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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 50,000
Max Cl/Cd: 38.1 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1138-il-50000.txt
Download as CSV file: xf-dga1138-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4972   0.10446   0.09766  -0.0096   1.0000   0.2183
  -8.500  -0.4756   0.09864   0.09180  -0.0077   1.0000   0.2271
  -8.250  -0.4981   0.09828   0.09161  -0.0121   1.0000   0.2331
  -8.000  -0.4755   0.09237   0.08567  -0.0083   1.0000   0.2416
  -7.750  -0.4813   0.08965   0.08305  -0.0107   1.0000   0.2495
  -7.500  -0.4802   0.08688   0.08032  -0.0119   1.0000   0.2611
  -7.250  -0.4686   0.08255   0.07602  -0.0098   1.0000   0.2714
  -7.000  -0.4656   0.07937   0.07289  -0.0097   1.0000   0.2865
  -6.750  -0.4695   0.07714   0.07070  -0.0121   1.0000   0.3048
  -6.500  -0.4595   0.07298   0.06661  -0.0086   1.0000   0.3221
  -6.250  -0.4523   0.06970   0.06336  -0.0066   1.0000   0.3410
  -6.000  -0.4495   0.06671   0.06040  -0.0053   1.0000   0.3656
  -5.750  -0.4450   0.06376   0.05750  -0.0024   1.0000   0.3946
  -5.500  -0.4393   0.06085   0.05466   0.0021   1.0000   0.4282
  -4.750  -0.3164   0.04161   0.03308  -0.0360   1.0000   0.1733
  -4.500  -0.2901   0.03753   0.02830  -0.0368   1.0000   0.1599
  -4.250  -0.2674   0.03471   0.02518  -0.0363   1.0000   0.1570
  -4.000  -0.2429   0.03235   0.02229  -0.0360   1.0000   0.1591
  -3.750  -0.2188   0.03031   0.01989  -0.0354   1.0000   0.1625
  -3.500  -0.1937   0.02844   0.01767  -0.0349   1.0000   0.1641
  -3.250  -0.1682   0.02687   0.01582  -0.0343   1.0000   0.1677
  -3.000  -0.1412   0.02549   0.01404  -0.0338   1.0000   0.1738
  -2.750  -0.1155   0.02437   0.01284  -0.0332   1.0000   0.1843
  -2.500  -0.0896   0.02353   0.01186  -0.0326   1.0000   0.2052
  -2.250  -0.0598   0.02245   0.01080  -0.0325   1.0000   0.2393
  -2.000  -0.0275   0.02031   0.00928  -0.0330   1.0000   0.3684
  -1.750   0.0095   0.01770   0.00860  -0.0339   1.0000   1.0000
  -1.500   0.0324   0.01792   0.00835  -0.0331   1.0000   1.0000
  -1.250   0.0542   0.01816   0.00822  -0.0322   1.0000   1.0000
  -1.000   0.0757   0.01842   0.00822  -0.0314   1.0000   1.0000
  -0.750   0.0970   0.01871   0.00829  -0.0306   1.0000   1.0000
  -0.500   0.1181   0.01903   0.00843  -0.0299   1.0000   1.0000
  -0.250   0.1390   0.01939   0.00863  -0.0292   1.0000   1.0000
   0.000   0.1598   0.01978   0.00890  -0.0285   1.0000   1.0000
   0.250   0.1803   0.02021   0.00924  -0.0280   1.0000   1.0000
   0.500   0.2004   0.02069   0.00966  -0.0274   1.0000   1.0000
   0.750   0.2202   0.02123   0.01016  -0.0270   1.0000   1.0000
   1.000   0.2394   0.02184   0.01075  -0.0266   1.0000   1.0000
   1.250   0.2578   0.02255   0.01146  -0.0263   1.0000   1.0000
   1.500   0.2754   0.02337   0.01230  -0.0261   1.0000   1.0000
   1.750   0.2918   0.02433   0.01330  -0.0260   1.0000   1.0000
   2.000   0.3073   0.02542   0.01444  -0.0261   1.0000   1.0000
   2.250   0.3648   0.02669   0.01583  -0.0339   0.9827   1.0000
   2.500   0.4378   0.02744   0.01678  -0.0436   0.9511   1.0000
   2.750   0.5136   0.02752   0.01717  -0.0523   0.9183   1.0000
   3.000   0.5853   0.02704   0.01704  -0.0593   0.8877   1.0000
   3.250   0.6399   0.02664   0.01702  -0.0630   0.8604   1.0000
   3.500   0.6920   0.02580   0.01656  -0.0652   0.8307   1.0000
   3.750   0.7336   0.02466   0.01580  -0.0644   0.7926   1.0000
   4.000   0.7745   0.02284   0.01427  -0.0618   0.7438   1.0000
   4.250   0.7986   0.02169   0.01317  -0.0566   0.6675   1.0000
   4.500   0.8200   0.02152   0.01240  -0.0514   0.5535   1.0000
   4.750   0.8410   0.02316   0.01338  -0.0487   0.4573   1.0000
   5.000   0.8622   0.02433   0.01440  -0.0469   0.4020   1.0000
   5.250   0.8831   0.02535   0.01523  -0.0451   0.3591   1.0000
   5.500   0.8995   0.02637   0.01601  -0.0430   0.3112   1.0000
   5.750   0.9140   0.02762   0.01703  -0.0409   0.2609   1.0000
   6.000   0.9251   0.02952   0.01865  -0.0383   0.1977   1.0000
   6.250   0.9420   0.03311   0.02185  -0.0361   0.1341   1.0000
   6.500   0.9666   0.03585   0.02464  -0.0348   0.1141   1.0000
   6.750   0.9891   0.03824   0.02717  -0.0336   0.1020   1.0000
   7.000   1.0106   0.04069   0.02981  -0.0325   0.0932   1.0000
   7.250   1.0309   0.04447   0.03401  -0.0311   0.0899   1.0000
   7.500   1.0454   0.04864   0.03882  -0.0291   0.0885   1.0000
   7.750   1.0551   0.05307   0.04382  -0.0269   0.0881   1.0000
   8.000   1.0604   0.05769   0.04895  -0.0247   0.0884   1.0000
   8.250   1.0610   0.06243   0.05420  -0.0225   0.0887   1.0000
   8.500   1.0574   0.06723   0.05939  -0.0204   0.0893   1.0000
   8.750   1.0509   0.07207   0.06453  -0.0185   0.0899   1.0000
   9.000   1.0425   0.07693   0.06962  -0.0169   0.0905   1.0000
   9.250   1.0344   0.08184   0.07468  -0.0157   0.0911   1.0000
   9.500   0.9618   0.08960   0.08280  -0.0161   0.0992   1.0000
   9.750   0.9427   0.09607   0.08930  -0.0184   0.1016   1.0000
  10.000   0.9401   0.10176   0.09500  -0.0194   0.1035   1.0000
  10.250   0.8895   0.11689   0.11004  -0.0333   0.1142   1.0000
  10.500   0.7401   0.11442   0.10781  -0.0211   0.1149   1.0000
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