Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 100,000
Max Cl/Cd: 49.2 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1138-il-100000-n5.txt
Download as CSV file: xf-dga1138-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4887   0.09069   0.08578  -0.0200   1.0000   0.0310
  -8.750  -0.4915   0.08684   0.08200  -0.0219   1.0000   0.0312
  -8.500  -0.4914   0.08249   0.07770  -0.0248   1.0000   0.0312
  -8.250  -0.4895   0.07782   0.07305  -0.0280   1.0000   0.0310
  -8.000  -0.4862   0.07290   0.06813  -0.0312   1.0000   0.0308
  -7.750  -0.4814   0.06773   0.06292  -0.0342   1.0000   0.0308
  -7.500  -0.4748   0.06225   0.05737  -0.0371   1.0000   0.0309
  -7.250  -0.4660   0.05641   0.05138  -0.0396   1.0000   0.0315
  -7.000  -0.4554   0.04901   0.04367  -0.0423   1.0000   0.0331
  -6.750  -0.4446   0.04072   0.03457  -0.0440   1.0000   0.0348
  -6.500  -0.4320   0.03616   0.02952  -0.0436   1.0000   0.0362
  -6.250  -0.4157   0.03432   0.02764  -0.0425   1.0000   0.0384
  -6.000  -0.3982   0.03196   0.02486  -0.0416   1.0000   0.0425
  -5.750  -0.3791   0.02915   0.02130  -0.0404   1.0000   0.0450
  -5.500  -0.3602   0.02671   0.01845  -0.0394   1.0000   0.0481
  -5.250  -0.3401   0.02531   0.01690  -0.0384   1.0000   0.0517
  -5.000  -0.3182   0.02376   0.01496  -0.0374   1.0000   0.0534
  -4.750  -0.2956   0.02251   0.01335  -0.0364   1.0000   0.0548
  -4.500  -0.2729   0.02173   0.01224  -0.0355   1.0000   0.0575
  -4.250  -0.2497   0.02070   0.01101  -0.0347   1.0000   0.0593
  -4.000  -0.2255   0.01986   0.01004  -0.0341   0.9998   0.0597
  -3.750  -0.1909   0.01902   0.00906  -0.0356   0.9962   0.0602
  -3.500  -0.1571   0.01832   0.00828  -0.0370   0.9925   0.0610
  -3.250  -0.1233   0.01774   0.00763  -0.0384   0.9884   0.0623
  -3.000  -0.0889   0.01727   0.00706  -0.0399   0.9839   0.0641
  -2.750  -0.0544   0.01686   0.00658  -0.0413   0.9788   0.0668
  -2.500  -0.0204   0.01652   0.00617  -0.0427   0.9739   0.0705
  -2.250   0.0129   0.01615   0.00588  -0.0440   0.9685   0.0782
  -2.000   0.0481   0.01576   0.00575  -0.0457   0.9637   0.1234
  -1.750   0.0812   0.01550   0.00571  -0.0470   0.9570   0.1913
  -1.500   0.1185   0.01531   0.00561  -0.0491   0.9525   0.2354
  -1.250   0.1507   0.01515   0.00551  -0.0501   0.9448   0.2660
  -1.000   0.1899   0.01480   0.00535  -0.0525   0.9391   0.3204
  -0.750   0.2439   0.01302   0.00539  -0.0577   0.9353   1.0000
  -0.500   0.2809   0.01294   0.00520  -0.0594   0.9258   1.0000
  -0.250   0.3152   0.01289   0.00506  -0.0606   0.9147   1.0000
   0.250   0.3833   0.01278   0.00484  -0.0627   0.8922   1.0000
   0.500   0.4148   0.01276   0.00479  -0.0632   0.8792   1.0000
   0.750   0.4439   0.01276   0.00478  -0.0631   0.8645   1.0000
   1.000   0.4717   0.01278   0.00481  -0.0629   0.8490   1.0000
   1.250   0.4988   0.01280   0.00485  -0.0624   0.8310   1.0000
   1.500   0.5257   0.01278   0.00483  -0.0617   0.8080   1.0000
   1.750   0.5520   0.01277   0.00480  -0.0608   0.7802   1.0000
   2.000   0.5778   0.01278   0.00476  -0.0598   0.7435   1.0000
   2.250   0.6032   0.01286   0.00475  -0.0587   0.7014   1.0000
   2.500   0.6279   0.01302   0.00483  -0.0577   0.6531   1.0000
   2.750   0.6515   0.01329   0.00488  -0.0563   0.5871   1.0000
   3.250   0.6971   0.01424   0.00536  -0.0539   0.4997   1.0000
   3.500   0.7206   0.01466   0.00576  -0.0530   0.4607   1.0000
   3.750   0.7434   0.01511   0.00617  -0.0520   0.3965   1.0000
   4.000   0.7627   0.01594   0.00655  -0.0506   0.3079   1.0000
   4.250   0.7818   0.01698   0.00715  -0.0494   0.2355   1.0000
   4.500   0.8023   0.01788   0.00778  -0.0484   0.1930   1.0000
   4.750   0.8241   0.01860   0.00842  -0.0476   0.1669   1.0000
   5.000   0.8472   0.01918   0.00908  -0.0469   0.1403   1.0000
   5.250   0.8693   0.01990   0.00960  -0.0462   0.0874   1.0000
   5.500   0.8865   0.02135   0.01062  -0.0447   0.0354   1.0000
   5.750   0.9058   0.02261   0.01186  -0.0433   0.0283   1.0000
   6.000   0.9263   0.02368   0.01311  -0.0420   0.0261   1.0000
   6.250   0.9460   0.02484   0.01448  -0.0406   0.0242   1.0000
   6.500   0.9645   0.02614   0.01601  -0.0392   0.0218   1.0000
   6.750   0.9810   0.02768   0.01773  -0.0376   0.0200   1.0000
   7.000   0.9964   0.02947   0.01969  -0.0358   0.0192   1.0000
   7.250   1.0116   0.03165   0.02204  -0.0340   0.0185   1.0000
   7.500   1.0280   0.03423   0.02479  -0.0324   0.0180   1.0000
   7.750   1.0459   0.03634   0.02717  -0.0310   0.0178   1.0000
   8.000   1.0624   0.03841   0.02957  -0.0295   0.0172   1.0000
   8.250   1.0766   0.04062   0.03215  -0.0277   0.0165   1.0000
   8.500   1.0877   0.04314   0.03506  -0.0258   0.0158   1.0000
   8.750   1.0948   0.04607   0.03839  -0.0235   0.0155   1.0000
   9.000   1.0973   0.04928   0.04201  -0.0209   0.0154   1.0000
   9.250   1.0947   0.05263   0.04574  -0.0181   0.0154   1.0000
   9.500   1.0865   0.05596   0.04950  -0.0150   0.0154   1.0000
   9.750   1.0728   0.05927   0.05310  -0.0117   0.0154   1.0000
  10.000   1.0568   0.06300   0.05710  -0.0095   0.0154   1.0000
  10.250   1.0392   0.06727   0.06161  -0.0087   0.0155   1.0000
  10.500   1.0202   0.07227   0.06684  -0.0094   0.0156   1.0000
  10.750   1.0002   0.07824   0.07293  -0.0119   0.0157   1.0000
  11.000   0.9794   0.08554   0.08041  -0.0164   0.0158   1.0000
  11.250   0.9581   0.09455   0.08956  -0.0227   0.0160   1.0000
<< Back to D.G.A. 1138 (dga1138-il)

Polar data table (+)

Polar graphs


<< Back to D.G.A. 1138 (dga1138-il)