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TsAGI R-3a (12%) (tsagi-r-3a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: TsAGI R-3a (12%) (tsagi-r-3a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.09 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-tsagi-r-3a-il-1000000.txt
Download as CSV file: xf-tsagi-r-3a-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: TsAGI R-3a (12%)                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3941   0.08891   0.08748  -0.0018   1.0045   0.0188
  -9.500  -0.3907   0.08547   0.08405  -0.0028   0.9773   0.0189
  -9.250  -0.3929   0.08284   0.08097  -0.0021   0.8061   0.0190
  -9.000  -0.3918   0.07959   0.07742  -0.0030   0.7201   0.0191
  -8.750  -0.3918   0.07568   0.07333  -0.0045   0.6645   0.0193
  -8.500  -0.3929   0.07151   0.06902  -0.0064   0.6201   0.0194
  -8.250  -0.6177   0.02871   0.02573  -0.0337   1.0045   0.0153
  -8.000  -0.6032   0.02231   0.01862  -0.0347   0.9707   0.0145
  -7.750  -0.5854   0.01982   0.01563  -0.0333   0.9028   0.0144
  -7.500  -0.5665   0.01871   0.01407  -0.0315   0.8232   0.0145
  -7.250  -0.5444   0.01764   0.01251  -0.0305   0.7381   0.0145
  -7.000  -0.5206   0.01669   0.01109  -0.0298   0.6551   0.0145
  -6.750  -0.4954   0.01593   0.00998  -0.0293   0.5875   0.0146
  -6.500  -0.4694   0.01528   0.00905  -0.0289   0.5422   0.0147
  -6.250  -0.4429   0.01469   0.00825  -0.0285   0.5096   0.0149
  -6.000  -0.4160   0.01416   0.00756  -0.0282   0.4863   0.0151
  -5.750  -0.3888   0.01369   0.00696  -0.0278   0.4691   0.0153
  -5.500  -0.3613   0.01329   0.00645  -0.0275   0.4574   0.0155
  -5.250  -0.3335   0.01295   0.00602  -0.0273   0.4497   0.0157
  -5.000  -0.3070   0.01224   0.00521  -0.0269   0.4429   0.0160
  -4.750  -0.2796   0.01181   0.00472  -0.0266   0.4374   0.0164
  -4.500  -0.2517   0.01147   0.00436  -0.0264   0.4331   0.0167
  -4.250  -0.2237   0.01120   0.00405  -0.0262   0.4287   0.0171
  -4.000  -0.1955   0.01097   0.00377  -0.0260   0.4247   0.0175
  -3.750  -0.1673   0.01075   0.00351  -0.0258   0.4207   0.0180
  -3.500  -0.1388   0.01053   0.00326  -0.0256   0.4178   0.0184
  -3.250  -0.1105   0.01028   0.00299  -0.0254   0.4145   0.0191
  -3.000  -0.0820   0.01010   0.00279  -0.0253   0.4112   0.0203
  -2.750  -0.0535   0.00998   0.00264  -0.0251   0.4074   0.0217
  -2.500  -0.0250   0.00986   0.00252  -0.0250   0.4035   0.0244
  -2.250   0.0038   0.00971   0.00240  -0.0249   0.4010   0.0298
  -2.000   0.0325   0.00957   0.00229  -0.0247   0.3976   0.0376
  -1.750   0.0611   0.00946   0.00218  -0.0247   0.3938   0.0436
  -1.500   0.0898   0.00937   0.00209  -0.0246   0.3900   0.0499
  -1.250   0.1183   0.00926   0.00201  -0.0245   0.3860   0.0624
  -1.000   0.1467   0.00903   0.00194  -0.0244   0.3831   0.1014
  -0.750   0.1753   0.00886   0.00188  -0.0244   0.3791   0.1327
  -0.500   0.2038   0.00871   0.00183  -0.0243   0.3744   0.1723
  -0.250   0.2317   0.00848   0.00179  -0.0243   0.3692   0.2441
   0.000   0.2592   0.00801   0.00174  -0.0243   0.3647   0.3779
   0.250   0.2850   0.00736   0.00172  -0.0240   0.3584   0.5888
   0.500   0.3100   0.00690   0.00174  -0.0232   0.3514   0.7503
   0.750   0.3339   0.00661   0.00178  -0.0220   0.3427   0.8609
   1.000   0.3589   0.00654   0.00180  -0.0208   0.3312   0.9206
   1.250   0.3905   0.00661   0.00182  -0.0212   0.3110   0.9591
   1.500   0.4297   0.00681   0.00187  -0.0235   0.2869   0.9811
   1.750   0.4700   0.00702   0.00195  -0.0260   0.2727   0.9914
   2.000   0.5066   0.00719   0.00203  -0.0277   0.2647   0.9955
   2.250   0.5327   0.00734   0.00211  -0.0273   0.2583   0.9955
   2.500   0.5593   0.00743   0.00217  -0.0269   0.2545   0.9955
   2.750   0.5859   0.00756   0.00225  -0.0265   0.2503   0.9955
   3.000   0.6124   0.00772   0.00236  -0.0261   0.2458   0.9955
   3.250   0.6392   0.00786   0.00246  -0.0257   0.2423   0.9955
   3.500   0.6664   0.00795   0.00254  -0.0255   0.2398   0.9955
   3.750   0.6937   0.00806   0.00263  -0.0252   0.2372   0.9955
   4.000   0.7209   0.00820   0.00273  -0.0250   0.2344   0.9955
   4.250   0.7481   0.00836   0.00286  -0.0248   0.2313   0.9955
   4.500   0.7751   0.00856   0.00302  -0.0245   0.2279   0.9955
   4.750   0.8027   0.00866   0.00313  -0.0244   0.2266   0.9955
   5.000   0.8304   0.00877   0.00324  -0.0243   0.2251   0.9955
   5.250   0.8580   0.00889   0.00337  -0.0241   0.2234   0.9955
   5.500   0.8855   0.00903   0.00349  -0.0240   0.2214   0.9955
   5.750   0.9129   0.00918   0.00363  -0.0239   0.2190   0.9955
   6.000   0.9400   0.00936   0.00380  -0.0237   0.2163   0.9955
   6.250   0.9667   0.00961   0.00402  -0.0235   0.2130   0.9955
   6.500   0.9942   0.00974   0.00416  -0.0234   0.2116   0.9955
   6.750   1.0218   0.00985   0.00430  -0.0234   0.2101   0.9955
   7.000   1.0493   0.00998   0.00445  -0.0233   0.2081   0.9955
   7.250   1.0766   0.01012   0.00460  -0.0232   0.2059   0.9955
   7.500   1.1036   0.01029   0.00477  -0.0231   0.2033   0.9955
   7.750   1.1302   0.01052   0.00499  -0.0229   0.2000   0.9955
   8.000   1.1570   0.01071   0.00518  -0.0228   0.1967   0.9955
   8.250   1.1845   0.01080   0.00531  -0.0228   0.1940   0.9955
   8.500   1.2116   0.01095   0.00546  -0.0227   0.1902   0.9955
   8.750   1.2380   0.01117   0.00567  -0.0225   0.1857   0.9955
   9.000   1.2646   0.01135   0.00587  -0.0224   0.1818   0.9955
   9.250   1.2913   0.01152   0.00603  -0.0223   0.1761   0.9955
   9.500   1.3171   0.01179   0.00627  -0.0221   0.1696   0.9955
   9.750   1.3431   0.01201   0.00650  -0.0220   0.1630   0.9955
  10.000   1.3682   0.01234   0.00679  -0.0217   0.1551   0.9955
  10.250   1.3925   0.01273   0.00714  -0.0214   0.1467   0.9955
  10.500   1.4170   0.01310   0.00749  -0.0211   0.1406   0.9955
  10.750   1.4406   0.01353   0.00790  -0.0207   0.1350   0.9955
  11.000   1.4648   0.01389   0.00828  -0.0204   0.1312   0.9955
  11.250   1.4883   0.01429   0.00869  -0.0200   0.1270   0.9955
  11.500   1.5106   0.01479   0.00918  -0.0195   0.1223   0.9955
  11.750   1.5344   0.01512   0.00956  -0.0191   0.1199   0.9955
  12.000   1.5576   0.01550   0.00997  -0.0186   0.1169   0.9955
  12.250   1.5793   0.01598   0.01046  -0.0181   0.1133   0.9955
  12.500   1.6007   0.01648   0.01098  -0.0175   0.1098   0.9955
  12.750   1.6230   0.01686   0.01140  -0.0169   0.1068   0.9955
  13.000   1.6428   0.01743   0.01196  -0.0162   0.1021   0.9955
  13.250   1.6626   0.01796   0.01253  -0.0154   0.0980   0.9955
  13.500   1.6813   0.01855   0.01312  -0.0146   0.0932   0.9955
  13.750   1.6982   0.01923   0.01381  -0.0135   0.0881   0.9955
  14.000   1.7118   0.02009   0.01465  -0.0122   0.0808   0.9955
  14.250   1.7196   0.02116   0.01568  -0.0101   0.0715   0.9955
  14.500   1.7138   0.02289   0.01735  -0.0068   0.0581   0.9955
  14.750   1.7006   0.02550   0.01994  -0.0042   0.0464   0.9955
  15.000   1.6887   0.02873   0.02321  -0.0034   0.0398   0.9955
  15.250   1.6790   0.03255   0.02712  -0.0043   0.0357   0.9955
  15.500   1.6673   0.03725   0.03192  -0.0063   0.0325   0.9955
  15.750   1.6509   0.04285   0.03765  -0.0088   0.0300   0.9955
  16.000   1.6334   0.04853   0.04345  -0.0111   0.0283   0.9955
  16.250   1.6097   0.05486   0.04991  -0.0133   0.0267   0.9955
  16.750   1.5589   0.06762   0.06291  -0.0174   0.0253   0.9955
  17.000   1.5318   0.07421   0.06962  -0.0196   0.0245   0.9955
  17.250   1.5061   0.08098   0.07650  -0.0220   0.0233   0.9955
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