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DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DAE-21 AIRFOIL (dae21-il)
Reynolds number: 500,000
Max Cl/Cd: 136.48 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dae21-il-500000.txt
Download as CSV file: xf-dae21-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.0253   0.09115   0.08804  -0.0652   0.7551   0.0185
  -9.250  -0.0178   0.08818   0.08506  -0.0662   0.7530   0.0188
  -9.000  -0.0528   0.09395   0.09059  -0.0743   0.7621   0.0184
  -8.750  -0.0439   0.09149   0.08815  -0.0754   0.7594   0.0187
  -8.500  -0.0355   0.08898   0.08564  -0.0766   0.7568   0.0192
  -8.250  -0.0279   0.08639   0.08306  -0.0778   0.7543   0.0195
  -8.000  -0.0208   0.08373   0.08039  -0.0791   0.7518   0.0201
  -7.750  -0.0226   0.08048   0.07714  -0.0819   0.7490   0.0210
  -7.500  -0.0260   0.07699   0.07368  -0.0849   0.7460   0.0212
  -7.250  -0.0168   0.07431   0.07104  -0.0848   0.7436   0.0214
  -7.000  -0.0055   0.07231   0.06905  -0.0847   0.7409   0.0216
  -6.750   0.0012   0.07029   0.06705  -0.0850   0.7381   0.0218
  -6.500   0.0096   0.06806   0.06481  -0.0863   0.7354   0.0221
  -6.250   0.0196   0.06553   0.06227  -0.0884   0.7328   0.0227
  -6.000   0.0311   0.06272   0.05943  -0.0915   0.7302   0.0236
  -5.750   0.0512   0.05411   0.05077  -0.1074   0.7272   0.0250
  -5.500   0.0635   0.05232   0.04901  -0.1066   0.7244   0.0253
  -5.250   0.0817   0.05013   0.04680  -0.1082   0.7216   0.0256
  -5.000   0.1024   0.04761   0.04424  -0.1107   0.7190   0.0261
  -4.750   0.1262   0.04428   0.04081  -0.1147   0.7166   0.0269
  -4.500   0.1614   0.03482   0.03089  -0.1250   0.7143   0.0296
  -4.250   0.1844   0.03355   0.02962  -0.1258   0.7118   0.0301
  -4.000   0.2180   0.02953   0.02498  -0.1292   0.7091   0.0340
  -3.750   0.2414   0.02647   0.02194  -0.1305   0.7064   0.0348
  -3.500   0.2674   0.02530   0.02074  -0.1311   0.7036   0.0358
  -3.000   0.3284   0.01737   0.01144  -0.1328   0.6991   0.0298
  -2.750   0.3570   0.01566   0.00948  -0.1329   0.6965   0.0274
  -2.500   0.3860   0.01430   0.00788  -0.1330   0.6938   0.0270
  -2.250   0.4147   0.01350   0.00694  -0.1330   0.6908   0.0276
  -2.000   0.4434   0.01288   0.00620  -0.1330   0.6879   0.0283
  -1.750   0.4722   0.01242   0.00562  -0.1330   0.6851   0.0294
  -1.500   0.5005   0.01193   0.00513  -0.1331   0.6826   0.0312
  -1.250   0.5291   0.01163   0.00478  -0.1332   0.6798   0.0326
  -1.000   0.5577   0.01136   0.00450  -0.1333   0.6767   0.0341
  -0.750   0.5862   0.01096   0.00414  -0.1334   0.6733   0.0366
  -0.500   0.6150   0.01073   0.00389  -0.1335   0.6702   0.0406
  -0.250   0.6438   0.01053   0.00367  -0.1336   0.6673   0.0462
   0.000   0.6727   0.01032   0.00347  -0.1337   0.6644   0.0623
   0.250   0.7008   0.00981   0.00342  -0.1340   0.6609   0.1954
   0.500   0.7286   0.00938   0.00347  -0.1343   0.6572   0.3737
   0.750   0.7557   0.00896   0.00352  -0.1343   0.6537   0.5595
   1.000   0.7838   0.00805   0.00349  -0.1341   0.6506   1.0000
   1.250   0.8124   0.00813   0.00348  -0.1342   0.6472   1.0000
   1.500   0.8407   0.00817   0.00349  -0.1343   0.6430   1.0000
   1.750   0.8692   0.00821   0.00347  -0.1343   0.6389   1.0000
   2.000   0.8977   0.00825   0.00344  -0.1344   0.6352   1.0000
   2.250   0.9261   0.00834   0.00346  -0.1345   0.6312   1.0000
   2.500   0.9541   0.00839   0.00351  -0.1345   0.6263   1.0000
   2.750   0.9823   0.00843   0.00351  -0.1346   0.6217   1.0000
   3.000   1.0106   0.00852   0.00351  -0.1346   0.6175   1.0000
   3.250   1.0383   0.00859   0.00360  -0.1347   0.6122   1.0000
   3.500   1.0661   0.00864   0.00364  -0.1347   0.6068   1.0000
   3.750   1.0940   0.00874   0.00366  -0.1347   0.6019   1.0000
   4.000   1.1213   0.00882   0.00377  -0.1347   0.5959   1.0000
   4.250   1.1488   0.00890   0.00383  -0.1347   0.5898   1.0000
   4.500   1.1761   0.00901   0.00391  -0.1346   0.5841   1.0000
   4.750   1.2031   0.00910   0.00404  -0.1346   0.5772   1.0000
   5.000   1.2301   0.00924   0.00411  -0.1345   0.5709   1.0000
   5.250   1.2568   0.00935   0.00426  -0.1344   0.5634   1.0000
   5.500   1.2832   0.00949   0.00437  -0.1342   0.5561   1.0000
   5.750   1.3094   0.00963   0.00454  -0.1341   0.5478   1.0000
   6.250   1.3607   0.00997   0.00487  -0.1336   0.5298   1.0000
   6.500   1.3857   0.01018   0.00506  -0.1332   0.5203   1.0000
   6.750   1.4101   0.01041   0.00527  -0.1328   0.5098   1.0000
   7.000   1.4343   0.01064   0.00551  -0.1324   0.4985   1.0000
   7.250   1.4575   0.01092   0.00578  -0.1318   0.4866   1.0000
   7.500   1.4796   0.01124   0.00607  -0.1310   0.4738   1.0000
   7.750   1.5007   0.01161   0.00640  -0.1301   0.4603   1.0000
   8.000   1.5207   0.01201   0.00677  -0.1291   0.4460   1.0000
   8.250   1.5396   0.01243   0.00717  -0.1278   0.4312   1.0000
   8.500   1.5568   0.01291   0.00761  -0.1264   0.4161   1.0000
   8.750   1.5718   0.01344   0.00811  -0.1246   0.4009   1.0000
   9.000   1.5819   0.01404   0.00868  -0.1219   0.3851   1.0000
   9.250   1.5878   0.01475   0.00936  -0.1187   0.3701   1.0000
   9.500   1.5925   0.01565   0.01021  -0.1157   0.3545   1.0000
   9.750   1.5974   0.01669   0.01120  -0.1130   0.3386   1.0000
  10.000   1.6020   0.01786   0.01233  -0.1105   0.3224   1.0000
  10.250   1.6069   0.01911   0.01353  -0.1082   0.3068   1.0000
  10.500   1.6108   0.02049   0.01486  -0.1059   0.2907   1.0000
  10.750   1.6149   0.02193   0.01625  -0.1037   0.2751   1.0000
  11.000   1.6183   0.02347   0.01774  -0.1016   0.2596   1.0000
  11.250   1.6220   0.02505   0.01928  -0.0997   0.2445   1.0000
  11.500   1.6245   0.02675   0.02093  -0.0977   0.2292   1.0000
  11.750   1.6279   0.02845   0.02259  -0.0959   0.2151   1.0000
  12.000   1.6309   0.03022   0.02433  -0.0942   0.2013   1.0000
  12.250   1.6331   0.03209   0.02616  -0.0925   0.1874   1.0000
  12.500   1.6354   0.03401   0.02805  -0.0909   0.1740   1.0000
  12.750   1.6373   0.03605   0.03006  -0.0895   0.1611   1.0000
  13.000   1.6394   0.03814   0.03212  -0.0881   0.1489   1.0000
  13.250   1.6414   0.04032   0.03427  -0.0869   0.1376   1.0000
  13.500   1.6427   0.04263   0.03656  -0.0857   0.1270   1.0000
  13.750   1.6434   0.04506   0.03897  -0.0846   0.1166   1.0000
  14.000   1.6454   0.04744   0.04133  -0.0837   0.1074   1.0000
  14.250   1.6472   0.04988   0.04379  -0.0828   0.0988   1.0000
  14.500   1.6483   0.05246   0.04637  -0.0820   0.0912   1.0000
  14.750   1.6483   0.05525   0.04915  -0.0814   0.0839   1.0000
  15.000   1.6505   0.05785   0.05179  -0.0808   0.0778   1.0000
  15.250   1.6494   0.06088   0.05483  -0.0803   0.0721   1.0000
  15.500   1.6513   0.06363   0.05763  -0.0800   0.0671   1.0000
  15.750   1.6495   0.06689   0.06091  -0.0797   0.0624   1.0000
  16.000   1.6510   0.06980   0.06388  -0.0796   0.0583   1.0000
  16.250   1.6468   0.07351   0.06761  -0.0795   0.0544   1.0000
  16.500   1.6489   0.07644   0.07063  -0.0796   0.0512   1.0000
  16.750   1.6456   0.08017   0.07440  -0.0798   0.0482   1.0000
  17.000   1.6438   0.08378   0.07809  -0.0800   0.0455   1.0000
  17.250   1.6426   0.08734   0.08173  -0.0804   0.0432   1.0000
  17.500   1.6372   0.09156   0.08599  -0.0810   0.0410   1.0000
  17.750   1.6343   0.09551   0.09002  -0.0817   0.0391   1.0000
  18.000   1.6328   0.09929   0.09390  -0.0824   0.0373   1.0000
  18.250   1.6283   0.10357   0.09824  -0.0834   0.0357   1.0000
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