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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 200,000
Max Cl/Cd: 29.27 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1182-il-200000.txt
Download as CSV file: xf-dga1182-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.5660   0.08381   0.07929   0.0007   0.3351   0.0346
  -8.250  -0.5746   0.07804   0.07353  -0.0033   0.3338   0.0347
  -8.000  -0.5863   0.07210   0.06758  -0.0079   0.3326   0.0344
  -7.750  -0.5994   0.06717   0.06258  -0.0100   0.3321   0.0344
  -7.500  -0.6061   0.06236   0.05762  -0.0120   0.3307   0.0350
  -7.250  -0.6063   0.05862   0.05359  -0.0130   0.3285   0.0359
  -7.000  -0.6013   0.05479   0.04947  -0.0131   0.3260   0.0363
  -6.500  -0.6379   0.05482   0.04867  -0.0102   0.3206   0.0373
  -6.250  -0.6253   0.05042   0.04430  -0.0105   0.3179   0.0389
  -6.000  -0.6092   0.04742   0.04118  -0.0105   0.3154   0.0414
  -5.750  -0.5896   0.04456   0.03803  -0.0102   0.3134   0.0459
  -5.500  -0.5710   0.04081   0.03381  -0.0097   0.3118   0.0520
  -5.250  -0.5510   0.03843   0.03132  -0.0096   0.3101   0.0573
  -5.000  -0.5306   0.03611   0.02875  -0.0093   0.3085   0.0696
  -4.750  -0.5088   0.03511   0.02727  -0.0088   0.3070   0.0915
  -4.500  -0.4871   0.03265   0.02473  -0.0086   0.3056   0.1062
  -4.250  -0.4648   0.03027   0.02231  -0.0085   0.3041   0.1225
  -3.750  -0.3936   0.02171   0.01223  -0.0038   0.3012   0.0398
  -3.500  -0.3645   0.02095   0.01122  -0.0030   0.3003   0.0358
  -3.250  -0.3380   0.01896   0.00912  -0.0023   0.2998   0.0350
  -3.000  -0.3115   0.01787   0.00791  -0.0016   0.2996   0.0370
  -2.750  -0.2870   0.01635   0.00637  -0.0009   0.2988   0.0387
  -2.500  -0.2615   0.01541   0.00538  -0.0003   0.2977   0.0401
  -2.250  -0.2352   0.01476   0.00462   0.0001   0.2972   0.0434
  -2.000  -0.2080   0.01436   0.00409   0.0004   0.2967   0.0506
  -1.750  -0.1812   0.01353   0.00367   0.0006   0.2960   0.1852
  -1.500  -0.1536   0.01396   0.00426   0.0008   0.2941   0.3882
  -1.250  -0.1273   0.01398   0.00428   0.0011   0.2915   0.4186
  -1.000  -0.1014   0.01364   0.00397   0.0013   0.2880   0.4454
  -0.750  -0.0740   0.01354   0.00379   0.0014   0.2853   0.4543
  -0.500  -0.0463   0.01344   0.00363   0.0014   0.2839   0.4566
  -0.250  -0.0186   0.01333   0.00349   0.0014   0.2823   0.4581
   0.000   0.0091   0.01326   0.00338   0.0014   0.2807   0.4593
   0.250   0.0369   0.01317   0.00330   0.0014   0.2791   0.4611
   0.500   0.0647   0.01310   0.00325   0.0014   0.2768   0.4628
   0.750   0.0925   0.01305   0.00320   0.0014   0.2688   0.4639
   1.000   0.1199   0.01311   0.00309   0.0013   0.2044   0.4647
   1.250   0.1469   0.01331   0.00315   0.0013   0.1971   0.4659
   1.500   0.1742   0.01347   0.00330   0.0013   0.1919   0.4671
   1.750   0.2013   0.01368   0.00353   0.0014   0.1880   0.4677
   2.000   0.2278   0.01407   0.00393   0.0014   0.1830   0.4687
   2.250   0.2539   0.01458   0.00445   0.0015   0.1774   0.4698
   2.500   0.2780   0.01582   0.00547   0.0018   0.1663   0.4711
   2.750   0.3035   0.01708   0.00661   0.0019   0.1518   0.4723
   3.000   0.3298   0.01818   0.00767   0.0018   0.1393   0.4733
   3.250   0.3565   0.01843   0.00809   0.0019   0.1288   0.4743
   3.500   0.3834   0.01835   0.00829   0.0021   0.1182   0.4756
   3.750   0.4108   0.01794   0.00813   0.0022   0.1061   0.4774
   4.000   0.4394   0.01708   0.00751   0.0023   0.0944   0.4796
   4.250   0.4686   0.01643   0.00698   0.0023   0.0855   0.4820
   4.500   0.4948   0.01702   0.00766   0.0026   0.0784   0.4842
   4.750   0.5204   0.01778   0.00852   0.0030   0.0739   0.4874
   5.000   0.5449   0.01910   0.00990   0.0034   0.0694   0.4912
   5.250   0.5708   0.02012   0.01111   0.0038   0.0672   0.4958
   5.500   0.5965   0.02163   0.01287   0.0041   0.0651   0.5019
   5.750   0.6220   0.02340   0.01500   0.0045   0.0626   0.5117
   6.000   0.6452   0.02325   0.01538   0.0050   0.0586   0.6584
   6.250   0.6618   0.02543   0.01836   0.0071   0.0559   0.8675
   6.500   0.6853   0.02802   0.02159   0.0082   0.0516   0.9002
   6.750   0.7194   0.02813   0.02186   0.0064   0.0467   0.9748
   7.000   0.7362   0.03300   0.02724   0.0071   0.0439   1.0000
   7.250   0.7506   0.03986   0.03491   0.0087   0.0406   1.0000
   7.500   0.7611   0.04601   0.04158   0.0096   0.0406   1.0000
   7.750   0.7681   0.05194   0.04788   0.0101   0.0422   1.0000
   8.000   0.7641   0.06272   0.05924   0.0098   0.0591   1.0000
   8.250   0.7745   0.06695   0.06347   0.0098   0.0577   1.0000
   8.500   0.7724   0.07609   0.07256   0.0086   0.0563   1.0000
   8.750   0.6616   0.06844   0.06565   0.0099   0.0598   1.0000
   9.000   0.6301   0.07723   0.07443   0.0015   0.0611   1.0000
   9.250   0.6219   0.08267   0.07985  -0.0009   0.0602   1.0000
   9.500   0.6271   0.08601   0.08319   0.0000   0.0584   1.0000
   9.750   0.7250   0.10358   0.10056  -0.0165   0.0544   1.0000
  10.000   0.6306   0.09624   0.09338   0.0032   0.0563   1.0000
  10.250   0.6199   0.10234   0.09946  -0.0008   0.0562   1.0000
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