -0.0865   0.2459   1.0000
  13.000   1.6173   0.04169   0.03517  -0.0849   0.2313   1.0000
  13.250   1.6146   0.04425   0.03772  -0.0835   0.2167   1.0000
  13.500   1.6122   0.04692   0.04037  -0.0823   0.2027   1.0000
  13.750   1.6092   0.04973   0.04317  -0.0812   0.1889   1.0000
  14.000   1.6062   0.05267   0.04610  -0.0802   0.1758   1.0000
  14.250   1.6031   0.05572   0.04915  -0.0794   0.1635   1.0000
  14.500   1.5995   0.05890   0.05232  -0.0787   0.1519   1.0000
  14.750   1.5951   0.06227   0.05565  -0.0781   0.1415   1.0000
  15.000   1.5908   0.06574   0.05912  -0.0777   0.1315   1.0000
  15.250   1.5886   0.06905   0.06247  -0.0774   0.1219   1.0000
  15.500   1.5850   0.07257   0.06601  -0.0771   0.1137   1.0000
  15.750   1.5802   0.07632   0.06974  -0.0771   0.1063   1.0000
  16.000   1.5788   0.07976   0.07327  -0.0771   0.0990   1.0000
  16.250   1.5739   0.08360   0.07705  -0.0772   0.0931   1.0000
  16.500   1.5731   0.08708   0.08066  -0.0775   0.0870   1.0000
  16.750   1.5692   0.09086   0.08438  -0.0777   0.0821   1.0000
  17.000   1.5686   0.09442   0.08809  -0.0781   0.0771   1.0000
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