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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 500,000
Max Cl/Cd: 78.93 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14a147-il-500000.txt
Download as CSV file: xf-rg14a147-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14A-1.4/7.0 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4457   0.11108   0.10887  -0.0075   1.0000   0.0120
 -10.500  -0.4442   0.10703   0.10482  -0.0085   1.0000   0.0122
  -9.500  -0.5268   0.09909   0.09678  -0.0103   1.0000   0.0119
  -9.250  -0.5291   0.09452   0.09223  -0.0119   1.0000   0.0122
  -9.000  -0.5281   0.09081   0.08854  -0.0133   1.0000   0.0124
  -8.750  -0.5276   0.08690   0.08465  -0.0151   1.0000   0.0124
  -8.500  -0.5277   0.08325   0.08103  -0.0167   1.0000   0.0126
  -8.250  -0.5291   0.07958   0.07739  -0.0185   1.0000   0.0128
  -8.000  -0.5351   0.07558   0.07344  -0.0209   1.0000   0.0128
  -7.750  -0.5389   0.07083   0.06869  -0.0250   1.0000   0.0129
  -7.500  -0.5380   0.06632   0.06415  -0.0279   1.0000   0.0131
  -7.250  -0.5354   0.06178   0.05955  -0.0301   1.0000   0.0132
  -7.000  -0.5310   0.05756   0.05527  -0.0314   1.0000   0.0135
  -6.750  -0.5249   0.05324   0.05084  -0.0323   1.0000   0.0137
  -6.500  -0.5171   0.04928   0.04676  -0.0325   1.0000   0.0141
  -6.250  -0.5078   0.04530   0.04263  -0.0322   1.0000   0.0146
  -6.000  -0.4970   0.04149   0.03864  -0.0315   1.0000   0.0152
  -5.750  -0.4846   0.03779   0.03472  -0.0305   1.0000   0.0160
  -5.500  -0.4703   0.03432   0.03100  -0.0290   1.0000   0.0171
  -5.250  -0.4466   0.03370   0.03013  -0.0271   1.0000   0.0194
  -5.000  -0.4306   0.03146   0.02758  -0.0254   1.0000   0.0196
  -4.750  -0.4236   0.02436   0.01993  -0.0238   1.0000   0.0212
  -4.500  -0.4056   0.02230   0.01773  -0.0226   1.0000   0.0224
  -4.250  -0.3812   0.01743   0.01212  -0.0197   1.0000   0.0121
  -4.000  -0.3588   0.01624   0.01076  -0.0184   1.0000   0.0112
  -3.750  -0.3327   0.01492   0.00921  -0.0178   0.9995   0.0115
  -3.500  -0.3017   0.01179   0.00575  -0.0183   0.9980   0.0129
  -3.250  -0.2652   0.01111   0.00505  -0.0203   0.9953   0.0158
  -3.000  -0.2293   0.01028   0.00412  -0.0219   0.9924   0.0175
  -2.750  -0.1932   0.00968   0.00343  -0.0236   0.9886   0.0196
  -2.500  -0.1563   0.00882   0.00259  -0.0254   0.9851   0.0501
  -2.250  -0.1193   0.00792   0.00232  -0.0280   0.9824   0.2088
  -2.000  -0.0890   0.00697   0.00213  -0.0291   0.9763   0.4190
  -1.750  -0.0560   0.00606   0.00199  -0.0306   0.9717   0.6381
  -1.500  -0.0281   0.00549   0.00207  -0.0301   0.9662   0.8345
  -1.250   0.0046   0.00536   0.00199  -0.0307   0.9597   0.8744
  -1.000   0.0368   0.00525   0.00191  -0.0312   0.9531   0.9038
  -0.750   0.0668   0.00517   0.00184  -0.0310   0.9439   0.9317
  -0.500   0.0992   0.00512   0.00176  -0.0315   0.9328   0.9496
  -0.250   0.1356   0.00509   0.00169  -0.0329   0.9207   0.9626
   0.000   0.1742   0.00508   0.00163  -0.0349   0.9067   0.9725
   0.250   0.2141   0.00509   0.00157  -0.0372   0.8890   0.9796
   0.500   0.2549   0.00512   0.00151  -0.0398   0.8660   0.9849
   0.750   0.2949   0.00517   0.00146  -0.0423   0.8399   0.9901
   1.000   0.3332   0.00524   0.00143  -0.0445   0.8106   0.9957
   1.250   0.3694   0.00534   0.00138  -0.0463   0.7785   1.0000
   1.500   0.3901   0.00544   0.00137  -0.0448   0.7489   1.0000
   1.750   0.4109   0.00556   0.00138  -0.0433   0.7197   1.0000
   2.000   0.4317   0.00568   0.00140  -0.0419   0.6848   1.0000
   2.250   0.4523   0.00585   0.00143  -0.0404   0.6468   1.0000
   2.500   0.4733   0.00605   0.00149  -0.0390   0.6091   1.0000
   2.750   0.4949   0.00627   0.00161  -0.0377   0.5698   1.0000
   3.000   0.5165   0.00655   0.00171  -0.0365   0.5246   1.0000
   3.250   0.5386   0.00685   0.00184  -0.0354   0.4774   1.0000
   3.500   0.5604   0.00724   0.00200  -0.0343   0.4164   1.0000
   3.750   0.5828   0.00767   0.00219  -0.0333   0.3571   1.0000
   4.000   0.6057   0.00811   0.00244  -0.0325   0.2982   1.0000
   4.250   0.6287   0.00860   0.00270  -0.0318   0.2398   1.0000
   4.500   0.6519   0.00911   0.00299  -0.0312   0.1860   1.0000
   4.750   0.6746   0.00974   0.00335  -0.0305   0.1276   1.0000
   5.000   0.6967   0.01049   0.00381  -0.0297   0.0666   1.0000
   5.250   0.7183   0.01143   0.00454  -0.0286   0.0295   1.0000
   5.500   0.7423   0.01202   0.00526  -0.0278   0.0256   1.0000
   5.750   0.7664   0.01255   0.00585  -0.0272   0.0215   1.0000
   6.000   0.7868   0.01374   0.00717  -0.0258   0.0183   1.0000
   6.250   0.8095   0.01451   0.00805  -0.0249   0.0163   1.0000
   6.500   0.8329   0.01521   0.00882  -0.0241   0.0141   1.0000
   6.750   0.8550   0.01614   0.00983  -0.0232   0.0122   1.0000
   7.000   0.8711   0.01871   0.01261  -0.0212   0.0105   1.0000
   7.250   0.8890   0.02170   0.01592  -0.0195   0.0099   1.0000
   7.500   0.9090   0.02384   0.01837  -0.0182   0.0097   1.0000
   7.750   0.9283   0.02584   0.02065  -0.0169   0.0094   1.0000
   8.000   0.9498   0.02668   0.02166  -0.0160   0.0084   1.0000
   8.250   0.9656   0.02913   0.02443  -0.0144   0.0079   1.0000
   8.500   0.9772   0.03225   0.02793  -0.0125   0.0077   1.0000
   8.750   0.9845   0.03584   0.03191  -0.0103   0.0075   1.0000
   9.000   0.9814   0.04099   0.03752  -0.0074   0.0077   1.0000
   9.250   0.9709   0.04640   0.04334  -0.0046   0.0079   1.0000
   9.500   0.9542   0.05150   0.04876  -0.0020   0.0081   1.0000
   9.750   0.9327   0.05532   0.05276   0.0009   0.0083   1.0000
  10.000   0.9104   0.05951   0.05710   0.0014   0.0085   1.0000
  10.250   0.8900   0.06469   0.06242  -0.0011   0.0085   1.0000
  10.500   0.8731   0.07086   0.06870  -0.0062   0.0087   1.0000
  10.750   0.8514   0.08090   0.07883  -0.0150   0.0091   1.0000
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