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RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 100,000
Max Cl/Cd: 48.22 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg1410-il-100000.txt
Download as CSV file: xf-rg1410-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 10% AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4846   0.10302   0.09782  -0.0199   1.0000   0.1257
  -9.500  -0.5013   0.09960   0.09450  -0.0241   1.0000   0.1311
  -9.250  -0.5466   0.09553   0.09063  -0.0329   1.0000   0.1324
  -9.000  -0.4925   0.09185   0.08682  -0.0239   1.0000   0.1371
  -8.750  -0.4935   0.08856   0.08358  -0.0246   1.0000   0.1423
  -8.500  -0.5428   0.08449   0.07970  -0.0316   1.0000   0.1463
  -8.250  -0.5347   0.08010   0.07536  -0.0300   1.0000   0.1492
  -8.000  -0.5188   0.07758   0.07285  -0.0273   1.0000   0.1544
  -7.750  -0.5869   0.07410   0.06920  -0.0336   1.0000   0.1616
  -7.500  -0.5505   0.06953   0.06486  -0.0298   1.0000   0.1648
  -7.250  -0.6061   0.05137   0.04565  -0.0357   1.0000   0.0917
  -7.000  -0.6082   0.04406   0.03760  -0.0332   1.0000   0.0751
  -6.750  -0.6007   0.04048   0.03370  -0.0311   1.0000   0.0747
  -6.500  -0.5913   0.03730   0.03008  -0.0289   1.0000   0.0751
  -6.250  -0.5790   0.03419   0.02656  -0.0268   1.0000   0.0749
  -6.000  -0.5642   0.03137   0.02331  -0.0248   1.0000   0.0749
  -5.750  -0.5471   0.02905   0.02054  -0.0229   1.0000   0.0756
  -5.500  -0.5292   0.02675   0.01801  -0.0215   1.0000   0.0787
  -5.250  -0.5096   0.02534   0.01649  -0.0201   1.0000   0.0829
  -5.000  -0.4885   0.02381   0.01471  -0.0187   1.0000   0.0863
  -4.750  -0.4668   0.02247   0.01307  -0.0172   1.0000   0.0904
  -4.500  -0.4463   0.02124   0.01196  -0.0161   1.0000   0.0992
  -4.250  -0.4252   0.02005   0.01077  -0.0148   1.0000   0.1089
  -4.000  -0.4045   0.01902   0.00979  -0.0134   1.0000   0.1239
  -3.750  -0.3845   0.01810   0.00899  -0.0121   1.0000   0.1494
  -3.500  -0.3653   0.01722   0.00836  -0.0108   1.0000   0.1880
  -3.250  -0.3467   0.01632   0.00786  -0.0095   1.0000   0.2487
  -3.000  -0.3297   0.01526   0.00750  -0.0081   1.0000   0.3569
  -2.750  -0.3161   0.01416   0.00741  -0.0055   1.0000   0.5392
  -2.500  -0.3070   0.01373   0.00789  -0.0003   1.0000   0.7447
  -2.250  -0.2958   0.01395   0.00826   0.0044   1.0000   0.8604
  -2.000  -0.2404   0.01448   0.00866   0.0010   1.0000   0.9508
  -1.750  -0.1022   0.01511   0.00877  -0.0189   1.0000   1.0000
  -1.500  -0.1097   0.01504   0.00864  -0.0143   1.0000   1.0000
  -1.250  -0.1144   0.01503   0.00855  -0.0102   1.0000   1.0000
  -1.000  -0.0923   0.01524   0.00863  -0.0107   0.9960   1.0000
  -0.750  -0.0385   0.01563   0.00886  -0.0166   0.9855   1.0000
  -0.500   0.0131   0.01591   0.00901  -0.0220   0.9742   1.0000
  -0.250   0.0635   0.01610   0.00910  -0.0269   0.9623   1.0000
   0.000   0.1129   0.01621   0.00914  -0.0316   0.9503   1.0000
   0.250   0.1648   0.01625   0.00913  -0.0365   0.9389   1.0000
   0.500   0.2216   0.01618   0.00903  -0.0421   0.9288   1.0000
   0.750   0.2709   0.01603   0.00888  -0.0462   0.9160   1.0000
   1.000   0.3223   0.01580   0.00867  -0.0505   0.9035   1.0000
   1.250   0.3707   0.01548   0.00838  -0.0540   0.8900   1.0000
   1.500   0.4149   0.01515   0.00808  -0.0566   0.8750   1.0000
   1.750   0.4543   0.01482   0.00778  -0.0581   0.8581   1.0000
   2.000   0.4910   0.01446   0.00743  -0.0588   0.8394   1.0000
   2.250   0.5154   0.01429   0.00727  -0.0572   0.8151   1.0000
   2.500   0.5418   0.01409   0.00704  -0.0559   0.7915   1.0000
   2.750   0.5644   0.01399   0.00690  -0.0540   0.7658   1.0000
   3.000   0.5851   0.01401   0.00688  -0.0520   0.7400   1.0000
   3.250   0.6070   0.01406   0.00690  -0.0502   0.7153   1.0000
   3.500   0.6286   0.01415   0.00693  -0.0484   0.6902   1.0000
   3.750   0.6484   0.01431   0.00705  -0.0463   0.6633   1.0000
   4.000   0.6684   0.01448   0.00715  -0.0443   0.6352   1.0000
   4.250   0.6879   0.01466   0.00728  -0.0422   0.6054   1.0000
   4.500   0.7070   0.01488   0.00741  -0.0400   0.5740   1.0000
   4.750   0.7258   0.01514   0.00756  -0.0379   0.5413   1.0000
   5.000   0.7441   0.01545   0.00778  -0.0357   0.5061   1.0000
   5.250   0.7619   0.01580   0.00803  -0.0335   0.4678   1.0000
   5.500   0.7789   0.01623   0.00833  -0.0312   0.4254   1.0000
   5.750   0.7951   0.01680   0.00869  -0.0289   0.3790   1.0000
   6.000   0.8108   0.01753   0.00916  -0.0267   0.3323   1.0000
   6.250   0.8270   0.01837   0.00978  -0.0246   0.2897   1.0000
   6.500   0.8441   0.01930   0.01049  -0.0228   0.2547   1.0000
   6.750   0.8620   0.02028   0.01130  -0.0212   0.2255   1.0000
   7.000   0.8805   0.02131   0.01217  -0.0198   0.2012   1.0000
   7.250   0.9001   0.02242   0.01322  -0.0185   0.1805   1.0000
   7.500   0.9202   0.02360   0.01436  -0.0173   0.1631   1.0000
   7.750   0.9412   0.02491   0.01563  -0.0163   0.1482   1.0000
   8.000   0.9623   0.02630   0.01705  -0.0154   0.1352   1.0000
   8.250   0.9837   0.02780   0.01857  -0.0145   0.1239   1.0000
   8.500   1.0055   0.02936   0.02006  -0.0138   0.1138   1.0000
   8.750   1.0245   0.03068   0.02167  -0.0124   0.1051   1.0000
   9.000   1.0437   0.03247   0.02360  -0.0113   0.0972   1.0000
   9.250   1.0632   0.03403   0.02521  -0.0103   0.0902   1.0000
   9.500   1.0778   0.03627   0.02780  -0.0086   0.0841   1.0000
   9.750   1.0939   0.03794   0.02960  -0.0072   0.0782   1.0000
  10.000   1.1053   0.04072   0.03268  -0.0055   0.0737   1.0000
  10.250   1.1115   0.04315   0.03556  -0.0030   0.0696   1.0000
  10.500   1.1246   0.04515   0.03762  -0.0016   0.0655   1.0000
  10.750   1.1278   0.04877   0.04147   0.0003   0.0628   1.0000
  11.000   1.1182   0.05180   0.04502   0.0038   0.0613   1.0000
  11.250   1.1046   0.05520   0.04883   0.0072   0.0602   1.0000
  11.500   1.0861   0.05862   0.05255   0.0107   0.0599   1.0000
  11.750   1.0638   0.06241   0.05661   0.0131   0.0598   1.0000
  12.000   1.0397   0.06675   0.06118   0.0142   0.0601   1.0000
  12.250   1.0130   0.07185   0.06649   0.0136   0.0606   1.0000
  12.500   0.9852   0.07791   0.07272   0.0113   0.0612   1.0000
  12.750   0.9581   0.08499   0.07993   0.0075   0.0619   1.0000
  13.000   0.9325   0.09306   0.08807   0.0028   0.0627   1.0000
  13.250   0.9111   0.10162   0.09667  -0.0020   0.0634   1.0000
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