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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 50,000
Max Cl/Cd: 37.44 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1138-il-50000-n5.txt
Download as CSV file: xf-dga1138-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: D.G.A. 1138                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4915   0.11322   0.10621  -0.0118   1.0000   0.1224
  -9.500  -0.5010   0.11114   0.10425  -0.0153   1.0000   0.1239
  -9.250  -0.5087   0.10852   0.10174  -0.0183   1.0000   0.1243
  -8.750  -0.4965   0.09942   0.09272  -0.0192   1.0000   0.1255
  -8.500  -0.4911   0.08940   0.08262  -0.0257   1.0000   0.0692
  -8.250  -0.4855   0.08526   0.07850  -0.0264   1.0000   0.0664
  -8.000  -0.4821   0.08057   0.07384  -0.0290   1.0000   0.0638
  -7.750  -0.4785   0.07499   0.06823  -0.0331   1.0000   0.0611
  -7.500  -0.4714   0.07063   0.06382  -0.0350   1.0000   0.0617
  -7.250  -0.4627   0.06667   0.05979  -0.0362   1.0000   0.0639
  -7.000  -0.4529   0.06200   0.05498  -0.0381   1.0000   0.0649
  -6.750  -0.4414   0.05695   0.04973  -0.0397   1.0000   0.0646
  -6.500  -0.4280   0.05178   0.04427  -0.0411   1.0000   0.0643
  -6.250  -0.4127   0.04712   0.03923  -0.0418   1.0000   0.0659
  -6.000  -0.3956   0.04212   0.03355  -0.0426   1.0000   0.0696
  -5.750  -0.3768   0.03794   0.02871  -0.0424   1.0000   0.0708
  -5.500  -0.3575   0.03511   0.02554  -0.0417   1.0000   0.0722
  -5.250  -0.3369   0.03289   0.02300  -0.0409   1.0000   0.0742
  -5.000  -0.3156   0.03125   0.02095  -0.0401   1.0000   0.0801
  -4.750  -0.2923   0.02907   0.01815  -0.0393   1.0000   0.0826
  -4.500  -0.2688   0.02733   0.01608  -0.0385   1.0000   0.0834
  -4.250  -0.2454   0.02599   0.01451  -0.0376   1.0000   0.0847
  -4.000  -0.2213   0.02488   0.01319  -0.0369   1.0000   0.0864
  -3.750  -0.1965   0.02394   0.01201  -0.0362   1.0000   0.0888
  -3.500  -0.1715   0.02316   0.01100  -0.0355   1.0000   0.0920
  -3.250  -0.1457   0.02251   0.01013  -0.0349   1.0000   0.0962
  -3.000  -0.1209   0.02200   0.00957  -0.0344   1.0000   0.1024
  -2.750  -0.0963   0.02157   0.00907  -0.0339   1.0000   0.1143
  -2.500  -0.0720   0.02120   0.00880  -0.0334   1.0000   0.1417
  -2.250  -0.0475   0.02083   0.00856  -0.0330   1.0000   0.1880
  -2.000  -0.0234   0.02058   0.00838  -0.0326   1.0000   0.2436
  -1.750   0.0006   0.02031   0.00825  -0.0323   1.0000   0.2987
  -1.500   0.0247   0.02000   0.00814  -0.0321   1.0000   0.3491
  -1.250   0.0546   0.01816   0.00812  -0.0324   1.0000   1.0000
  -1.000   0.0760   0.01843   0.00810  -0.0315   1.0000   1.0000
  -0.750   0.0973   0.01872   0.00818  -0.0308   1.0000   1.0000
  -0.500   0.1293   0.01903   0.00830  -0.0322   0.9953   1.0000
  -0.250   0.1688   0.01935   0.00842  -0.0351   0.9866   1.0000
   0.000   0.2079   0.01963   0.00858  -0.0379   0.9772   1.0000
   0.250   0.2460   0.01990   0.00877  -0.0405   0.9670   1.0000
   0.500   0.2834   0.02014   0.00896  -0.0429   0.9561   1.0000
   0.750   0.3209   0.02038   0.00918  -0.0453   0.9447   1.0000
   1.000   0.3602   0.02058   0.00942  -0.0479   0.9328   1.0000
   1.250   0.4020   0.02069   0.00958  -0.0508   0.9193   1.0000
   1.500   0.4455   0.02070   0.00971  -0.0538   0.9040   1.0000
   1.750   0.4878   0.02060   0.00973  -0.0562   0.8861   1.0000
   2.000   0.5292   0.02040   0.00966  -0.0581   0.8664   1.0000
   2.250   0.5621   0.02025   0.00967  -0.0582   0.8415   1.0000
   2.500   0.5937   0.02000   0.00955  -0.0578   0.8123   1.0000
   2.750   0.6220   0.01981   0.00947  -0.0567   0.7797   1.0000
   3.000   0.6498   0.01973   0.00956  -0.0557   0.7484   1.0000
   3.250   0.6770   0.01973   0.00969  -0.0547   0.7160   1.0000
   3.500   0.7027   0.01978   0.00985  -0.0534   0.6780   1.0000
   3.750   0.7265   0.01990   0.01005  -0.0518   0.6285   1.0000
   4.000   0.7511   0.02006   0.01001  -0.0497   0.5634   1.0000
   4.250   0.7723   0.02073   0.01031  -0.0476   0.4966   1.0000
   4.500   0.7910   0.02149   0.01101  -0.0457   0.4209   1.0000
   4.750   0.8089   0.02240   0.01165  -0.0438   0.3456   1.0000
   5.000   0.8280   0.02346   0.01255  -0.0424   0.3007   1.0000
   5.250   0.8463   0.02464   0.01351  -0.0411   0.2552   1.0000
   5.500   0.8633   0.02588   0.01446  -0.0399   0.2064   1.0000
   5.750   0.8828   0.02699   0.01562  -0.0388   0.1752   1.0000
   6.000   0.9020   0.02806   0.01669  -0.0378   0.1124   1.0000
   6.250   0.9183   0.02987   0.01810  -0.0364   0.0677   1.0000
   6.500   0.9356   0.03170   0.01999  -0.0347   0.0533   1.0000
   6.750   0.9525   0.03342   0.02184  -0.0332   0.0457   1.0000
   7.000   0.9700   0.03517   0.02378  -0.0317   0.0404   1.0000
   7.250   0.9859   0.03705   0.02578  -0.0301   0.0373   1.0000
   7.500   1.0018   0.03928   0.02817  -0.0285   0.0356   1.0000
   7.750   1.0205   0.04171   0.03096  -0.0270   0.0344   1.0000
   8.000   1.0379   0.04441   0.03404  -0.0255   0.0329   1.0000
   8.250   1.0518   0.04720   0.03719  -0.0240   0.0312   1.0000
   8.500   1.0621   0.05001   0.04030  -0.0223   0.0298   1.0000
   8.750   1.0690   0.05306   0.04361  -0.0206   0.0287   1.0000
   9.000   1.0725   0.05662   0.04746  -0.0186   0.0282   1.0000
   9.250   1.0715   0.06041   0.05161  -0.0165   0.0280   1.0000
   9.500   1.0652   0.06417   0.05569  -0.0142   0.0279   1.0000
   9.750   1.0530   0.06780   0.05962  -0.0116   0.0279   1.0000
  10.000   1.0384   0.07173   0.06381  -0.0098   0.0280   1.0000
  10.250   1.0211   0.07612   0.06851  -0.0093   0.0281   1.0000
  10.500   1.0005   0.08140   0.07406  -0.0103   0.0283   1.0000
  10.750   0.9756   0.08836   0.08128  -0.0138   0.0287   1.0000
  11.000   0.9460   0.09823   0.09136  -0.0205   0.0294   1.0000
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