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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 100,000
Max Cl/Cd: 46.55 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1495-il-100000-n5.txt
Download as CSV file: xf-rg1495-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 9.5% 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5317   0.09029   0.08509  -0.0276   1.0000   0.0295
  -9.750  -0.5390   0.08465   0.07952  -0.0305   1.0000   0.0292
  -9.500  -0.5504   0.07805   0.07299  -0.0345   1.0000   0.0291
  -9.250  -0.5675   0.06985   0.06485  -0.0410   1.0000   0.0284
  -9.000  -0.5933   0.06335   0.05831  -0.0437   1.0000   0.0279
  -8.750  -0.6147   0.05792   0.05278  -0.0439   1.0000   0.0277
  -8.500  -0.6298   0.05299   0.04763  -0.0431   1.0000   0.0277
  -8.250  -0.6382   0.04869   0.04304  -0.0416   1.0000   0.0281
  -8.000  -0.6415   0.04471   0.03869  -0.0398   1.0000   0.0291
  -7.750  -0.6411   0.04087   0.03438  -0.0377   1.0000   0.0303
  -7.500  -0.6364   0.03732   0.03025  -0.0355   1.0000   0.0312
  -7.250  -0.6270   0.03430   0.02670  -0.0334   1.0000   0.0317
  -7.000  -0.6147   0.03154   0.02356  -0.0315   1.0000   0.0325
  -6.750  -0.5993   0.02971   0.02160  -0.0301   1.0000   0.0338
  -6.500  -0.5822   0.02849   0.02023  -0.0287   1.0000   0.0359
  -6.250  -0.5642   0.02702   0.01849  -0.0272   1.0000   0.0381
  -6.000  -0.5451   0.02537   0.01654  -0.0256   1.0000   0.0395
  -5.750  -0.5252   0.02393   0.01481  -0.0242   1.0000   0.0410
  -5.500  -0.5055   0.02261   0.01335  -0.0228   1.0000   0.0426
  -5.250  -0.4864   0.02169   0.01245  -0.0215   1.0000   0.0459
  -5.000  -0.4664   0.02086   0.01153  -0.0202   1.0000   0.0493
  -4.750  -0.4463   0.01999   0.01053  -0.0188   1.0000   0.0523
  -4.500  -0.4270   0.01910   0.00962  -0.0174   1.0000   0.0558
  -4.250  -0.4072   0.01843   0.00890  -0.0161   1.0000   0.0613
  -4.000  -0.3872   0.01782   0.00829  -0.0149   1.0000   0.0705
  -3.750  -0.3625   0.01722   0.00773  -0.0147   0.9984   0.0863
  -3.500  -0.3270   0.01659   0.00722  -0.0167   0.9926   0.1159
  -3.250  -0.2924   0.01597   0.00684  -0.0186   0.9862   0.1695
  -3.000  -0.2589   0.01531   0.00657  -0.0203   0.9797   0.2509
  -2.750  -0.2258   0.01465   0.00634  -0.0219   0.9726   0.3528
  -2.500  -0.1953   0.01398   0.00618  -0.0227   0.9649   0.4759
  -2.250  -0.1649   0.01335   0.00620  -0.0228   0.9580   0.6348
  -2.000  -0.1378   0.01319   0.00644  -0.0213   0.9494   0.7705
  -1.750  -0.1021   0.01322   0.00648  -0.0218   0.9429   0.8428
  -1.500  -0.0682   0.01326   0.00646  -0.0222   0.9340   0.8865
  -1.250  -0.0205   0.01331   0.00641  -0.0254   0.9294   0.9199
  -1.000   0.0285   0.01334   0.00633  -0.0292   0.9228   0.9454
  -0.750   0.0841   0.01332   0.00621  -0.0344   0.9173   0.9634
  -0.500   0.1417   0.01324   0.00602  -0.0403   0.9112   0.9771
  -0.250   0.1961   0.01309   0.00580  -0.0456   0.9021   0.9889
   0.000   0.2478   0.01292   0.00557  -0.0505   0.8907   0.9989
   0.250   0.2831   0.01277   0.00537  -0.0520   0.8749   1.0000
   0.500   0.3150   0.01264   0.00519  -0.0527   0.8579   1.0000
   0.750   0.3449   0.01254   0.00504  -0.0530   0.8397   1.0000
   1.000   0.3710   0.01248   0.00495  -0.0525   0.8194   1.0000
   1.250   0.3975   0.01244   0.00485  -0.0520   0.7993   1.0000
   1.500   0.4221   0.01244   0.00482  -0.0512   0.7781   1.0000
   1.750   0.4461   0.01246   0.00478  -0.0502   0.7559   1.0000
   2.000   0.4689   0.01251   0.00477  -0.0490   0.7309   1.0000
   2.250   0.4912   0.01258   0.00476  -0.0476   0.7045   1.0000
   2.500   0.5128   0.01269   0.00480  -0.0461   0.6767   1.0000
   2.750   0.5339   0.01284   0.00484  -0.0445   0.6476   1.0000
   3.000   0.5548   0.01301   0.00492  -0.0429   0.6192   1.0000
   3.500   0.5967   0.01343   0.00523  -0.0399   0.5665   1.0000
   3.750   0.6177   0.01367   0.00541  -0.0384   0.5400   1.0000
   4.000   0.6383   0.01395   0.00561  -0.0369   0.5105   1.0000
   4.250   0.6585   0.01427   0.00582  -0.0353   0.4780   1.0000
   4.500   0.6786   0.01462   0.00609  -0.0338   0.4431   1.0000
   4.750   0.6987   0.01501   0.00637  -0.0323   0.4068   1.0000
   5.000   0.7186   0.01545   0.00669  -0.0308   0.3691   1.0000
   5.250   0.7382   0.01595   0.00705  -0.0294   0.3303   1.0000
   5.500   0.7579   0.01650   0.00749  -0.0280   0.2908   1.0000
   5.750   0.7773   0.01711   0.00797  -0.0267   0.2528   1.0000
   6.000   0.7967   0.01779   0.00850  -0.0254   0.2186   1.0000
   6.250   0.8161   0.01849   0.00910  -0.0241   0.1901   1.0000
   6.500   0.8355   0.01923   0.00975  -0.0229   0.1679   1.0000
   6.750   0.8547   0.02000   0.01051  -0.0217   0.1496   1.0000
   7.000   0.8739   0.02080   0.01129  -0.0204   0.1341   1.0000
   7.250   0.8932   0.02158   0.01210  -0.0192   0.1201   1.0000
   7.500   0.9126   0.02236   0.01292  -0.0181   0.1078   1.0000
   7.750   0.9314   0.02320   0.01380  -0.0168   0.0977   1.0000
   8.000   0.9493   0.02411   0.01472  -0.0155   0.0889   1.0000
   8.250   0.9678   0.02502   0.01575  -0.0142   0.0811   1.0000
   8.500   0.9846   0.02611   0.01688  -0.0128   0.0750   1.0000
   8.750   1.0022   0.02710   0.01798  -0.0115   0.0682   1.0000
   9.000   1.0178   0.02837   0.01929  -0.0101   0.0635   1.0000
   9.250   1.0351   0.02960   0.02071  -0.0087   0.0587   1.0000
   9.500   1.0494   0.03080   0.02198  -0.0073   0.0542   1.0000
   9.750   1.0646   0.03221   0.02360  -0.0058   0.0498   1.0000
  10.000   1.0780   0.03345   0.02500  -0.0043   0.0455   1.0000
  10.250   1.0877   0.03491   0.02645  -0.0026   0.0421   1.0000
  10.500   1.0983   0.03642   0.02831  -0.0006   0.0384   1.0000
  10.750   1.1053   0.03782   0.02987   0.0015   0.0355   1.0000
  11.000   1.1094   0.03937   0.03148   0.0036   0.0334   1.0000
  11.250   1.1129   0.04168   0.03397   0.0056   0.0317   1.0000
  11.500   1.1142   0.04410   0.03673   0.0076   0.0300   1.0000
  11.750   1.1129   0.04649   0.03941   0.0093   0.0284   1.0000
  12.000   1.1107   0.04867   0.04174   0.0105   0.0268   1.0000
  12.250   1.1076   0.05118   0.04437   0.0113   0.0258   1.0000
  12.500   1.1032   0.05397   0.04725   0.0116   0.0250   1.0000
  12.750   1.0933   0.05788   0.05137   0.0114   0.0244   1.0000
  13.000   1.0804   0.06248   0.05626   0.0104   0.0240   1.0000
  13.250   1.0649   0.06777   0.06182   0.0085   0.0238   1.0000
  13.500   1.0475   0.07378   0.06807   0.0055   0.0237   1.0000
  13.750   1.0276   0.08074   0.07524   0.0016   0.0237   1.0000
  14.000   1.0053   0.08878   0.08348  -0.0035   0.0238   1.0000
  14.250   0.9811   0.09794   0.09281  -0.0095   0.0240   1.0000
  14.500   0.9561   0.10804   0.10303  -0.0159   0.0244   1.0000
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