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D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: D.G.A. 1182 (dga1182-il)
Reynolds number: 200,000
Max Cl/Cd: 37.49 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-dga1182-il-200000-n5.txt
Download as CSV file: xf-dga1182-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6137   0.09705   0.09190   0.0044   0.1602   0.0188
  -8.250  -0.6116   0.09208   0.08695  -0.0002   0.1602   0.0189
  -8.000  -0.6118   0.08676   0.08163  -0.0060   0.1601   0.0189
  -7.750  -0.6090   0.08178   0.07657  -0.0103   0.1600   0.0189
  -7.500  -0.6045   0.07728   0.07196  -0.0132   0.1600   0.0190
  -7.250  -0.5978   0.07293   0.06747  -0.0154   0.1599   0.0191
  -7.000  -0.5891   0.06866   0.06305  -0.0169   0.1598   0.0191
  -6.750  -0.5782   0.06443   0.05863  -0.0180   0.1597   0.0192
  -6.500  -0.5656   0.06027   0.05426  -0.0188   0.1596   0.0192
  -6.250  -0.5515   0.05623   0.04997  -0.0192   0.1596   0.0193
  -5.750  -0.5317   0.04538   0.03880  -0.0203   0.1595   0.0155
  -5.500  -0.5118   0.04079   0.03384  -0.0199   0.1594   0.0135
  -5.250  -0.4901   0.03772   0.03042  -0.0196   0.1594   0.0148
  -5.000  -0.4671   0.03447   0.02678  -0.0189   0.1593   0.0152
  -4.750  -0.4431   0.03091   0.02277  -0.0180   0.1593   0.0138
  -4.500  -0.4176   0.02768   0.01904  -0.0170   0.1593   0.0127
  -4.250  -0.3912   0.02511   0.01600  -0.0160   0.1593   0.0121
  -4.000  -0.3648   0.02313   0.01368  -0.0153   0.1594   0.0119
  -3.750  -0.3384   0.02148   0.01177  -0.0147   0.1595   0.0121
  -3.500  -0.3122   0.02010   0.01018  -0.0142   0.1597   0.0125
  -3.250  -0.2861   0.01915   0.00910  -0.0138   0.1599   0.0142
  -3.000  -0.2601   0.01822   0.00805  -0.0133   0.1601   0.0160
  -2.750  -0.2343   0.01727   0.00700  -0.0127   0.1603   0.0168
  -2.500  -0.2083   0.01654   0.00613  -0.0123   0.1605   0.0179
  -2.250  -0.1820   0.01595   0.00541  -0.0121   0.1608   0.0206
  -2.000  -0.1553   0.01552   0.00485  -0.0119   0.1610   0.0248
  -1.750  -0.1280   0.01532   0.00448  -0.0117   0.1605   0.0306
  -1.500  -0.1014   0.01469   0.00427  -0.0117   0.1594   0.1797
  -1.250  -0.0748   0.01445   0.00437  -0.0118   0.1578   0.3458
  -1.000  -0.0468   0.01518   0.00485  -0.0118   0.1560   0.3809
  -0.750  -0.0196   0.01538   0.00490  -0.0117   0.1549   0.3853
  -0.500   0.0075   0.01550   0.00491  -0.0117   0.1545   0.3881
  -0.250   0.0342   0.01580   0.00505  -0.0116   0.1532   0.3908
   0.000   0.0613   0.01598   0.00512  -0.0116   0.1516   0.3934
   0.250   0.0887   0.01604   0.00511  -0.0115   0.1503   0.3947
   0.500   0.1159   0.01616   0.00516  -0.0115   0.1493   0.3957
   0.750   0.1430   0.01632   0.00524  -0.0115   0.1483   0.3966
   1.000   0.1700   0.01647   0.00536  -0.0114   0.1470   0.3976
   1.250   0.1967   0.01664   0.00550  -0.0114   0.1456   0.3989
   1.500   0.2232   0.01701   0.00581  -0.0113   0.1436   0.4002
   1.750   0.2503   0.01711   0.00595  -0.0113   0.1400   0.4014
   2.000   0.2773   0.01725   0.00615  -0.0113   0.1344   0.4022
   2.250   0.3044   0.01730   0.00627  -0.0113   0.1298   0.4030
   2.500   0.3316   0.01733   0.00639  -0.0112   0.1256   0.4042
   2.750   0.3588   0.01738   0.00653  -0.0112   0.1217   0.4054
   3.000   0.3863   0.01725   0.00657  -0.0112   0.1158   0.4062
   3.250   0.4138   0.01718   0.00670  -0.0110   0.1016   0.4069
   3.500   0.4412   0.01712   0.00675  -0.0110   0.0923   0.4078
   3.750   0.4696   0.01681   0.00649  -0.0112   0.0865   0.4089
   4.000   0.4985   0.01651   0.00619  -0.0113   0.0795   0.4100
   4.250   0.5247   0.01682   0.00657  -0.0111   0.0718   0.4108
   4.500   0.5509   0.01713   0.00695  -0.0110   0.0655   0.4117
   4.750   0.5768   0.01749   0.00746  -0.0107   0.0611   0.4128
   5.000   0.6026   0.01788   0.00798  -0.0105   0.0580   0.4143
   5.250   0.6283   0.01828   0.00848  -0.0103   0.0551   0.4160
   5.500   0.6536   0.01878   0.00914  -0.0100   0.0527   0.4177
   5.750   0.6789   0.01934   0.00987  -0.0097   0.0513   0.4190
   6.000   0.7040   0.01998   0.01069  -0.0093   0.0497   0.4200
   6.250   0.7292   0.02060   0.01149  -0.0090   0.0476   0.4207
   6.500   0.7547   0.02077   0.01173  -0.0089   0.0428   0.4214
   6.750   0.7800   0.02114   0.01226  -0.0088   0.0371   0.4222
   7.000   0.8044   0.02164   0.01287  -0.0086   0.0311   0.4230
   7.250   0.8301   0.02214   0.01362  -0.0084   0.0235   0.4239
   7.500   0.8543   0.02301   0.01459  -0.0080   0.0172   0.4248
   7.750   0.8782   0.02397   0.01564  -0.0077   0.0130   0.4258
   8.000   0.8981   0.02611   0.01811  -0.0067   0.0108   0.4269
   8.250   0.9184   0.02833   0.02077  -0.0058   0.0100   0.4280
   8.500   0.9368   0.03107   0.02398  -0.0049   0.0093   0.4292
   8.750   0.9551   0.03352   0.02681  -0.0041   0.0083   0.4306
   9.000   0.9732   0.03543   0.02897  -0.0036   0.0075   0.4321
   9.250   0.9832   0.03932   0.03334  -0.0025   0.0070   0.4333
   9.500   0.9829   0.04519   0.03982  -0.0011   0.0069   0.4341
  10.000   0.9577   0.05897   0.05454   0.0004   0.0069   0.4346
  10.250   0.9337   0.06566   0.06149   0.0001   0.0070   0.4345
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