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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 50,000
Max Cl/Cd: 20.55 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1182-il-50000-n5.txt
Download as CSV file: xf-dga1182-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6210   0.11190   0.10592   0.0118   1.0000   0.1176
  -8.750  -0.6289   0.10867   0.10278   0.0075   1.0000   0.1239
  -8.500  -0.6480   0.10519   0.09946  -0.0007   1.0000   0.1256
  -8.250  -0.6194   0.10018   0.09440   0.0064   1.0000   0.1323
  -8.000  -0.6353   0.09657   0.09089  -0.0013   1.0000   0.1394
  -7.500  -0.5302   0.07082   0.06538  -0.0158   1.0000   0.0755
  -7.000  -0.6038   0.07146   0.06497  -0.0194   1.0000   0.0530
  -6.750  -0.5924   0.06652   0.06012  -0.0192   1.0000   0.0509
  -6.500  -0.5817   0.06214   0.05558  -0.0199   1.0000   0.0491
  -6.250  -0.5691   0.05781   0.05102  -0.0207   1.0000   0.0471
  -6.000  -0.5541   0.05346   0.04632  -0.0211   1.0000   0.0446
  -5.750  -0.5320   0.05033   0.04228  -0.0208   1.0000   0.0406
  -5.500  -0.5149   0.04608   0.03783  -0.0206   1.0000   0.0395
  -5.250  -0.4953   0.04254   0.03398  -0.0202   1.0000   0.0385
  -5.000  -0.4739   0.03929   0.03036  -0.0196   1.0000   0.0377
  -4.750  -0.4509   0.03631   0.02696  -0.0189   1.0000   0.0371
  -4.500  -0.4264   0.03357   0.02383  -0.0180   1.0000   0.0368
  -4.250  -0.4009   0.03118   0.02106  -0.0171   1.0000   0.0375
  -4.000  -0.3747   0.02928   0.01877  -0.0161   1.0000   0.0398
  -3.750  -0.3495   0.02713   0.01644  -0.0150   1.0000   0.0417
  -3.500  -0.3250   0.02531   0.01455  -0.0138   1.0000   0.0432
  -3.250  -0.3014   0.02388   0.01301  -0.0125   1.0000   0.0453
  -3.000  -0.2779   0.02274   0.01169  -0.0114   1.0000   0.0499
  -2.750  -0.2491   0.02155   0.01036  -0.0117   0.9846   0.0583
  -2.500  -0.2176   0.02055   0.00913  -0.0123   0.9627   0.0683
  -2.250  -0.1866   0.01910   0.00820  -0.0132   0.9428   0.1565
  -2.000  -0.1626   0.01793   0.00751  -0.0126   0.9237   0.4658
  -1.750  -0.1408   0.01697   0.00710  -0.0111   0.8977   0.5551
  -1.500  -0.1087   0.01684   0.00661  -0.0118   0.8630   0.5604
  -1.250  -0.0763   0.01675   0.00621  -0.0125   0.8245   0.5670
  -1.000  -0.0458   0.01669   0.00587  -0.0128   0.7852   0.5722
  -0.750  -0.0170   0.01664   0.00557  -0.0127   0.7459   0.5765
  -0.500   0.0107   0.01660   0.00534  -0.0125   0.7063   0.5827
  -0.250   0.0373   0.01657   0.00514  -0.0120   0.6678   0.5921
   0.000   0.0631   0.01654   0.00499  -0.0114   0.6343   0.6044
   0.250   0.0883   0.01647   0.00487  -0.0107   0.6071   0.6222
   0.500   0.1123   0.01636   0.00484  -0.0096   0.5766   0.6533
   0.750   0.1393   0.01605   0.00497  -0.0083   0.5405   0.8205
   1.000   0.1694   0.01617   0.00498  -0.0086   0.5073   0.8975
   1.250   0.2069   0.01625   0.00500  -0.0106   0.4746   0.9551
   1.500   0.2378   0.01645   0.00506  -0.0115   0.4430   1.0000
   1.750   0.2616   0.01686   0.00518  -0.0109   0.3989   1.0000
   2.000   0.2849   0.01744   0.00533  -0.0103   0.3619   1.0000
   2.250   0.3092   0.01791   0.00558  -0.0099   0.3350   1.0000
   2.500   0.3345   0.01823   0.00587  -0.0096   0.3155   1.0000
   2.750   0.3605   0.01844   0.00622  -0.0093   0.2953   1.0000
   3.000   0.3854   0.01888   0.00651  -0.0089   0.2074   1.0000
   3.250   0.4082   0.01986   0.00706  -0.0085   0.1948   1.0000
   3.500   0.4305   0.02120   0.00826  -0.0080   0.1838   1.0000
   3.750   0.4540   0.02287   0.00992  -0.0076   0.1713   1.0000
   4.000   0.4803   0.02465   0.01166  -0.0072   0.1583   1.0000
   4.250   0.5067   0.02656   0.01358  -0.0070   0.1391   1.0000
   4.500   0.5322   0.02763   0.01490  -0.0066   0.1251   1.0000
   4.750   0.5585   0.02862   0.01623  -0.0062   0.1164   1.0000
   5.000   0.5848   0.02978   0.01764  -0.0057   0.1097   1.0000
   5.250   0.6110   0.03106   0.01920  -0.0053   0.1043   1.0000
   5.500   0.6369   0.03260   0.02098  -0.0049   0.1008   1.0000
   5.750   0.6626   0.03433   0.02312  -0.0043   0.0978   1.0000
   6.000   0.6874   0.03625   0.02549  -0.0038   0.0952   1.0000
   6.250   0.7103   0.03774   0.02728  -0.0033   0.0887   1.0000
   6.500   0.7326   0.03941   0.02933  -0.0028   0.0824   1.0000
   6.750   0.7541   0.04191   0.03213  -0.0023   0.0791   1.0000
   7.000   0.7724   0.04565   0.03664  -0.0012   0.0761   1.0000
   7.250   0.7892   0.04838   0.03982  -0.0005   0.0695   1.0000
   7.500   0.8019   0.05182   0.04376   0.0002   0.0632   1.0000
   7.750   0.8120   0.05555   0.04799   0.0009   0.0576   1.0000
   8.000   0.8232   0.05839   0.05111   0.0014   0.0524   1.0000
   8.250   0.8237   0.06387   0.05709   0.0016   0.0510   1.0000
   8.500   0.8208   0.06910   0.06268   0.0013   0.0498   1.0000
   8.750   0.8148   0.07421   0.06803   0.0004   0.0489   1.0000
   9.000   0.8058   0.07934   0.07332  -0.0011   0.0484   1.0000
   9.250   0.7936   0.08448   0.07854  -0.0031   0.0485   1.0000
   9.500   0.7811   0.09016   0.08413  -0.0066   0.0490   1.0000
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