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RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il)
Reynolds number: 1,000,000
Max Cl/Cd: 88.05 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rg14a147-il-1000000.txt
Download as CSV file: xf-rg14a147-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5322   0.09229   0.09066  -0.0108   1.0000   0.0067
  -9.000  -0.5350   0.08774   0.08613  -0.0129   1.0000   0.0068
  -8.750  -0.5355   0.08368   0.08209  -0.0149   1.0000   0.0069
  -8.500  -0.5382   0.07942   0.07786  -0.0172   1.0000   0.0069
  -8.250  -0.5433   0.07517   0.07363  -0.0198   1.0000   0.0070
  -8.000  -0.5516   0.07034   0.06882  -0.0240   1.0000   0.0070
  -7.750  -0.5527   0.06502   0.06347  -0.0280   1.0000   0.0070
  -7.500  -0.5516   0.05999   0.05838  -0.0306   1.0000   0.0071
  -7.250  -0.5484   0.05542   0.05374  -0.0320   1.0000   0.0072
  -7.000  -0.5436   0.05116   0.04938  -0.0325   1.0000   0.0073
  -6.750  -0.5373   0.04680   0.04489  -0.0325   1.0000   0.0073
  -6.500  -0.5291   0.04310   0.04105  -0.0319   1.0000   0.0075
  -6.250  -0.5197   0.03945   0.03725  -0.0308   1.0000   0.0077
  -4.750  -0.3953   0.01524   0.01082  -0.0275   0.9952   0.0070
  -4.500  -0.3616   0.01381   0.00923  -0.0286   0.9938   0.0061
  -4.250  -0.3315   0.01170   0.00684  -0.0289   0.9915   0.0060
  -4.000  -0.2987   0.01072   0.00571  -0.0298   0.9890   0.0063
  -3.750  -0.2669   0.00907   0.00389  -0.0308   0.9865   0.0080
  -3.500  -0.2317   0.00864   0.00342  -0.0324   0.9845   0.0091
  -3.250  -0.1955   0.00823   0.00297  -0.0342   0.9828   0.0104
  -3.000  -0.1641   0.00796   0.00269  -0.0350   0.9786   0.0115
  -2.750  -0.1311   0.00728   0.00186  -0.0359   0.9745   0.0188
  -2.500  -0.0967   0.00674   0.00155  -0.0375   0.9711   0.0748
  -2.250  -0.0664   0.00627   0.00136  -0.0382   0.9648   0.1558
  -2.000  -0.0359   0.00573   0.00119  -0.0390   0.9574   0.2665
  -1.750  -0.0069   0.00521   0.00104  -0.0395   0.9468   0.3909
  -1.500   0.0217   0.00468   0.00091  -0.0399   0.9335   0.5264
  -1.250   0.0452   0.00393   0.00086  -0.0390   0.9162   0.7472
  -1.000   0.0710   0.00382   0.00084  -0.0383   0.8966   0.8058
  -0.750   0.0968   0.00381   0.00081  -0.0375   0.8751   0.8354
  -0.500   0.1216   0.00381   0.00080  -0.0366   0.8519   0.8648
  -0.250   0.1467   0.00386   0.00079  -0.0357   0.8273   0.8845
   0.250   0.1962   0.00400   0.00079  -0.0339   0.7726   0.9151
   0.500   0.2206   0.00409   0.00080  -0.0330   0.7504   0.9296
   0.750   0.2454   0.00416   0.00083  -0.0321   0.7298   0.9431
   1.000   0.2708   0.00424   0.00085  -0.0314   0.7061   0.9562
   1.250   0.2979   0.00435   0.00086  -0.0311   0.6727   0.9690
   1.500   0.3294   0.00451   0.00089  -0.0318   0.6371   0.9775
   1.750   0.3621   0.00469   0.00095  -0.0329   0.6008   0.9849
   2.000   0.3978   0.00488   0.00100  -0.0348   0.5616   0.9900
   2.250   0.4329   0.00510   0.00106  -0.0365   0.5207   0.9948
   2.500   0.4691   0.00534   0.00114  -0.0385   0.4712   0.9986
   2.750   0.4957   0.00563   0.00124  -0.0385   0.4181   1.0000
   3.000   0.5162   0.00594   0.00135  -0.0372   0.3650   1.0000
   3.250   0.5382   0.00624   0.00148  -0.0361   0.3208   1.0000
   3.500   0.5604   0.00659   0.00163  -0.0351   0.2705   1.0000
   3.750   0.5836   0.00692   0.00181  -0.0344   0.2282   1.0000
   4.000   0.6068   0.00734   0.00203  -0.0336   0.1784   1.0000
   4.250   0.6302   0.00780   0.00228  -0.0329   0.1298   1.0000
   4.500   0.6542   0.00823   0.00254  -0.0323   0.0915   1.0000
   4.750   0.6778   0.00875   0.00287  -0.0317   0.0503   1.0000
   5.000   0.7015   0.00932   0.00328  -0.0310   0.0229   1.0000
   5.250   0.7261   0.00980   0.00385  -0.0303   0.0174   1.0000
   5.500   0.7518   0.01007   0.00416  -0.0300   0.0163   1.0000
   5.750   0.7771   0.01039   0.00451  -0.0296   0.0141   1.0000
   6.000   0.8014   0.01093   0.00510  -0.0290   0.0119   1.0000
   6.250   0.8231   0.01190   0.00623  -0.0278   0.0099   1.0000
   6.500   0.8488   0.01216   0.00653  -0.0275   0.0090   1.0000
   6.750   0.8736   0.01259   0.00698  -0.0271   0.0075   1.0000
   7.000   0.8965   0.01331   0.00778  -0.0263   0.0062   1.0000
   7.250   0.9142   0.01499   0.00967  -0.0246   0.0053   1.0000
   7.500   0.9391   0.01534   0.01007  -0.0242   0.0049   1.0000
   7.750   0.9604   0.01640   0.01127  -0.0232   0.0046   1.0000
   8.000   0.9816   0.01747   0.01247  -0.0222   0.0044   1.0000
   8.250   1.0018   0.01877   0.01393  -0.0211   0.0041   1.0000
   8.500   1.0231   0.01973   0.01501  -0.0202   0.0039   1.0000
   8.750   1.0448   0.02048   0.01585  -0.0195   0.0036   1.0000
   9.000   1.0648   0.02151   0.01700  -0.0186   0.0034   1.0000
   9.250   1.0808   0.02317   0.01884  -0.0173   0.0031   1.0000
   9.500   1.0380   0.01855   0.01523  -0.0113   0.0027   1.0000
   9.750   1.0404   0.02155   0.01855  -0.0090   0.0027   1.0000
  10.000   1.0319   0.02538   0.02270  -0.0059   0.0027   1.0000
  10.250   1.0124   0.02859   0.02616  -0.0015   0.0026   1.0000
  10.500   0.9892   0.03188   0.02964   0.0014   0.0026   1.0000
  10.750   0.9617   0.03638   0.03432   0.0020   0.0027   1.0000
  11.000   0.9394   0.04171   0.03978   0.0002   0.0027   1.0000
  11.250   0.9095   0.05016   0.04838  -0.0044   0.0027   1.0000
  11.500   0.8856   0.05977   0.05812  -0.0103   0.0028   1.0000
  12.750   0.8748   0.11705   0.11562  -0.0380   0.0031   1.0000
  13.000   0.8056   0.14541   0.14386  -0.0496   0.0049   1.0000
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