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NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 2.5411 (naca2411-il)
Reynolds number: 500,000
Max Cl/Cd: 95.6 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca2411-il-500000.txt
Download as CSV file: xf-naca2411-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2.5411                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7556   0.05417   0.05117  -0.0700   1.0000   0.0217
 -12.250  -0.7845   0.04684   0.04366  -0.0762   1.0000   0.0216
 -12.000  -0.8126   0.04241   0.03906  -0.0770   1.0000   0.0215
 -11.750  -0.8384   0.04004   0.03656  -0.0731   1.0000   0.0215
 -11.500  -0.8584   0.03786   0.03420  -0.0684   1.0000   0.0215
 -11.250  -0.8663   0.03634   0.03248  -0.0646   1.0000   0.0217
 -11.000  -0.8774   0.03401   0.02991  -0.0605   1.0000   0.0218
 -10.750  -0.8881   0.03105   0.02668  -0.0563   1.0000   0.0220
 -10.500  -0.8881   0.02898   0.02445  -0.0530   1.0000   0.0223
 -10.250  -0.8818   0.02757   0.02294  -0.0503   1.0000   0.0226
 -10.000  -0.8726   0.02644   0.02170  -0.0478   1.0000   0.0229
  -9.750  -0.8616   0.02546   0.02062  -0.0455   1.0000   0.0233
  -9.500  -0.8379   0.02420   0.01919  -0.0458   0.9986   0.0238
  -9.250  -0.8077   0.02302   0.01785  -0.0471   0.9962   0.0245
  -9.000  -0.7762   0.02191   0.01656  -0.0486   0.9942   0.0253
  -8.750  -0.7465   0.02103   0.01550  -0.0495   0.9913   0.0260
  -8.500  -0.7172   0.01970   0.01397  -0.0505   0.9885   0.0266
  -8.250  -0.6873   0.01831   0.01250  -0.0517   0.9861   0.0276
  -8.000  -0.6535   0.01756   0.01170  -0.0533   0.9843   0.0284
  -7.750  -0.6228   0.01691   0.01097  -0.0542   0.9813   0.0295
  -7.500  -0.5924   0.01631   0.01029  -0.0549   0.9776   0.0307
  -7.250  -0.5585   0.01580   0.00968  -0.0563   0.9750   0.0318
  -7.000  -0.5257   0.01476   0.00862  -0.0577   0.9728   0.0336
  -6.750  -0.4890   0.01424   0.00808  -0.0597   0.9713   0.0356
  -6.500  -0.4610   0.01380   0.00757  -0.0597   0.9659   0.0375
  -6.250  -0.4284   0.01304   0.00680  -0.0609   0.9623   0.0404
  -6.000  -0.3914   0.01265   0.00639  -0.0628   0.9601   0.0442
  -5.750  -0.3547   0.01207   0.00581  -0.0647   0.9585   0.0490
  -5.500  -0.3162   0.01173   0.00545  -0.0670   0.9573   0.0541
  -5.250  -0.2907   0.01127   0.00502  -0.0665   0.9511   0.0603
  -5.000  -0.2573   0.01089   0.00464  -0.0676   0.9475   0.0675
  -4.750  -0.2220   0.01057   0.00432  -0.0691   0.9447   0.0758
  -4.500  -0.1866   0.01017   0.00396  -0.0707   0.9421   0.0872
  -4.250  -0.1624   0.00987   0.00372  -0.0698   0.9341   0.0989
  -4.000  -0.1301   0.00955   0.00344  -0.0706   0.9293   0.1151
  -3.750  -0.1017   0.00925   0.00321  -0.0706   0.9227   0.1339
  -3.500  -0.0735   0.00896   0.00300  -0.0706   0.9152   0.1565
  -3.250  -0.0447   0.00869   0.00280  -0.0707   0.9080   0.1819
  -3.000  -0.0176   0.00845   0.00264  -0.0704   0.8990   0.2098
  -2.750   0.0093   0.00823   0.00250  -0.0701   0.8898   0.2408
  -2.500   0.0373   0.00800   0.00235  -0.0700   0.8808   0.2745
  -2.250   0.0625   0.00779   0.00225  -0.0693   0.8694   0.3107
  -2.000   0.0887   0.00759   0.00214  -0.0688   0.8584   0.3512
  -1.500   0.1384   0.00705   0.00195  -0.0673   0.8346   0.4749
  -1.250   0.1611   0.00676   0.00191  -0.0661   0.8212   0.5620
  -1.000   0.1834   0.00650   0.00188  -0.0647   0.8077   0.6454
  -0.750   0.2054   0.00628   0.00187  -0.0632   0.7936   0.7212
  -0.500   0.2280   0.00610   0.00188  -0.0616   0.7793   0.7935
  -0.250   0.2533   0.00600   0.00192  -0.0606   0.7646   0.8601
   0.000   0.2882   0.00602   0.00198  -0.0616   0.7493   0.9115
   0.250   0.3285   0.00612   0.00204  -0.0639   0.7329   0.9411
   0.500   0.3692   0.00626   0.00208  -0.0664   0.7157   0.9580
   0.750   0.4073   0.00641   0.00214  -0.0684   0.6978   0.9705
   1.000   0.4496   0.00656   0.00219  -0.0713   0.6795   0.9783
   1.250   0.4896   0.00671   0.00223  -0.0738   0.6608   0.9860
   1.500   0.5304   0.00685   0.00228  -0.0766   0.6419   0.9926
   1.750   0.5728   0.00696   0.00230  -0.0798   0.6220   0.9982
   2.000   0.6021   0.00707   0.00232  -0.0801   0.6041   1.0000
   2.250   0.6229   0.00717   0.00235  -0.0787   0.5873   1.0000
   2.500   0.6440   0.00728   0.00240  -0.0773   0.5716   1.0000
   2.750   0.6653   0.00741   0.00246  -0.0759   0.5560   1.0000
   3.000   0.6865   0.00755   0.00254  -0.0744   0.5400   1.0000
   3.250   0.7078   0.00770   0.00263  -0.0730   0.5239   1.0000
   3.500   0.7292   0.00785   0.00272  -0.0717   0.5082   1.0000
   3.750   0.7506   0.00801   0.00284  -0.0703   0.4917   1.0000
   4.000   0.7718   0.00819   0.00295  -0.0689   0.4742   1.0000
   4.250   0.7931   0.00838   0.00308  -0.0675   0.4571   1.0000
   4.500   0.8147   0.00856   0.00322  -0.0662   0.4405   1.0000
   5.000   0.8575   0.00897   0.00352  -0.0635   0.4025   1.0000
   5.250   0.8782   0.00922   0.00369  -0.0620   0.3791   1.0000
   5.500   0.8985   0.00951   0.00389  -0.0605   0.3526   1.0000
   5.750   0.9181   0.00984   0.00412  -0.0589   0.3240   1.0000
   6.000   0.9368   0.01025   0.00438  -0.0571   0.2916   1.0000
   6.250   0.9543   0.01074   0.00470  -0.0552   0.2553   1.0000
   6.500   0.9712   0.01130   0.00506  -0.0533   0.2156   1.0000
   6.750   0.9877   0.01189   0.00545  -0.0513   0.1796   1.0000
   7.000   1.0044   0.01249   0.00588  -0.0493   0.1465   1.0000
   7.250   1.0210   0.01308   0.00633  -0.0474   0.1189   1.0000
   7.500   1.0374   0.01370   0.00681  -0.0454   0.0962   1.0000
   7.750   1.0547   0.01424   0.00727  -0.0436   0.0804   1.0000
   8.000   1.0718   0.01478   0.00776  -0.0418   0.0687   1.0000
   8.250   1.0883   0.01535   0.00829  -0.0398   0.0600   1.0000
   8.500   1.1048   0.01590   0.00881  -0.0379   0.0533   1.0000
   8.750   1.1212   0.01642   0.00937  -0.0359   0.0482   1.0000
   9.000   1.1335   0.01709   0.01000  -0.0333   0.0435   1.0000
   9.250   1.1477   0.01759   0.01055  -0.0309   0.0401   1.0000
   9.500   1.1602   0.01818   0.01115  -0.0284   0.0372   1.0000
   9.750   1.1695   0.01896   0.01197  -0.0254   0.0346   1.0000
  10.000   1.1832   0.01954   0.01260  -0.0233   0.0327   1.0000
  10.250   1.1948   0.02025   0.01333  -0.0209   0.0309   1.0000
  10.500   1.2002   0.02133   0.01444  -0.0178   0.0295   1.0000
  10.750   1.2103   0.02219   0.01539  -0.0154   0.0284   1.0000
  11.000   1.2212   0.02302   0.01629  -0.0133   0.0275   1.0000
  11.250   1.2323   0.02386   0.01718  -0.0113   0.0263   1.0000
  11.500   1.2412   0.02487   0.01824  -0.0093   0.0254   1.0000
  11.750   1.2453   0.02626   0.01966  -0.0069   0.0246   1.0000
  12.000   1.2457   0.02803   0.02150  -0.0044   0.0239   1.0000
  12.250   1.2550   0.02920   0.02277  -0.0028   0.0235   1.0000
  12.500   1.2628   0.03053   0.02420  -0.0012   0.0230   1.0000
  12.750   1.2692   0.03203   0.02579   0.0003   0.0226   1.0000
  13.000   1.2762   0.03352   0.02736   0.0015   0.0221   1.0000
  13.250   1.2820   0.03517   0.02910   0.0027   0.0215   1.0000
  13.500   1.2869   0.03696   0.03096   0.0038   0.0211   1.0000
  13.750   1.2914   0.03885   0.03291   0.0047   0.0208   1.0000
  14.000   1.2947   0.04091   0.03504   0.0055   0.0204   1.0000
  14.250   1.2952   0.04333   0.03753   0.0064   0.0199   1.0000
  14.500   1.2948   0.04597   0.04026   0.0072   0.0195   1.0000
  14.750   1.2973   0.04833   0.04275   0.0076   0.0193   1.0000
  15.000   1.2991   0.05081   0.04536   0.0078   0.0191   1.0000
  15.250   1.2992   0.05359   0.04827   0.0079   0.0189   1.0000
  15.500   1.2994   0.05643   0.05124   0.0077   0.0186   1.0000
  15.750   1.2982   0.05949   0.05443   0.0074   0.0184   1.0000
  16.000   1.2955   0.06286   0.05794   0.0069   0.0181   1.0000
  16.250   1.2923   0.06640   0.06161   0.0062   0.0180   1.0000
  16.500   1.2888   0.07008   0.06541   0.0051   0.0177   1.0000
  16.750   1.2825   0.07425   0.06972   0.0040   0.0176   1.0000
  17.000   1.2761   0.07858   0.07419   0.0024   0.0174   1.0000
  17.250   1.2686   0.08322   0.07896   0.0007   0.0173   1.0000
  17.500   1.2610   0.08798   0.08384  -0.0014   0.0171   1.0000
  17.750   1.2511   0.09324   0.08923  -0.0037   0.0170   1.0000
  18.000   1.2436   0.09826   0.09435  -0.0062   0.0168   1.0000
  18.250   1.2284   0.10482   0.10110  -0.0094   0.0169   1.0000
  18.500   1.2162   0.11099   0.10740  -0.0127   0.0167   1.0000
  18.750   1.2059   0.11696   0.11347  -0.0160   0.0166   1.0000
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