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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 100,000
Max Cl/Cd: 24.16 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-dga1182-il-100000.txt
Download as CSV file: xf-dga1182-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6737   0.11020   0.10592   0.0145   1.0000   0.0753
  -9.000  -0.6840   0.10546   0.10125   0.0068   1.0000   0.0760
  -8.750  -0.6958   0.10040   0.09619  -0.0005   1.0000   0.0762
  -8.500  -0.6659   0.09705   0.09288   0.0116   1.0000   0.0823
  -8.250  -0.6681   0.09258   0.08846   0.0079   1.0000   0.0857
  -8.000  -0.6759   0.08718   0.08308   0.0009   1.0000   0.0878
  -7.750  -0.6899   0.08248   0.07810  -0.0077   1.0000   0.0896
  -7.500  -0.6740   0.07723   0.07308  -0.0044   1.0000   0.0945
  -7.250  -0.6717   0.07313   0.06884  -0.0075   1.0000   0.1018
  -7.000  -0.6673   0.06827   0.06392  -0.0089   1.0000   0.1077
  -6.750  -0.6678   0.06748   0.06242  -0.0118   1.0000   0.1183
  -6.500  -0.6554   0.06335   0.05824  -0.0118   1.0000   0.1321
  -6.250  -0.6384   0.05710   0.05238  -0.0109   1.0000   0.1434
  -6.000  -0.6297   0.05409   0.04894  -0.0118   1.0000   0.1608
  -5.750  -0.6147   0.04913   0.04407  -0.0113   1.0000   0.1764
  -5.000  -0.5427   0.02321   0.01862  -0.0099   1.0000   0.2570
  -4.750  -0.5246   0.02054   0.01595  -0.0086   1.0000   0.2728
  -4.500  -0.4817   0.03135   0.02376  -0.0088   1.0000   0.0871
  -4.250  -0.4520   0.02729   0.01909  -0.0072   1.0000   0.0666
  -4.000  -0.4236   0.02518   0.01658  -0.0060   1.0000   0.0612
  -3.750  -0.3968   0.02343   0.01455  -0.0050   1.0000   0.0623
  -3.500  -0.3701   0.02133   0.01232  -0.0041   1.0000   0.0618
  -3.250  -0.3440   0.01955   0.01050  -0.0031   1.0000   0.0615
  -3.000  -0.3194   0.01819   0.00918  -0.0019   1.0000   0.0622
  -2.750  -0.2971   0.01696   0.00797  -0.0006   1.0000   0.0645
  -2.500  -0.2736   0.01613   0.00713   0.0003   1.0000   0.0743
  -2.250  -0.2488   0.01535   0.00631   0.0011   1.0000   0.0874
  -2.000  -0.2159   0.01436   0.00602   0.0002   0.9828   0.3836
  -1.750  -0.1891   0.01343   0.00538   0.0003   0.9640   0.4817
  -1.500  -0.1624   0.01282   0.00516   0.0006   0.9444   0.5455
  -1.250  -0.1309   0.01267   0.00496   0.0001   0.9127   0.5695
  -1.000  -0.0982   0.01257   0.00469  -0.0007   0.8746   0.5723
  -0.750  -0.0671   0.01251   0.00448  -0.0011   0.8400   0.5753
  -0.500  -0.0384   0.01247   0.00430  -0.0010   0.8081   0.5787
  -0.250  -0.0110   0.01247   0.00415  -0.0007   0.7712   0.5819
   0.000   0.0152   0.01252   0.00400   0.0000   0.7142   0.5847
   0.250   0.0395   0.01270   0.00384   0.0011   0.6328   0.5886
   0.500   0.0647   0.01288   0.00374   0.0018   0.5686   0.5951
   0.750   0.0908   0.01299   0.00371   0.0022   0.5190   0.6030
   1.000   0.1176   0.01302   0.00371   0.0024   0.4846   0.6130
   1.500   0.1690   0.01298   0.00377   0.0032   0.4134   0.6582
   1.750   0.1904   0.01267   0.00403   0.0055   0.3930   0.8463
   2.000   0.2212   0.01283   0.00418   0.0051   0.3723   0.9095
   2.250   0.2643   0.01310   0.00443   0.0019   0.3463   0.9674
   2.500   0.2994   0.01343   0.00468   0.0002   0.3218   1.0000
   2.750   0.3260   0.01362   0.00491   0.0006   0.2916   1.0000
   3.000   0.3498   0.01448   0.00514   0.0011   0.2022   1.0000
   3.250   0.3692   0.01655   0.00674   0.0020   0.1820   1.0000
   3.500   0.3935   0.01888   0.00874   0.0025   0.1669   1.0000
   3.750   0.4190   0.02136   0.01116   0.0027   0.1446   1.0000
   4.000   0.4444   0.02326   0.01315   0.0030   0.1283   1.0000
   4.250   0.4705   0.02417   0.01436   0.0036   0.1180   1.0000
   4.500   0.4967   0.02548   0.01590   0.0041   0.1121   1.0000
   4.750   0.5230   0.02683   0.01757   0.0047   0.1083   1.0000
   5.000   0.5489   0.02854   0.01952   0.0052   0.1064   1.0000
   5.250   0.5739   0.03026   0.02146   0.0056   0.1027   1.0000
   5.500   0.5989   0.03185   0.02350   0.0063   0.0991   1.0000
   5.750   0.6230   0.03435   0.02643   0.0070   0.0992   1.0000
   6.000   0.6458   0.03752   0.03005   0.0077   0.1013   1.0000
   6.250   0.6673   0.04009   0.03313   0.0084   0.0982   1.0000
   6.500   0.6898   0.04641   0.04042   0.0093   0.1353   1.0000
   6.750   0.7076   0.05155   0.04574   0.0093   0.1376   1.0000
   7.000   0.7184   0.05497   0.04981   0.0090   0.1339   1.0000
   7.250   0.7308   0.05954   0.05454   0.0089   0.1295   1.0000
   7.500   0.7517   0.06795   0.06255   0.0090   0.1274   1.0000
   7.750   0.7400   0.07009   0.06555   0.0061   0.1255   1.0000
   8.000   0.7363   0.07521   0.07090   0.0025   0.1206   1.0000
   8.250   0.7458   0.07952   0.07521   0.0031   0.1170   1.0000
   8.500   0.7566   0.08555   0.08116   0.0038   0.1148   1.0000
   8.750   0.7367   0.09084   0.08662  -0.0033   0.1141   1.0000
   9.000   0.7187   0.09692   0.09264  -0.0126   0.1125   1.0000
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