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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 100,000
Max Cl/Cd: 27.84 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1182-il-100000-n5.txt
Download as CSV file: xf-dga1182-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6253   0.10342   0.09731   0.0011   0.3092   0.0402
  -8.500  -0.6267   0.09823   0.09214  -0.0054   0.3086   0.0403
  -8.250  -0.6298   0.09379   0.08762  -0.0102   0.3079   0.0404
  -8.000  -0.6297   0.08976   0.08345  -0.0135   0.3068   0.0406
  -7.750  -0.6209   0.08404   0.07795  -0.0087   0.3018   0.0431
  -7.500  -0.6157   0.07990   0.07378  -0.0105   0.2991   0.0446
  -7.250  -0.6103   0.07540   0.06919  -0.0133   0.2970   0.0461
  -7.000  -0.6035   0.07094   0.06459  -0.0159   0.2952   0.0480
  -6.750  -0.5419   0.05266   0.04647  -0.0224   0.2952   0.0559
  -6.500  -0.5335   0.04831   0.04205  -0.0225   0.2932   0.0580
  -6.250  -0.5245   0.04387   0.03743  -0.0230   0.2916   0.0605
  -6.000  -0.5161   0.03916   0.03235  -0.0239   0.2906   0.0697
  -5.750  -0.5297   0.04768   0.03983  -0.0210   0.2869   0.0276
  -5.500  -0.5104   0.04367   0.03543  -0.0209   0.2849   0.0249
  -5.250  -0.4877   0.03944   0.03067  -0.0202   0.2828   0.0222
  -5.000  -0.4614   0.03630   0.02683  -0.0190   0.2806   0.0201
  -4.750  -0.4360   0.03432   0.02442  -0.0183   0.2782   0.0196
  -4.500  -0.4119   0.03141   0.02108  -0.0177   0.2761   0.0197
  -4.250  -0.3883   0.02837   0.01772  -0.0174   0.2743   0.0212
  -4.000  -0.3626   0.02641   0.01552  -0.0170   0.2724   0.0227
  -3.750  -0.3356   0.02453   0.01335  -0.0163   0.2703   0.0229
  -3.500  -0.3090   0.02289   0.01148  -0.0156   0.2684   0.0234
  -3.250  -0.2830   0.02148   0.00995  -0.0149   0.2664   0.0243
  -3.000  -0.2578   0.02040   0.00880  -0.0141   0.2645   0.0269
  -2.750  -0.2324   0.01961   0.00785  -0.0134   0.2626   0.0300
  -2.500  -0.2072   0.01868   0.00674  -0.0129   0.2608   0.0325
  -2.250  -0.1804   0.01809   0.00598  -0.0126   0.2601   0.0387
  -1.750  -0.1269   0.01649   0.00519  -0.0124   0.2590   0.3585
  -1.500  -0.1005   0.01675   0.00519  -0.0121   0.2590   0.4224
  -1.250  -0.0737   0.01653   0.00486  -0.0119   0.2590   0.4371
  -1.000  -0.0457   0.01635   0.00465  -0.0118   0.2115   0.4400
  -0.750  -0.0188   0.01638   0.00442  -0.0118   0.2042   0.4426
  -0.500   0.0085   0.01634   0.00422  -0.0117   0.2029   0.4446
  -0.250   0.0359   0.01631   0.00408  -0.0116   0.2019   0.4457
   0.000   0.0632   0.01631   0.00393  -0.0115   0.1980   0.4474
   0.250   0.0904   0.01636   0.00385  -0.0115   0.1934   0.4490
   0.500   0.1174   0.01652   0.00392  -0.0114   0.1892   0.4501
   0.750   0.1441   0.01676   0.00408  -0.0113   0.1839   0.4508
   1.000   0.1708   0.01698   0.00430  -0.0112   0.1791   0.4514
   1.250   0.1973   0.01723   0.00454  -0.0110   0.1759   0.4526
   1.500   0.2237   0.01744   0.00477  -0.0109   0.1742   0.4542
   1.750   0.2499   0.01764   0.00502  -0.0107   0.1725   0.4561
   2.000   0.2764   0.01782   0.00528  -0.0105   0.1706   0.4576
   2.250   0.3023   0.01816   0.00566  -0.0103   0.1674   0.4589
   2.500   0.3271   0.01880   0.00626  -0.0100   0.1636   0.4603
   2.750   0.3527   0.01929   0.00682  -0.0097   0.1589   0.4622
   3.000   0.3777   0.02023   0.00768  -0.0095   0.1491   0.4645
   3.250   0.4035   0.02087   0.00839  -0.0093   0.1368   0.4671
   3.500   0.4298   0.02112   0.00885  -0.0092   0.1265   0.4697
   3.750   0.4564   0.02113   0.00919  -0.0090   0.1162   0.4723
   4.000   0.4835   0.02118   0.00952  -0.0088   0.1048   0.4744
   4.250   0.5102   0.02135   0.00987  -0.0086   0.0951   0.4761
   4.500   0.5370   0.02137   0.01008  -0.0085   0.0891   0.4780
   4.750   0.5637   0.02148   0.01035  -0.0084   0.0838   0.4803
   5.250   0.6151   0.02277   0.01186  -0.0078   0.0761   0.4879
   5.500   0.6407   0.02395   0.01322  -0.0074   0.0732   0.4947
   6.000   0.6830   0.02453   0.01512  -0.0049   0.0662   0.8473
   6.250   0.7100   0.02618   0.01724  -0.0046   0.0628   0.9017
   6.500   0.7408   0.02820   0.01974  -0.0054   0.0589   1.0000
   6.750   0.7641   0.02911   0.02082  -0.0050   0.0549   1.0000
   7.000   0.7872   0.03010   0.02217  -0.0045   0.0459   1.0000
   7.250   0.8093   0.03088   0.02323  -0.0041   0.0390   1.0000
   7.500   0.8310   0.03157   0.02408  -0.0036   0.0324   1.0000
   7.750   0.8470   0.03656   0.02986  -0.0023   0.0271   1.0000
   8.000   0.8603   0.04105   0.03495  -0.0012   0.0232   1.0000
   8.250   0.8740   0.04387   0.03810  -0.0004   0.0213   1.0000
   8.750   0.8821   0.05308   0.04806   0.0013   0.0194   1.0000
   9.000   0.8743   0.05978   0.05519   0.0016   0.0191   1.0000
   9.250   0.8627   0.06597   0.06166   0.0012   0.0190   1.0000
   9.500   0.8482   0.07150   0.06736   0.0002   0.0190   1.0000
   9.750   0.8314   0.07675   0.07270  -0.0020   0.0192   1.0000
  10.000   0.8168   0.08325   0.07925  -0.0074   0.0195   1.0000
  10.250   0.8058   0.09133   0.08730  -0.0142   0.0198   1.0000
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