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D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1138 (dga1138-il)
Reynolds number: 500,000
Max Cl/Cd: 67.37 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1138-il-500000-n5.txt
Download as CSV file: xf-dga1138-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5326   0.11282   0.11050  -0.0064   1.0000   0.0062
 -11.000  -0.5345   0.10757   0.10527  -0.0085   1.0000   0.0065
  -9.500  -0.6981   0.02988   0.02674  -0.0513   1.0000   0.0061
  -9.250  -0.6915   0.02419   0.02038  -0.0504   1.0000   0.0064
  -9.000  -0.6755   0.02159   0.01736  -0.0492   1.0000   0.0067
  -8.750  -0.6570   0.01977   0.01522  -0.0480   1.0000   0.0069
  -8.500  -0.6379   0.01817   0.01334  -0.0467   1.0000   0.0075
  -8.250  -0.6088   0.01690   0.01180  -0.0475   0.9982   0.0082
  -8.000  -0.5785   0.01581   0.01049  -0.0483   0.9962   0.0090
  -7.750  -0.5477   0.01485   0.00931  -0.0492   0.9941   0.0100
  -7.500  -0.5169   0.01416   0.00853  -0.0500   0.9910   0.0122
  -7.250  -0.4844   0.01395   0.00832  -0.0511   0.9880   0.0147
  -7.000  -0.4521   0.01380   0.00814  -0.0520   0.9852   0.0170
  -6.750  -0.4206   0.01413   0.00849  -0.0527   0.9806   0.0197
  -6.500  -0.3883   0.01414   0.00842  -0.0537   0.9772   0.0231
  -6.250  -0.3579   0.01411   0.00826  -0.0542   0.9716   0.0249
  -6.000  -0.3260   0.01407   0.00813  -0.0551   0.9665   0.0257
  -5.750  -0.2960   0.01342   0.00743  -0.0557   0.9594   0.0278
  -5.500  -0.2633   0.01329   0.00725  -0.0569   0.9527   0.0295
  -5.250  -0.2318   0.01300   0.00687  -0.0577   0.9449   0.0312
  -5.000  -0.1999   0.01263   0.00641  -0.0585   0.9381   0.0325
  -4.750  -0.1699   0.01213   0.00582  -0.0590   0.9301   0.0330
  -4.500  -0.1403   0.01166   0.00526  -0.0593   0.9216   0.0333
  -4.000  -0.0845   0.01100   0.00441  -0.0591   0.8980   0.0342
  -3.750  -0.0577   0.01061   0.00395  -0.0587   0.8871   0.0342
  -3.500  -0.0308   0.01027   0.00354  -0.0584   0.8778   0.0342
  -3.250  -0.0039   0.00997   0.00318  -0.0582   0.8687   0.0344
  -3.000   0.0232   0.00971   0.00287  -0.0579   0.8596   0.0346
  -2.750   0.0504   0.00949   0.00261  -0.0577   0.8509   0.0349
  -2.500   0.0776   0.00931   0.00238  -0.0575   0.8405   0.0352
  -2.250   0.1044   0.00902   0.00204  -0.0572   0.8277   0.0371
  -2.000   0.1317   0.00886   0.00185  -0.0570   0.8150   0.0395
  -1.750   0.1589   0.00877   0.00170  -0.0568   0.8005   0.0417
  -1.500   0.1859   0.00871   0.00157  -0.0565   0.7837   0.0436
  -1.250   0.2126   0.00871   0.00147  -0.0562   0.7595   0.0453
  -1.000   0.2391   0.00873   0.00137  -0.0558   0.7341   0.0474
  -0.750   0.2655   0.00875   0.00128  -0.0554   0.7049   0.0525
  -0.500   0.2918   0.00875   0.00122  -0.0551   0.6685   0.0676
  -0.250   0.3144   0.00897   0.00124  -0.0541   0.5624   0.1421
   0.000   0.3398   0.00913   0.00134  -0.0538   0.5253   0.1817
   0.250   0.3663   0.00918   0.00143  -0.0537   0.5057   0.2202
   0.500   0.3932   0.00918   0.00151  -0.0536   0.4918   0.2587
   1.000   0.4723   0.00757   0.00179  -0.0595   0.4566   1.0000
   1.250   0.4978   0.00774   0.00185  -0.0591   0.4259   1.0000
   1.500   0.5214   0.00814   0.00193  -0.0584   0.3493   1.0000
   1.750   0.5447   0.00863   0.00211  -0.0577   0.2816   1.0000
   2.000   0.5683   0.00909   0.00232  -0.0571   0.2210   1.0000
   2.250   0.5927   0.00944   0.00251  -0.0566   0.1880   1.0000
   2.500   0.6175   0.00974   0.00270  -0.0561   0.1684   1.0000
   2.750   0.6427   0.00998   0.00290  -0.0557   0.1549   1.0000
   3.000   0.6684   0.01017   0.00307  -0.0553   0.1476   1.0000
   3.250   0.6938   0.01039   0.00325  -0.0550   0.1347   1.0000
   3.500   0.7188   0.01067   0.00343  -0.0546   0.1051   1.0000
   3.750   0.7423   0.01118   0.00374  -0.0540   0.0735   1.0000
   4.000   0.7647   0.01185   0.00417  -0.0532   0.0245   1.0000
   4.250   0.7894   0.01222   0.00455  -0.0527   0.0163   1.0000
   4.500   0.8139   0.01260   0.00497  -0.0521   0.0135   1.0000
   4.750   0.8380   0.01308   0.00555  -0.0515   0.0109   1.0000
   5.000   0.8618   0.01359   0.00617  -0.0508   0.0099   1.0000
   5.250   0.8859   0.01405   0.00670  -0.0502   0.0093   1.0000
   5.500   0.9096   0.01456   0.00727  -0.0495   0.0085   1.0000
   5.750   0.9331   0.01505   0.00780  -0.0489   0.0076   1.0000
   6.000   0.9558   0.01566   0.00846  -0.0482   0.0070   1.0000
   6.250   0.9756   0.01670   0.00961  -0.0470   0.0065   1.0000
   6.500   0.9967   0.01753   0.01053  -0.0459   0.0062   1.0000
   6.750   1.0178   0.01835   0.01145  -0.0449   0.0059   1.0000
   7.000   1.0381   0.01929   0.01250  -0.0438   0.0057   1.0000
   7.250   1.0576   0.02036   0.01368  -0.0425   0.0054   1.0000
   7.500   1.0770   0.02143   0.01486  -0.0413   0.0052   1.0000
   7.750   1.0969   0.02234   0.01587  -0.0403   0.0048   1.0000
   8.000   1.1170   0.02311   0.01671  -0.0394   0.0046   1.0000
   8.250   1.1357   0.02403   0.01774  -0.0383   0.0043   1.0000
   8.500   1.1503   0.02567   0.01950  -0.0367   0.0041   1.0000
   8.750   1.1644   0.02745   0.02148  -0.0349   0.0040   1.0000
   9.000   1.1786   0.02907   0.02333  -0.0331   0.0039   1.0000
   9.250   1.1902   0.03099   0.02550  -0.0310   0.0038   1.0000
   9.500   1.1985   0.03322   0.02801  -0.0285   0.0037   1.0000
   9.750   1.2025   0.03575   0.03084  -0.0256   0.0036   1.0000
  10.000   1.2011   0.03844   0.03382  -0.0222   0.0035   1.0000
  10.250   1.1934   0.04103   0.03667  -0.0180   0.0034   1.0000
  10.500   1.1828   0.04391   0.03981  -0.0143   0.0034   1.0000
  10.750   1.1700   0.04720   0.04334  -0.0115   0.0034   1.0000
  11.000   1.1552   0.05099   0.04737  -0.0097   0.0033   1.0000
  11.250   1.1388   0.05541   0.05201  -0.0091   0.0033   1.0000
  11.500   1.1213   0.06056   0.05737  -0.0100   0.0033   1.0000
  11.750   1.1027   0.06671   0.06372  -0.0126   0.0033   1.0000
  12.000   1.0841   0.07406   0.07125  -0.0170   0.0034   1.0000
  12.250   1.0651   0.08260   0.07996  -0.0228   0.0034   1.0000
  12.500   1.0449   0.09229   0.08980  -0.0293   0.0034   1.0000
  12.750   1.0242   0.10331   0.10095  -0.0362   0.0035   1.0000
  13.000   1.0018   0.11508   0.11281  -0.0425   0.0036   1.0000
  13.250   0.9791   0.12648   0.12426  -0.0480   0.0037   1.0000
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