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RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: RG 14 10% AIRFOIL (rg1410-il)
Reynolds number: 200,000
Max Cl/Cd: 58.15 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-rg1410-il-200000-n5.txt
Download as CSV file: xf-rg1410-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RG 14 10% 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5577   0.09319   0.08942  -0.0270   1.0000   0.0185
 -10.750  -0.7066   0.05313   0.04916  -0.0549   1.0000   0.0163
 -10.500  -0.7495   0.04714   0.04285  -0.0545   1.0000   0.0161
 -10.250  -0.7689   0.04399   0.03951  -0.0514   1.0000   0.0161
 -10.000  -0.7699   0.04217   0.03757  -0.0493   1.0000   0.0164
  -9.750  -0.7682   0.04038   0.03564  -0.0472   1.0000   0.0168
  -9.500  -0.7688   0.03791   0.03293  -0.0448   1.0000   0.0172
  -9.250  -0.7671   0.03538   0.03010  -0.0423   1.0000   0.0176
  -9.000  -0.7620   0.03304   0.02747  -0.0399   1.0000   0.0181
  -8.750  -0.7548   0.03076   0.02484  -0.0375   1.0000   0.0188
  -8.500  -0.7447   0.02870   0.02243  -0.0353   1.0000   0.0195
  -8.250  -0.7316   0.02713   0.02050  -0.0332   1.0000   0.0204
  -8.000  -0.7181   0.02548   0.01867  -0.0313   1.0000   0.0213
  -7.750  -0.7019   0.02446   0.01755  -0.0297   1.0000   0.0221
  -7.500  -0.6852   0.02343   0.01640  -0.0281   1.0000   0.0230
  -7.250  -0.6679   0.02236   0.01517  -0.0264   1.0000   0.0239
  -7.000  -0.6500   0.02139   0.01404  -0.0248   1.0000   0.0249
  -6.750  -0.6314   0.02061   0.01309  -0.0233   1.0000   0.0263
  -6.500  -0.6132   0.01965   0.01201  -0.0217   1.0000   0.0273
  -6.250  -0.5821   0.01858   0.01087  -0.0229   0.9969   0.0287
  -6.000  -0.5492   0.01780   0.01002  -0.0243   0.9936   0.0302
  -5.750  -0.5173   0.01711   0.00925  -0.0255   0.9894   0.0321
  -5.500  -0.4836   0.01653   0.00856  -0.0269   0.9854   0.0346
  -5.250  -0.4516   0.01574   0.00774  -0.0281   0.9812   0.0373
  -5.000  -0.4203   0.01518   0.00714  -0.0290   0.9758   0.0407
  -4.750  -0.3860   0.01467   0.00656  -0.0305   0.9716   0.0454
  -4.500  -0.3555   0.01416   0.00607  -0.0312   0.9658   0.0546
  -4.250  -0.3230   0.01369   0.00562  -0.0323   0.9604   0.0687
  -4.000  -0.2877   0.01322   0.00523  -0.0341   0.9567   0.0880
  -3.750  -0.2591   0.01284   0.00491  -0.0343   0.9490   0.1095
  -3.500  -0.2249   0.01237   0.00459  -0.0359   0.9443   0.1455
  -3.250  -0.1947   0.01187   0.00433  -0.0366   0.9374   0.1990
  -3.000  -0.1622   0.01138   0.00407  -0.0378   0.9309   0.2580
  -2.750  -0.1316   0.01092   0.00383  -0.0385   0.9231   0.3199
  -2.500  -0.1003   0.01044   0.00361  -0.0393   0.9154   0.3941
  -2.250  -0.0722   0.00997   0.00344  -0.0394   0.9058   0.4761
  -2.000  -0.0426   0.00945   0.00330  -0.0396   0.8976   0.5761
  -1.750  -0.0173   0.00905   0.00331  -0.0386   0.8865   0.6794
  -1.500   0.0095   0.00890   0.00339  -0.0376   0.8752   0.7603
  -1.250   0.0382   0.00887   0.00337  -0.0371   0.8635   0.8036
  -1.000   0.0669   0.00885   0.00333  -0.0367   0.8507   0.8315
  -0.750   0.0947   0.00885   0.00329  -0.0361   0.8368   0.8543
  -0.500   0.1223   0.00887   0.00326  -0.0355   0.8220   0.8733
  -0.250   0.1501   0.00889   0.00323  -0.0349   0.8064   0.8894
   0.000   0.1784   0.00893   0.00321  -0.0345   0.7902   0.9036
   0.250   0.2076   0.00898   0.00319  -0.0343   0.7730   0.9169
   0.500   0.2376   0.00904   0.00317  -0.0344   0.7551   0.9292
   0.750   0.2696   0.00912   0.00316  -0.0348   0.7360   0.9391
   1.000   0.3031   0.00920   0.00315  -0.0357   0.7138   0.9473
   1.250   0.3347   0.00931   0.00314  -0.0363   0.6900   0.9569
   1.500   0.3715   0.00943   0.00315  -0.0379   0.6641   0.9632
   1.750   0.4035   0.00955   0.00318  -0.0387   0.6389   0.9707
   2.000   0.4403   0.00968   0.00319  -0.0406   0.6120   0.9752
   2.250   0.4731   0.00984   0.00323  -0.0416   0.5843   0.9812
   2.750   0.5396   0.01015   0.00335  -0.0441   0.5312   0.9910
   3.000   0.5719   0.01033   0.00344  -0.0452   0.5046   0.9961
   3.250   0.6015   0.01053   0.00355  -0.0458   0.4765   1.0000
   3.500   0.6191   0.01075   0.00367  -0.0439   0.4473   1.0000
   3.750   0.6365   0.01101   0.00380  -0.0419   0.4173   1.0000
   4.000   0.6542   0.01127   0.00398  -0.0400   0.3889   1.0000
   4.250   0.6722   0.01156   0.00416  -0.0382   0.3603   1.0000
   4.500   0.6905   0.01188   0.00437  -0.0365   0.3315   1.0000
   4.750   0.7091   0.01223   0.00461  -0.0348   0.3017   1.0000
   5.000   0.7280   0.01262   0.00487  -0.0332   0.2698   1.0000
   5.250   0.7474   0.01305   0.00519  -0.0318   0.2387   1.0000
   5.500   0.7675   0.01350   0.00553  -0.0305   0.2100   1.0000
   5.750   0.7877   0.01398   0.00589  -0.0293   0.1835   1.0000
   6.000   0.8080   0.01449   0.00630  -0.0281   0.1635   1.0000
   6.250   0.8288   0.01499   0.00676  -0.0270   0.1482   1.0000
   6.500   0.8501   0.01547   0.00721  -0.0260   0.1346   1.0000
   6.750   0.8719   0.01592   0.00767  -0.0250   0.1215   1.0000
   7.000   0.8936   0.01638   0.00813  -0.0241   0.1088   1.0000
   7.250   0.9150   0.01687   0.00862  -0.0231   0.0974   1.0000
   7.500   0.9359   0.01740   0.00917  -0.0221   0.0880   1.0000
   7.750   0.9559   0.01802   0.00976  -0.0210   0.0798   1.0000
   8.000   0.9768   0.01856   0.01037  -0.0200   0.0731   1.0000
   8.250   0.9956   0.01926   0.01107  -0.0187   0.0674   1.0000
   8.500   1.0160   0.01983   0.01176  -0.0177   0.0619   1.0000
   8.750   1.0339   0.02058   0.01252  -0.0163   0.0568   1.0000
   9.000   1.0527   0.02126   0.01330  -0.0151   0.0529   1.0000
   9.250   1.0710   0.02196   0.01408  -0.0138   0.0488   1.0000
   9.500   1.0865   0.02284   0.01496  -0.0122   0.0449   1.0000
   9.750   1.1052   0.02346   0.01572  -0.0110   0.0408   1.0000
  10.000   1.1211   0.02423   0.01655  -0.0096   0.0372   1.0000
  10.250   1.1345   0.02513   0.01752  -0.0078   0.0344   1.0000
  10.500   1.1483   0.02591   0.01843  -0.0059   0.0316   1.0000
  10.750   1.1598   0.02681   0.01941  -0.0039   0.0294   1.0000
  11.000   1.1677   0.02797   0.02062  -0.0016   0.0272   1.0000
  11.250   1.1792   0.02894   0.02174   0.0002   0.0249   1.0000
  11.500   1.1880   0.03006   0.02297   0.0021   0.0230   1.0000
  11.750   1.1921   0.03153   0.02452   0.0042   0.0214   1.0000
  12.000   1.1977   0.03304   0.02619   0.0060   0.0202   1.0000
  12.250   1.2019   0.03468   0.02799   0.0077   0.0190   1.0000
  12.500   1.2051   0.03645   0.02989   0.0091   0.0180   1.0000
  12.750   1.2067   0.03843   0.03198   0.0102   0.0171   1.0000
  13.000   1.2037   0.04096   0.03460   0.0111   0.0164   1.0000
  13.250   1.2032   0.04348   0.03731   0.0116   0.0156   1.0000
  13.500   1.2012   0.04631   0.04033   0.0118   0.0150   1.0000
  13.750   1.1979   0.04944   0.04363   0.0115   0.0143   1.0000
  14.000   1.1928   0.05298   0.04733   0.0108   0.0140   1.0000
  14.250   1.1865   0.05690   0.05140   0.0095   0.0135   1.0000
  14.500   1.1789   0.06123   0.05588   0.0078   0.0132   1.0000
  14.750   1.1695   0.06608   0.06089   0.0056   0.0130   1.0000
  15.000   1.1578   0.07154   0.06650   0.0029   0.0129   1.0000
  15.250   1.1447   0.07754   0.07266  -0.0003   0.0127   1.0000
  15.500   1.1301   0.08409   0.07935  -0.0039   0.0126   1.0000
  15.750   1.1145   0.09114   0.08656  -0.0078   0.0126   1.0000
  16.000   1.0974   0.09879   0.09437  -0.0122   0.0125   1.0000
  16.250   1.0793   0.10697   0.10271  -0.0169   0.0125   1.0000
  16.500   1.0600   0.11581   0.11171  -0.0220   0.0126   1.0000
  16.750   1.0382   0.12557   0.12163  -0.0276   0.0126   1.0000
  17.000   1.0097   0.13759   0.13384  -0.0345   0.0128   1.0000
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