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NACA 0010 (naca0010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010 (naca0010-il)
Reynolds number: 200,000
Max Cl/Cd: 42.23 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0010-il-200000-n5.txt
Download as CSV file: xf-naca0010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.9542   0.08870   0.08477  -0.0028   1.0000   0.0176
 -13.750  -0.9842   0.07796   0.07388  -0.0102   1.0000   0.0173
 -13.500  -1.0102   0.06862   0.06433  -0.0171   1.0000   0.0172
 -13.250  -1.0325   0.06085   0.05632  -0.0227   1.0000   0.0172
 -13.000  -1.0511   0.05461   0.04982  -0.0265   1.0000   0.0173
 -12.750  -1.0665   0.04964   0.04455  -0.0285   1.0000   0.0175
 -12.500  -1.0782   0.04575   0.04039  -0.0289   1.0000   0.0178
 -12.250  -1.0825   0.04313   0.03764  -0.0282   1.0000   0.0181
 -12.000  -1.0817   0.04130   0.03571  -0.0269   1.0000   0.0185
 -11.750  -1.0792   0.03972   0.03402  -0.0251   1.0000   0.0189
 -11.500  -1.0748   0.03815   0.03231  -0.0233   1.0000   0.0195
 -11.250  -1.0675   0.03642   0.03038  -0.0217   1.0000   0.0202
 -11.000  -1.0584   0.03459   0.02831  -0.0201   1.0000   0.0210
 -10.750  -1.0470   0.03285   0.02628  -0.0187   1.0000   0.0222
 -10.500  -1.0328   0.03137   0.02446  -0.0173   1.0000   0.0233
 -10.250  -1.0185   0.02987   0.02289  -0.0162   1.0000   0.0244
 -10.000  -1.0010   0.02888   0.02182  -0.0152   1.0000   0.0255
  -9.750  -0.9828   0.02777   0.02058  -0.0142   1.0000   0.0268
  -9.500  -0.9638   0.02669   0.01931  -0.0132   1.0000   0.0284
  -9.250  -0.9435   0.02577   0.01815  -0.0123   1.0000   0.0300
  -9.000  -0.9252   0.02440   0.01673  -0.0112   1.0000   0.0315
  -8.750  -0.9047   0.02353   0.01578  -0.0104   1.0000   0.0331
  -8.500  -0.8834   0.02275   0.01491  -0.0096   1.0000   0.0350
  -8.250  -0.8617   0.02197   0.01400  -0.0087   1.0000   0.0369
  -8.000  -0.8393   0.02126   0.01313  -0.0079   1.0000   0.0384
  -7.750  -0.8196   0.02016   0.01204  -0.0069   1.0000   0.0405
  -7.500  -0.7978   0.01946   0.01130  -0.0060   1.0000   0.0425
  -7.250  -0.7757   0.01880   0.01056  -0.0052   1.0000   0.0444
  -7.000  -0.7534   0.01819   0.00987  -0.0043   1.0000   0.0466
  -6.750  -0.7307   0.01765   0.00924  -0.0034   1.0000   0.0484
  -6.500  -0.7100   0.01686   0.00845  -0.0023   1.0000   0.0509
  -6.250  -0.6879   0.01629   0.00785  -0.0013   1.0000   0.0535
  -6.000  -0.6654   0.01580   0.00730  -0.0004   1.0000   0.0568
  -5.750  -0.6431   0.01531   0.00678   0.0006   1.0000   0.0613
  -5.500  -0.6209   0.01481   0.00631   0.0015   1.0000   0.0680
  -5.250  -0.5986   0.01434   0.00584   0.0025   1.0000   0.0772
  -5.000  -0.5762   0.01388   0.00543   0.0034   1.0000   0.0913
  -4.750  -0.5537   0.01344   0.00507   0.0043   1.0000   0.1108
  -4.500  -0.5313   0.01300   0.00475   0.0052   1.0000   0.1350
  -4.250  -0.5088   0.01259   0.00445   0.0061   1.0000   0.1637
  -4.000  -0.4864   0.01219   0.00420   0.0069   1.0000   0.1994
  -3.750  -0.4640   0.01178   0.00398   0.0077   1.0000   0.2397
  -3.500  -0.4414   0.01142   0.00378   0.0085   1.0000   0.2819
  -3.250  -0.4190   0.01103   0.00364   0.0093   1.0000   0.3356
  -3.000  -0.3951   0.01064   0.00352   0.0098   0.9994   0.3958
  -2.750  -0.3590   0.01029   0.00341   0.0078   0.9941   0.4540
  -2.500  -0.3237   0.01001   0.00331   0.0061   0.9877   0.5006
  -2.250  -0.2882   0.00975   0.00323   0.0044   0.9812   0.5479
  -2.000  -0.2526   0.00949   0.00316   0.0028   0.9744   0.5969
  -1.750  -0.2196   0.00927   0.00311   0.0019   0.9654   0.6409
  -1.500  -0.1866   0.00908   0.00307   0.0010   0.9560   0.6798
  -1.250  -0.1527   0.00891   0.00304   0.0001   0.9461   0.7175
  -1.000  -0.1217   0.00877   0.00303  -0.0002   0.9331   0.7521
  -0.750  -0.0908   0.00866   0.00302  -0.0003   0.9189   0.7843
  -0.500  -0.0601   0.00858   0.00301  -0.0003   0.9030   0.8140
  -0.250  -0.0298   0.00854   0.00301  -0.0002   0.8853   0.8409
   0.000   0.0000   0.00852   0.00302   0.0000   0.8641   0.8642
   0.250   0.0298   0.00854   0.00301   0.0002   0.8409   0.8853
   0.500   0.0602   0.00858   0.00301   0.0003   0.8140   0.9030
   0.750   0.0908   0.00866   0.00302   0.0003   0.7843   0.9189
   1.000   0.1217   0.00877   0.00303   0.0002   0.7521   0.9331
   1.250   0.1527   0.00891   0.00304  -0.0001   0.7175   0.9461
   1.500   0.1866   0.00908   0.00307  -0.0010   0.6798   0.9560
   1.750   0.2196   0.00927   0.00311  -0.0019   0.6408   0.9654
   2.000   0.2526   0.00949   0.00316  -0.0028   0.5970   0.9744
   2.250   0.2882   0.00975   0.00323  -0.0044   0.5479   0.9812
   2.500   0.3237   0.01001   0.00331  -0.0061   0.5007   0.9877
   2.750   0.3591   0.01029   0.00341  -0.0078   0.4541   0.9942
   3.000   0.3951   0.01064   0.00352  -0.0098   0.3960   0.9994
   3.250   0.4189   0.01103   0.00364  -0.0093   0.3357   1.0000
   3.500   0.4413   0.01142   0.00378  -0.0085   0.2819   1.0000
   3.750   0.4639   0.01178   0.00398  -0.0077   0.2397   1.0000
   4.000   0.4864   0.01219   0.00420  -0.0069   0.1995   1.0000
   4.250   0.5088   0.01259   0.00445  -0.0061   0.1638   1.0000
   4.500   0.5313   0.01300   0.00474  -0.0052   0.1351   1.0000
   4.750   0.5537   0.01344   0.00507  -0.0043   0.1108   1.0000
   5.000   0.5761   0.01388   0.00543  -0.0034   0.0913   1.0000
   5.250   0.5985   0.01434   0.00584  -0.0025   0.0772   1.0000
   5.500   0.6209   0.01481   0.00631  -0.0015   0.0681   1.0000
   5.750   0.6431   0.01531   0.00678  -0.0006   0.0613   1.0000
   6.000   0.6654   0.01580   0.00730   0.0004   0.0568   1.0000
   6.250   0.6879   0.01629   0.00784   0.0013   0.0535   1.0000
   6.500   0.7100   0.01686   0.00845   0.0023   0.0509   1.0000
   6.750   0.7307   0.01764   0.00923   0.0034   0.0484   1.0000
   7.000   0.7534   0.01819   0.00987   0.0043   0.0466   1.0000
   7.250   0.7758   0.01880   0.01056   0.0052   0.0444   1.0000
   7.500   0.7979   0.01946   0.01130   0.0060   0.0425   1.0000
   7.750   0.8196   0.02016   0.01204   0.0069   0.0404   1.0000
   8.000   0.8394   0.02126   0.01313   0.0079   0.0384   1.0000
   8.250   0.8617   0.02197   0.01400   0.0087   0.0369   1.0000
   8.500   0.8835   0.02275   0.01491   0.0096   0.0350   1.0000
   8.750   0.9048   0.02352   0.01577   0.0104   0.0331   1.0000
   9.000   0.9252   0.02440   0.01672   0.0112   0.0315   1.0000
   9.250   0.9435   0.02578   0.01815   0.0122   0.0300   1.0000
   9.500   0.9639   0.02670   0.01931   0.0132   0.0284   1.0000
   9.750   0.9829   0.02778   0.02058   0.0142   0.0268   1.0000
  10.000   1.0011   0.02888   0.02182   0.0152   0.0255   1.0000
  10.250   1.0186   0.02986   0.02288   0.0161   0.0244   1.0000
  10.500   1.0330   0.03137   0.02446   0.0173   0.0233   1.0000
  10.750   1.0472   0.03285   0.02628   0.0186   0.0222   1.0000
  11.000   1.0586   0.03459   0.02831   0.0201   0.0210   1.0000
  11.250   1.0677   0.03641   0.03037   0.0216   0.0202   1.0000
  11.500   1.0751   0.03815   0.03231   0.0232   0.0195   1.0000
  11.750   1.0796   0.03972   0.03403   0.0250   0.0189   1.0000
  12.000   1.0822   0.04130   0.03571   0.0268   0.0185   1.0000
  12.250   1.0830   0.04315   0.03766   0.0281   0.0181   1.0000
  12.500   1.0786   0.04577   0.04041   0.0288   0.0178   1.0000
  12.750   1.0670   0.04968   0.04459   0.0284   0.0175   1.0000
  13.000   1.0516   0.05467   0.04988   0.0264   0.0173   1.0000
  13.250   1.0329   0.06093   0.05641   0.0225   0.0172   1.0000
  13.500   1.0107   0.06873   0.06445   0.0168   0.0172   1.0000
  13.750   0.9846   0.07813   0.07405   0.0099   0.0173   1.0000
  14.000   0.9545   0.08895   0.08503   0.0024   0.0176   1.0000
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