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RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG 14 9.5% AIRFOIL (rg1495-il)
Reynolds number: 200,000
Max Cl/Cd: 57.91 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1495-il-200000-n5.txt
Download as CSV file: xf-rg1495-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5691   0.08176   0.07813  -0.0304   1.0000   0.0168
 -10.000  -0.5896   0.07308   0.06952  -0.0356   1.0000   0.0162
  -9.750  -0.6544   0.05455   0.05087  -0.0491   1.0000   0.0151
  -9.500  -0.6932   0.04833   0.04439  -0.0476   1.0000   0.0149
  -9.250  -0.7139   0.04322   0.03894  -0.0454   1.0000   0.0149
  -9.000  -0.7203   0.03958   0.03497  -0.0432   1.0000   0.0153
  -8.750  -0.7212   0.03628   0.03130  -0.0408   1.0000   0.0159
  -8.500  -0.7178   0.03330   0.02788  -0.0384   1.0000   0.0169
  -8.250  -0.7110   0.03054   0.02460  -0.0360   1.0000   0.0177
  -8.000  -0.7012   0.02805   0.02171  -0.0337   1.0000   0.0182
  -7.750  -0.6878   0.02622   0.01970  -0.0320   1.0000   0.0189
  -7.500  -0.6717   0.02497   0.01831  -0.0304   1.0000   0.0196
  -7.250  -0.6547   0.02378   0.01695  -0.0288   1.0000   0.0205
  -7.000  -0.6367   0.02284   0.01582  -0.0273   1.0000   0.0219
  -6.750  -0.6182   0.02181   0.01455  -0.0258   1.0000   0.0232
  -6.500  -0.5992   0.02082   0.01335  -0.0242   1.0000   0.0240
  -6.250  -0.5812   0.01943   0.01185  -0.0227   1.0000   0.0250
  -6.000  -0.5611   0.01858   0.01096  -0.0216   0.9998   0.0262
  -5.750  -0.5276   0.01791   0.01023  -0.0231   0.9964   0.0284
  -5.500  -0.4945   0.01712   0.00930  -0.0245   0.9929   0.0302
  -5.250  -0.4620   0.01638   0.00843  -0.0256   0.9887   0.0317
  -5.000  -0.4289   0.01553   0.00755  -0.0270   0.9847   0.0338
  -4.750  -0.3967   0.01500   0.00699  -0.0282   0.9800   0.0374
  -4.500  -0.3641   0.01451   0.00641  -0.0293   0.9747   0.0415
  -4.250  -0.3295   0.01391   0.00582  -0.0309   0.9708   0.0483
  -4.000  -0.2996   0.01343   0.00535  -0.0314   0.9641   0.0595
  -3.750  -0.2658   0.01299   0.00496  -0.0328   0.9591   0.0796
  -3.500  -0.2337   0.01253   0.00462  -0.0339   0.9534   0.1095
  -3.250  -0.2019   0.01210   0.00433  -0.0349   0.9469   0.1457
  -3.000  -0.1667   0.01152   0.00406  -0.0367   0.9426   0.2140
  -2.750  -0.1388   0.01098   0.00382  -0.0370   0.9335   0.2904
  -2.500  -0.1055   0.01045   0.00359  -0.0383   0.9275   0.3725
  -2.250  -0.0773   0.00997   0.00341  -0.0385   0.9177   0.4559
  -2.000  -0.0488   0.00943   0.00327  -0.0385   0.9088   0.5621
  -1.750  -0.0211   0.00894   0.00326  -0.0380   0.8999   0.6831
  -1.500   0.0052   0.00878   0.00334  -0.0369   0.8886   0.7711
  -1.250   0.0340   0.00874   0.00332  -0.0365   0.8771   0.8152
  -1.000   0.0633   0.00871   0.00326  -0.0361   0.8647   0.8438
  -0.750   0.0921   0.00869   0.00321  -0.0357   0.8512   0.8667
  -0.500   0.1207   0.00870   0.00317  -0.0353   0.8366   0.8862
  -0.250   0.1500   0.00872   0.00313  -0.0351   0.8210   0.9023
   0.000   0.1801   0.00874   0.00309  -0.0350   0.8045   0.9165
   0.250   0.2113   0.00879   0.00306  -0.0353   0.7874   0.9298
   0.500   0.2431   0.00885   0.00303  -0.0357   0.7692   0.9420
   0.750   0.2792   0.00891   0.00302  -0.0371   0.7496   0.9503
   1.000   0.3134   0.00899   0.00300  -0.0382   0.7265   0.9592
   1.250   0.3488   0.00909   0.00298  -0.0395   0.6999   0.9672
   1.500   0.3846   0.00920   0.00297  -0.0411   0.6720   0.9735
   1.750   0.4200   0.00932   0.00298  -0.0426   0.6463   0.9796
   2.000   0.4536   0.00945   0.00299  -0.0438   0.6175   0.9852
   2.250   0.4872   0.00960   0.00301  -0.0451   0.5876   0.9904
   2.500   0.5198   0.00975   0.00307  -0.0462   0.5595   0.9957
   2.750   0.5506   0.00992   0.00314  -0.0470   0.5331   1.0000
   3.000   0.5698   0.01010   0.00324  -0.0453   0.5078   1.0000
   3.250   0.5884   0.01031   0.00336  -0.0436   0.4793   1.0000
   3.500   0.6066   0.01056   0.00349  -0.0417   0.4479   1.0000
   3.750   0.6249   0.01084   0.00364  -0.0399   0.4166   1.0000
   4.000   0.6439   0.01113   0.00381  -0.0383   0.3855   1.0000
   4.250   0.6631   0.01145   0.00403  -0.0367   0.3535   1.0000
   4.500   0.6827   0.01179   0.00426  -0.0352   0.3215   1.0000
   4.750   0.7026   0.01218   0.00452  -0.0338   0.2886   1.0000
   5.000   0.7228   0.01262   0.00482  -0.0325   0.2530   1.0000
   5.250   0.7433   0.01309   0.00515  -0.0313   0.2188   1.0000
   5.500   0.7641   0.01358   0.00553  -0.0302   0.1888   1.0000
   5.750   0.7852   0.01409   0.00593  -0.0291   0.1654   1.0000
   6.000   0.8065   0.01459   0.00637  -0.0281   0.1477   1.0000
   6.250   0.8283   0.01508   0.00683  -0.0272   0.1323   1.0000
   6.500   0.8503   0.01556   0.00731  -0.0263   0.1175   1.0000
   6.750   0.8723   0.01604   0.00777  -0.0254   0.1039   1.0000
   7.000   0.8940   0.01655   0.00827  -0.0246   0.0918   1.0000
   7.250   0.9156   0.01707   0.00882  -0.0236   0.0826   1.0000
   7.500   0.9365   0.01767   0.00943  -0.0226   0.0747   1.0000
   7.750   0.9573   0.01828   0.01005  -0.0216   0.0671   1.0000
   8.000   0.9777   0.01891   0.01077  -0.0206   0.0614   1.0000
   8.250   0.9978   0.01957   0.01149  -0.0195   0.0561   1.0000
   8.500   1.0165   0.02034   0.01231  -0.0182   0.0517   1.0000
   8.750   1.0366   0.02097   0.01305  -0.0172   0.0469   1.0000
   9.000   1.0541   0.02182   0.01387  -0.0159   0.0420   1.0000
   9.250   1.0741   0.02241   0.01463  -0.0148   0.0379   1.0000
   9.500   1.0919   0.02317   0.01544  -0.0136   0.0341   1.0000
   9.750   1.1076   0.02410   0.01645  -0.0121   0.0312   1.0000
  10.000   1.1246   0.02489   0.01737  -0.0107   0.0281   1.0000
  10.250   1.1385   0.02584   0.01836  -0.0091   0.0251   1.0000
  10.500   1.1510   0.02686   0.01952  -0.0072   0.0229   1.0000
  10.750   1.1616   0.02790   0.02068  -0.0050   0.0210   1.0000
  11.000   1.1698   0.02907   0.02196  -0.0028   0.0194   1.0000
  11.250   1.1746   0.03054   0.02353  -0.0003   0.0182   1.0000
  11.500   1.1823   0.03185   0.02502   0.0017   0.0168   1.0000
  11.750   1.1876   0.03333   0.02665   0.0037   0.0157   1.0000
  12.000   1.1924   0.03485   0.02827   0.0053   0.0146   1.0000
  12.250   1.1920   0.03685   0.03036   0.0070   0.0139   1.0000
  12.500   1.1926   0.03898   0.03267   0.0083   0.0134   1.0000
  12.750   1.1911   0.04146   0.03535   0.0093   0.0130   1.0000
  13.000   1.1885   0.04419   0.03828   0.0099   0.0126   1.0000
  13.250   1.1841   0.04731   0.04158   0.0101   0.0122   1.0000
  13.500   1.1784   0.05078   0.04523   0.0097   0.0120   1.0000
  13.750   1.1715   0.05465   0.04928   0.0088   0.0117   1.0000
  14.000   1.1628   0.05902   0.05384   0.0072   0.0115   1.0000
  14.250   1.1525   0.06395   0.05894   0.0051   0.0113   1.0000
  14.500   1.1407   0.06940   0.06457   0.0023   0.0112   1.0000
  14.750   1.1267   0.07556   0.07091  -0.0010   0.0111   1.0000
  15.000   1.1109   0.08241   0.07794  -0.0049   0.0111   1.0000
  15.250   1.0922   0.09019   0.08591  -0.0094   0.0112   1.0000
  15.500   1.0716   0.09890   0.09481  -0.0146   0.0111   1.0000
  15.750   1.0468   0.10898   0.10508  -0.0206   0.0113   1.0000
  16.000   1.0164   0.12113   0.11742  -0.0278   0.0115   1.0000
  16.250   0.9692   0.13867   0.13516  -0.0378   0.0121   1.0000
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