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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 100,000
Max Cl/Cd: 48.59 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14a147-il-100000.txt
Download as CSV file: xf-rg14a147-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5226   0.09990   0.09497  -0.0101   1.0000   0.0794
  -8.500  -0.5352   0.09699   0.09217  -0.0158   1.0000   0.0812
  -8.250  -0.5492   0.09370   0.08897  -0.0220   1.0000   0.0816
  -8.000  -0.5279   0.08853   0.08381  -0.0159   1.0000   0.0847
  -7.750  -0.5235   0.08524   0.08056  -0.0156   1.0000   0.0879
  -7.500  -0.5266   0.08152   0.07689  -0.0187   1.0000   0.0912
  -7.250  -0.5404   0.07756   0.07278  -0.0290   1.0000   0.0949
  -7.000  -0.5295   0.07261   0.06797  -0.0262   1.0000   0.0976
  -6.750  -0.5201   0.06950   0.06489  -0.0250   1.0000   0.1022
  -6.500  -0.5225   0.06503   0.06016  -0.0307   1.0000   0.1096
  -6.250  -0.5086   0.06202   0.05732  -0.0275   1.0000   0.1171
  -6.000  -0.5014   0.05839   0.05362  -0.0280   1.0000   0.1275
  -5.750  -0.4923   0.05512   0.05029  -0.0279   1.0000   0.1410
  -5.500  -0.4817   0.05197   0.04707  -0.0275   1.0000   0.1555
  -5.250  -0.4696   0.04887   0.04384  -0.0271   1.0000   0.1715
  -4.750  -0.4182   0.03545   0.02836  -0.0296   1.0000   0.0827
  -4.500  -0.3951   0.03031   0.02288  -0.0281   1.0000   0.0626
  -4.250  -0.3699   0.02722   0.01897  -0.0262   1.0000   0.0544
  -4.000  -0.3468   0.02435   0.01574  -0.0250   1.0000   0.0528
  -3.750  -0.3224   0.02209   0.01311  -0.0236   1.0000   0.0526
  -3.500  -0.2978   0.02059   0.01125  -0.0223   1.0000   0.0560
  -3.250  -0.2747   0.01873   0.00944  -0.0213   1.0000   0.0634
  -3.000  -0.2510   0.01723   0.00785  -0.0198   1.0000   0.0698
  -2.750  -0.2292   0.01589   0.00669  -0.0186   1.0000   0.0894
  -2.500  -0.2110   0.01287   0.00522  -0.0170   1.0000   0.3417
  -2.250  -0.1124   0.01141   0.00527  -0.0259   1.0000   1.0000
  -2.000  -0.1020   0.01128   0.00495  -0.0232   1.0000   1.0000
  -1.750  -0.0907   0.01119   0.00468  -0.0205   1.0000   1.0000
  -1.500  -0.0784   0.01115   0.00447  -0.0180   1.0000   1.0000
  -1.250  -0.0640   0.01116   0.00428  -0.0159   1.0000   1.0000
  -1.000  -0.0479   0.01120   0.00417  -0.0142   1.0000   1.0000
  -0.750  -0.0307   0.01129   0.00412  -0.0127   1.0000   1.0000
  -0.500  -0.0128   0.01141   0.00413  -0.0114   1.0000   1.0000
  -0.250   0.0055   0.01157   0.00419  -0.0102   1.0000   1.0000
   0.000   0.0240   0.01177   0.00430  -0.0092   1.0000   1.0000
   0.250   0.0424   0.01201   0.00445  -0.0082   1.0000   1.0000
   0.500   0.0607   0.01230   0.00468  -0.0074   1.0000   1.0000
   0.750   0.0788   0.01264   0.00498  -0.0066   1.0000   1.0000
   1.000   0.1302   0.01312   0.00546  -0.0123   0.9876   1.0000
   1.250   0.1858   0.01350   0.00586  -0.0184   0.9729   1.0000
   1.500   0.2412   0.01371   0.00612  -0.0243   0.9577   1.0000
   1.750   0.2977   0.01374   0.00626  -0.0300   0.9424   1.0000
   2.000   0.3495   0.01362   0.00630  -0.0345   0.9243   1.0000
   2.250   0.4034   0.01334   0.00617  -0.0390   0.9059   1.0000
   2.500   0.4507   0.01303   0.00601  -0.0418   0.8843   1.0000
   2.750   0.4900   0.01275   0.00591  -0.0429   0.8578   1.0000
   3.000   0.5216   0.01257   0.00583  -0.0424   0.8258   1.0000
   3.250   0.5494   0.01249   0.00579  -0.0410   0.7899   1.0000
   3.500   0.5746   0.01252   0.00581  -0.0393   0.7503   1.0000
   3.750   0.5970   0.01269   0.00596  -0.0372   0.7051   1.0000
   4.000   0.6189   0.01288   0.00613  -0.0351   0.6563   1.0000
   4.250   0.6399   0.01318   0.00632  -0.0329   0.6014   1.0000
   4.500   0.6599   0.01358   0.00658  -0.0307   0.5385   1.0000
   4.750   0.6789   0.01412   0.00690  -0.0286   0.4671   1.0000
   5.000   0.6959   0.01485   0.00728  -0.0263   0.3748   1.0000
   5.250   0.7107   0.01603   0.00782  -0.0242   0.2520   1.0000
   5.500   0.7226   0.01827   0.00920  -0.0220   0.1288   1.0000
   5.750   0.7380   0.02057   0.01112  -0.0197   0.0880   1.0000
   6.000   0.7591   0.02241   0.01295  -0.0182   0.0731   1.0000
   6.250   0.7815   0.02452   0.01496  -0.0172   0.0626   1.0000
   6.500   0.8074   0.02664   0.01741  -0.0161   0.0582   1.0000
   6.750   0.8320   0.02909   0.02009  -0.0150   0.0541   1.0000
   7.000   0.8523   0.03213   0.02341  -0.0140   0.0491   1.0000
   7.250   0.8718   0.03544   0.02730  -0.0122   0.0480   1.0000
   7.500   0.8876   0.03943   0.03185  -0.0104   0.0483   1.0000
   7.750   0.8998   0.04410   0.03698  -0.0087   0.0494   1.0000
   8.000   0.9115   0.04968   0.04284  -0.0075   0.0509   1.0000
   8.250   0.9192   0.05360   0.04730  -0.0057   0.0511   1.0000
   8.500   0.9061   0.06035   0.05493  -0.0031   0.0610   1.0000
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