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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 1,000,000
Max Cl/Cd: 57.61 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1182-il-1000000.txt
Download as CSV file: xf-dga1182-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: D.G.A. 1182                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6886   0.08764   0.08416   0.0113   0.1499   0.0069
  -8.250  -0.6964   0.08073   0.07728   0.0031   0.1498   0.0069
  -8.000  -0.7000   0.07402   0.07049  -0.0028   0.1497   0.0069
  -7.750  -0.6991   0.06894   0.06530  -0.0056   0.1498   0.0069
  -7.500  -0.6946   0.06429   0.06054  -0.0073   0.1499   0.0070
  -7.250  -0.6869   0.05991   0.05602  -0.0084   0.1501   0.0071
  -7.000  -0.6764   0.05570   0.05167  -0.0090   0.1503   0.0073
  -6.750  -0.6634   0.05162   0.04741  -0.0092   0.1505   0.0076
  -6.500  -0.6479   0.04761   0.04321  -0.0091   0.1508   0.0079
  -6.250  -0.6297   0.04356   0.03896  -0.0087   0.1511   0.0085
  -6.000  -0.6038   0.04058   0.03575  -0.0076   0.1515   0.0093
  -5.750  -0.5827   0.03757   0.03250  -0.0068   0.1520   0.0095
  -5.500  -0.5626   0.03440   0.02904  -0.0059   0.1524   0.0095
  -5.250  -0.5418   0.03136   0.02570  -0.0050   0.1529   0.0096
  -5.000  -0.5201   0.02844   0.02244  -0.0041   0.1534   0.0096
  -4.750  -0.5014   0.02240   0.01579  -0.0025   0.1536   0.0100
  -4.500  -0.4780   0.02028   0.01354  -0.0023   0.1542   0.0110
  -4.250  -0.4522   0.01977   0.01298  -0.0023   0.1532   0.0125
  -3.500  -0.3716   0.01717   0.00992  -0.0012   0.1471   0.0147
  -3.250  -0.3477   0.01381   0.00629   0.0004   0.1467   0.0110
  -3.000  -0.3218   0.01298   0.00537   0.0008   0.1461   0.0112
  -2.750  -0.2951   0.01253   0.00487   0.0011   0.1456   0.0122
  -2.500  -0.2681   0.01221   0.00449   0.0012   0.1447   0.0135
  -2.250  -0.2409   0.01196   0.00417   0.0013   0.1439   0.0144
  -2.000  -0.2133   0.01187   0.00402   0.0013   0.1428   0.0152
  -1.750  -0.1863   0.01146   0.00346   0.0015   0.1417   0.0179
  -1.500  -0.1590   0.01147   0.00339   0.0015   0.1401   0.0211
  -1.250  -0.1315   0.01154   0.00339   0.0015   0.1374   0.0241
  -1.000  -0.1047   0.01085   0.00319   0.0015   0.1357   0.1828
  -0.750  -0.0769   0.01080   0.00315   0.0015   0.1344   0.1989
  -0.500  -0.0494   0.01074   0.00310   0.0014   0.1332   0.2133
  -0.250  -0.0228   0.01044   0.00310   0.0014   0.1319   0.3365
   0.000   0.0054   0.01065   0.00332   0.0013   0.1307   0.3520
   0.250   0.0335   0.01090   0.00352   0.0012   0.1295   0.3580
   0.500   0.0612   0.01121   0.00378   0.0011   0.1268   0.3611
   0.750   0.0901   0.01089   0.00352   0.0010   0.1239   0.3634
   1.000   0.1183   0.01091   0.00355   0.0009   0.1221   0.3652
   1.250   0.1465   0.01093   0.00357   0.0008   0.1203   0.3668
   1.500   0.1748   0.01091   0.00356   0.0007   0.1186   0.3682
   1.750   0.2037   0.01075   0.00341   0.0006   0.1166   0.3696
   2.000   0.2324   0.01069   0.00334   0.0005   0.1150   0.3711
   2.250   0.2600   0.01079   0.00348   0.0004   0.1098   0.3722
   2.500   0.2877   0.01088   0.00357   0.0004   0.0922   0.3729
   2.750   0.3185   0.01024   0.00280   0.0002   0.0842   0.3734
   3.000   0.3463   0.01026   0.00279   0.0001   0.0770   0.3742
   3.250   0.3740   0.01032   0.00285   0.0001   0.0692   0.3753
   3.500   0.4013   0.01047   0.00304   0.0000   0.0604   0.3762
   3.750   0.4282   0.01077   0.00324   0.0000   0.0422   0.3770
   4.000   0.4555   0.01099   0.00345   0.0000   0.0384   0.3778
   4.250   0.4830   0.01119   0.00368   0.0000   0.0362   0.3785
   4.500   0.5104   0.01140   0.00398   0.0000   0.0352   0.3792
   4.750   0.5376   0.01166   0.00431   0.0000   0.0345   0.3799
   5.000   0.5646   0.01200   0.00475   0.0001   0.0339   0.3809
   5.250   0.5911   0.01242   0.00525   0.0002   0.0329   0.3819
   5.500   0.6183   0.01255   0.00543   0.0002   0.0323   0.3828
   5.750   0.6452   0.01277   0.00570   0.0002   0.0314   0.3837
   6.000   0.6720   0.01299   0.00597   0.0002   0.0298   0.3844
   6.250   0.6986   0.01326   0.00628   0.0002   0.0281   0.3850
   6.500   0.7249   0.01356   0.00661   0.0003   0.0262   0.3855
   6.750   0.7489   0.01458   0.00778   0.0006   0.0226   0.3860
   7.000   0.7771   0.01431   0.00748   0.0004   0.0218   0.3864
   7.250   0.8043   0.01430   0.00748   0.0003   0.0197   0.3869
   7.500   0.8308   0.01451   0.00760   0.0002   0.0160   0.3873
   7.750   0.8566   0.01487   0.00800   0.0003   0.0136   0.3891
   8.000   0.8820   0.01540   0.00849   0.0005   0.0111   0.3908
   8.250   0.9065   0.01625   0.00952   0.0008   0.0096   0.3920
   8.500   0.9319   0.01677   0.01012   0.0010   0.0088   0.3927
   8.750   0.9569   0.01739   0.01081   0.0011   0.0079   0.3935
   9.000   0.9810   0.01826   0.01178   0.0014   0.0071   0.3943
   9.250   1.0007   0.02031   0.01418   0.0022   0.0063   0.3950
   9.500   1.0224   0.02177   0.01589   0.0028   0.0061   0.3957
   9.750   1.0452   0.02293   0.01722   0.0031   0.0059   0.3966
  10.000   1.0667   0.02442   0.01892   0.0036   0.0057   0.3974
  10.250   1.0870   0.02618   0.02094   0.0041   0.0055   0.3982
  10.500   1.1055   0.02826   0.02328   0.0047   0.0052   0.3990
  10.750   1.1215   0.03077   0.02608   0.0055   0.0050   0.3997
  11.000   1.1351   0.03383   0.02944   0.0063   0.0048   0.4003
  11.250   1.1442   0.03744   0.03336   0.0072   0.0046   0.4009
  11.500   1.1406   0.04317   0.03953   0.0084   0.0045   0.4017
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