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RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: RG 14 AIRFOIL (rg14-il)
Reynolds number: 50,000
Max Cl/Cd: 34.78 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg14-il-50000-n5.txt
Download as CSV file: xf-rg14-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5093   0.10219   0.09508  -0.0225   1.0000   0.0450
  -9.250  -0.5074   0.09813   0.09108  -0.0237   1.0000   0.0447
  -9.000  -0.5066   0.09402   0.08703  -0.0250   1.0000   0.0443
  -8.750  -0.5078   0.08972   0.08280  -0.0268   1.0000   0.0439
  -8.500  -0.5100   0.08546   0.07861  -0.0288   1.0000   0.0433
  -8.250  -0.5146   0.08113   0.07436  -0.0310   1.0000   0.0427
  -8.000  -0.5204   0.07669   0.06996  -0.0330   1.0000   0.0422
  -7.750  -0.5248   0.07215   0.06542  -0.0346   1.0000   0.0416
  -7.500  -0.5284   0.06767   0.06090  -0.0358   1.0000   0.0410
  -7.250  -0.5311   0.06317   0.05629  -0.0365   1.0000   0.0405
  -7.000  -0.5316   0.05875   0.05171  -0.0367   1.0000   0.0400
  -6.750  -0.5296   0.05439   0.04711  -0.0365   1.0000   0.0396
  -6.500  -0.5245   0.05023   0.04264  -0.0359   1.0000   0.0394
  -6.250  -0.5163   0.04622   0.03825  -0.0350   1.0000   0.0394
  -6.000  -0.5051   0.04250   0.03403  -0.0339   1.0000   0.0396
  -5.750  -0.4912   0.03899   0.03004  -0.0327   1.0000   0.0402
  -5.500  -0.4745   0.03585   0.02639  -0.0313   1.0000   0.0410
  -5.250  -0.4554   0.03301   0.02303  -0.0299   1.0000   0.0425
  -5.000  -0.4346   0.03068   0.02017  -0.0286   1.0000   0.0459
  -4.750  -0.4151   0.02903   0.01845  -0.0275   1.0000   0.0517
  -4.500  -0.3924   0.02717   0.01619  -0.0261   1.0000   0.0569
  -4.250  -0.3710   0.02554   0.01452  -0.0248   1.0000   0.0640
  -4.000  -0.3495   0.02425   0.01313  -0.0235   1.0000   0.0788
  -3.750  -0.3273   0.02292   0.01164  -0.0222   1.0000   0.0989
  -3.500  -0.3051   0.02167   0.01046  -0.0213   1.0000   0.1284
  -3.250  -0.2847   0.02050   0.00950  -0.0202   1.0000   0.1785
  -3.000  -0.2657   0.01923   0.00876  -0.0191   1.0000   0.2682
  -2.750  -0.2501   0.01787   0.00828  -0.0172   1.0000   0.4344
  -2.500  -0.2402   0.01682   0.00842  -0.0121   1.0000   0.6764
  -2.250  -0.2090   0.01680   0.00854  -0.0100   1.0000   0.8890
  -2.000  -0.1040   0.01683   0.00781  -0.0240   1.0000   1.0000
  -1.750  -0.0960   0.01675   0.00753  -0.0211   1.0000   1.0000
  -1.500  -0.0871   0.01672   0.00731  -0.0184   1.0000   1.0000
  -1.250  -0.0765   0.01674   0.00714  -0.0161   1.0000   1.0000
  -1.000  -0.0641   0.01682   0.00703  -0.0140   1.0000   1.0000
  -0.750  -0.0502   0.01694   0.00698  -0.0123   1.0000   1.0000
  -0.500  -0.0352   0.01710   0.00696  -0.0108   1.0000   1.0000
  -0.250   0.0082   0.01743   0.00710  -0.0147   0.9878   1.0000
   0.000   0.0513   0.01772   0.00725  -0.0184   0.9746   1.0000
   0.250   0.0934   0.01797   0.00737  -0.0218   0.9609   1.0000
   0.500   0.1348   0.01818   0.00749  -0.0249   0.9467   1.0000
   0.750   0.1763   0.01835   0.00761  -0.0280   0.9322   1.0000
   1.000   0.2179   0.01846   0.00771  -0.0309   0.9175   1.0000
   1.250   0.2602   0.01853   0.00778  -0.0338   0.9027   1.0000
   1.500   0.3020   0.01855   0.00784  -0.0364   0.8873   1.0000
   1.750   0.3369   0.01858   0.00793  -0.0376   0.8685   1.0000
   2.000   0.3736   0.01857   0.00797  -0.0389   0.8502   1.0000
   2.250   0.4097   0.01854   0.00800  -0.0400   0.8313   1.0000
   2.500   0.4409   0.01855   0.00808  -0.0401   0.8093   1.0000
   2.750   0.4722   0.01856   0.00820  -0.0402   0.7868   1.0000
   3.000   0.5034   0.01856   0.00826  -0.0400   0.7637   1.0000
   3.250   0.5306   0.01863   0.00839  -0.0392   0.7375   1.0000
   3.500   0.5573   0.01873   0.00854  -0.0383   0.7103   1.0000
   3.750   0.5832   0.01886   0.00877  -0.0372   0.6817   1.0000
   4.000   0.6079   0.01905   0.00900  -0.0359   0.6510   1.0000
   4.250   0.6318   0.01929   0.00927  -0.0346   0.6185   1.0000
   4.500   0.6555   0.01957   0.00954  -0.0332   0.5852   1.0000
   4.750   0.6778   0.01991   0.00991  -0.0316   0.5493   1.0000
   5.000   0.6996   0.02031   0.01036  -0.0301   0.5123   1.0000
   5.250   0.7207   0.02077   0.01079  -0.0284   0.4738   1.0000
   5.500   0.7409   0.02130   0.01130  -0.0268   0.4333   1.0000
   5.750   0.7603   0.02192   0.01188  -0.0251   0.3917   1.0000
   6.000   0.7790   0.02264   0.01254  -0.0235   0.3488   1.0000
   6.250   0.7970   0.02346   0.01330  -0.0219   0.3058   1.0000
   6.500   0.8145   0.02442   0.01419  -0.0203   0.2632   1.0000
   6.750   0.8313   0.02552   0.01528  -0.0188   0.2228   1.0000
   7.000   0.8474   0.02679   0.01643  -0.0173   0.1861   1.0000
   7.250   0.8639   0.02821   0.01782  -0.0159   0.1544   1.0000
   7.500   0.8793   0.02974   0.01930  -0.0144   0.1262   1.0000
   7.750   0.8940   0.03147   0.02093  -0.0129   0.1056   1.0000
   8.000   0.9101   0.03327   0.02289  -0.0114   0.0867   1.0000
   8.250   0.9248   0.03514   0.02486  -0.0100   0.0725   1.0000
   8.500   0.9410   0.03738   0.02724  -0.0085   0.0628   1.0000
   8.750   0.9565   0.03968   0.02961  -0.0072   0.0558   1.0000
   9.000   0.9701   0.04209   0.03251  -0.0057   0.0483   1.0000
   9.250   0.9815   0.04450   0.03494  -0.0045   0.0438   1.0000
   9.500   0.9932   0.04801   0.03894  -0.0029   0.0415   1.0000
   9.750   0.9982   0.05176   0.04321  -0.0011   0.0397   1.0000
  10.000   0.9977   0.05536   0.04722   0.0007   0.0382   1.0000
  10.250   0.9926   0.05863   0.05078   0.0026   0.0367   1.0000
  10.500   0.9834   0.06186   0.05426   0.0044   0.0357   1.0000
  10.750   0.9722   0.06532   0.05792   0.0054   0.0349   1.0000
  11.000   0.9606   0.06896   0.06169   0.0055   0.0340   1.0000
  11.250   0.9383   0.07457   0.06758   0.0038   0.0346   1.0000
  11.500   0.9028   0.08354   0.07685  -0.0015   0.0371   1.0000
  11.750   0.8769   0.09247   0.08589  -0.0077   0.0388   1.0000
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