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RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9% AIRFOIL (rg149-il)
Reynolds number: 500,000
Max Cl/Cd: 70.82 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg149-il-500000-n5.txt
Download as CSV file: xf-rg149-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9% 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.8160   0.04410   0.04153  -0.0539   1.0000   0.0063
 -11.000  -0.8535   0.03901   0.03616  -0.0509   1.0000   0.0062
 -10.750  -0.8722   0.03451   0.03127  -0.0482   1.0000   0.0063
 -10.500  -0.8788   0.03095   0.02734  -0.0455   1.0000   0.0064
 -10.250  -0.8763   0.02828   0.02434  -0.0431   1.0000   0.0066
 -10.000  -0.8688   0.02609   0.02184  -0.0409   1.0000   0.0069
  -9.750  -0.8577   0.02431   0.01978  -0.0389   1.0000   0.0071
  -9.500  -0.8442   0.02281   0.01803  -0.0371   1.0000   0.0072
  -9.250  -0.8302   0.02141   0.01647  -0.0353   1.0000   0.0076
  -9.000  -0.8119   0.02067   0.01562  -0.0340   1.0000   0.0079
  -8.750  -0.7931   0.01998   0.01483  -0.0327   1.0000   0.0082
  -8.500  -0.7730   0.01955   0.01434  -0.0315   1.0000   0.0087
  -8.250  -0.7543   0.01877   0.01343  -0.0301   1.0000   0.0092
  -8.000  -0.7346   0.01814   0.01268  -0.0288   1.0000   0.0099
  -7.750  -0.7054   0.01733   0.01170  -0.0295   0.9985   0.0105
  -7.500  -0.6753   0.01630   0.01051  -0.0305   0.9964   0.0112
  -7.250  -0.6436   0.01567   0.00983  -0.0317   0.9944   0.0119
  -7.000  -0.6132   0.01516   0.00925  -0.0326   0.9921   0.0127
  -6.750  -0.5823   0.01466   0.00867  -0.0334   0.9893   0.0138
  -6.500  -0.5502   0.01424   0.00816  -0.0345   0.9867   0.0148
  -6.250  -0.5175   0.01373   0.00754  -0.0358   0.9844   0.0156
  -6.000  -0.4879   0.01288   0.00663  -0.0365   0.9813   0.0168
  -5.750  -0.4586   0.01243   0.00616  -0.0369   0.9769   0.0179
  -5.500  -0.4267   0.01202   0.00570  -0.0379   0.9735   0.0192
  -5.250  -0.3934   0.01160   0.00523  -0.0392   0.9708   0.0203
  -5.000  -0.3649   0.01121   0.00477  -0.0394   0.9654   0.0210
  -4.750  -0.3342   0.01075   0.00426  -0.0401   0.9606   0.0225
  -4.500  -0.3009   0.01034   0.00382  -0.0413   0.9571   0.0246
  -4.250  -0.2720   0.01003   0.00349  -0.0415   0.9498   0.0262
  -4.000  -0.2388   0.00974   0.00315  -0.0426   0.9443   0.0285
  -3.750  -0.2077   0.00944   0.00286  -0.0433   0.9367   0.0340
  -3.500  -0.1745   0.00912   0.00259  -0.0444   0.9292   0.0488
  -3.250  -0.1441   0.00881   0.00236  -0.0450   0.9189   0.0711
  -3.000  -0.1136   0.00853   0.00215  -0.0456   0.9078   0.0959
  -2.750  -0.0842   0.00829   0.00197  -0.0459   0.8952   0.1243
  -2.500  -0.0561   0.00805   0.00181  -0.0460   0.8808   0.1601
  -2.250  -0.0293   0.00777   0.00167  -0.0458   0.8650   0.2112
  -2.000  -0.0032   0.00747   0.00153  -0.0455   0.8481   0.2769
  -1.750   0.0222   0.00717   0.00143  -0.0450   0.8306   0.3516
  -1.500   0.0472   0.00688   0.00134  -0.0445   0.8130   0.4295
  -1.250   0.0718   0.00659   0.00126  -0.0439   0.7950   0.5132
  -1.000   0.0949   0.00621   0.00121  -0.0429   0.7766   0.6263
  -0.750   0.1173   0.00594   0.00124  -0.0415   0.7578   0.7289
  -0.500   0.1419   0.00592   0.00128  -0.0405   0.7384   0.7810
  -0.250   0.1672   0.00597   0.00130  -0.0397   0.7170   0.8091
   0.000   0.1921   0.00605   0.00131  -0.0389   0.6906   0.8300
   0.250   0.2168   0.00615   0.00133  -0.0380   0.6625   0.8485
   0.500   0.2419   0.00625   0.00136  -0.0372   0.6392   0.8629
   0.750   0.2675   0.00634   0.00139  -0.0365   0.6186   0.8751
   1.000   0.2925   0.00644   0.00143  -0.0358   0.5965   0.8877
   1.250   0.3172   0.00656   0.00148  -0.0349   0.5715   0.9008
   1.500   0.3419   0.00668   0.00153  -0.0341   0.5469   0.9125
   1.750   0.3669   0.00681   0.00159  -0.0333   0.5239   0.9235
   2.000   0.3922   0.00695   0.00166  -0.0326   0.4996   0.9356
   2.250   0.4190   0.00710   0.00174  -0.0323   0.4750   0.9477
   2.500   0.4473   0.00728   0.00183  -0.0323   0.4471   0.9585
   2.750   0.4772   0.00754   0.00194  -0.0329   0.4100   0.9672
   3.000   0.5082   0.00780   0.00206  -0.0337   0.3735   0.9736
   3.250   0.5389   0.00808   0.00219  -0.0345   0.3376   0.9793
   3.500   0.5695   0.00835   0.00234  -0.0353   0.3054   0.9846
   3.750   0.6014   0.00863   0.00251  -0.0364   0.2745   0.9891
   4.000   0.6318   0.00899   0.00271  -0.0372   0.2360   0.9944
   4.250   0.6627   0.00939   0.00293  -0.0382   0.1965   0.9997
   4.500   0.6835   0.00974   0.00317  -0.0370   0.1680   1.0000
   4.750   0.7051   0.01005   0.00340  -0.0359   0.1492   1.0000
   5.000   0.7279   0.01034   0.00364  -0.0350   0.1348   1.0000
   5.250   0.7512   0.01064   0.00388  -0.0342   0.1189   1.0000
   5.500   0.7747   0.01097   0.00414  -0.0335   0.1029   1.0000
   5.750   0.7983   0.01130   0.00443  -0.0328   0.0890   1.0000
   6.000   0.8223   0.01162   0.00472  -0.0322   0.0790   1.0000
   6.250   0.8463   0.01195   0.00504  -0.0316   0.0705   1.0000
   6.500   0.8700   0.01232   0.00539  -0.0309   0.0626   1.0000
   6.750   0.8942   0.01264   0.00573  -0.0304   0.0566   1.0000
   7.000   0.9176   0.01305   0.00613  -0.0297   0.0490   1.0000
   7.250   0.9412   0.01343   0.00651  -0.0291   0.0424   1.0000
   7.500   0.9646   0.01384   0.00692  -0.0284   0.0372   1.0000
   7.750   0.9878   0.01426   0.00734  -0.0278   0.0324   1.0000
   8.000   1.0106   0.01471   0.00781  -0.0270   0.0287   1.0000
   8.250   1.0338   0.01512   0.00829  -0.0264   0.0259   1.0000
   8.500   1.0558   0.01563   0.00880  -0.0256   0.0226   1.0000
   8.750   1.0783   0.01609   0.00931  -0.0248   0.0199   1.0000
   9.000   1.0998   0.01664   0.00987  -0.0240   0.0169   1.0000
   9.250   1.1213   0.01718   0.01047  -0.0231   0.0144   1.0000
   9.500   1.1417   0.01781   0.01113  -0.0221   0.0120   1.0000
   9.750   1.1617   0.01847   0.01187  -0.0211   0.0103   1.0000
  10.000   1.1811   0.01915   0.01262  -0.0199   0.0091   1.0000
  10.250   1.1993   0.01992   0.01344  -0.0187   0.0081   1.0000
  10.500   1.2163   0.02077   0.01438  -0.0173   0.0073   1.0000
  10.750   1.2338   0.02153   0.01524  -0.0159   0.0069   1.0000
  11.000   1.2499   0.02234   0.01616  -0.0145   0.0064   1.0000
  11.250   1.2644   0.02325   0.01718  -0.0128   0.0060   1.0000
  11.500   1.2768   0.02417   0.01819  -0.0108   0.0057   1.0000
  11.750   1.2858   0.02517   0.01933  -0.0084   0.0055   1.0000
  12.000   1.2921   0.02634   0.02061  -0.0057   0.0053   1.0000
  12.250   1.2934   0.02786   0.02226  -0.0027   0.0050   1.0000
  12.500   1.2957   0.02935   0.02389  -0.0001   0.0048   1.0000
  12.750   1.2984   0.03087   0.02555   0.0021   0.0048   1.0000
  13.000   1.3007   0.03250   0.02733   0.0039   0.0047   1.0000
  13.250   1.3010   0.03442   0.02939   0.0055   0.0047   1.0000
  13.500   1.2994   0.03667   0.03179   0.0067   0.0045   1.0000
  13.750   1.2962   0.03925   0.03452   0.0075   0.0045   1.0000
  14.000   1.2915   0.04223   0.03766   0.0077   0.0044   1.0000
  14.250   1.2847   0.04575   0.04134   0.0073   0.0044   1.0000
  14.500   1.2763   0.04978   0.04553   0.0062   0.0043   1.0000
  14.750   1.2651   0.05459   0.05051   0.0044   0.0043   1.0000
  15.000   1.2537   0.05984   0.05592   0.0019   0.0042   1.0000
  15.250   1.2383   0.06610   0.06236  -0.0015   0.0042   1.0000
  15.500   1.2209   0.07314   0.06956  -0.0054   0.0042   1.0000
  15.750   1.2008   0.08104   0.07763  -0.0100   0.0043   1.0000
  16.000   1.1805   0.08941   0.08615  -0.0148   0.0043   1.0000
  16.250   1.1566   0.09881   0.09570  -0.0202   0.0043   1.0000
  16.500   1.1313   0.10890   0.10593  -0.0260   0.0044   1.0000
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