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NACA 23018 (naca23018-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 23018 (naca23018-il)
Reynolds number: 100,000
Max Cl/Cd: 36.13 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23018-il-100000.txt
Download as CSV file: xf-naca23018-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23018                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.8239   0.08224   0.07579  -0.0553   1.0000   0.1017
 -14.000  -0.8531   0.07594   0.06934  -0.0570   1.0000   0.1012
 -13.750  -0.8851   0.07040   0.06361  -0.0575   1.0000   0.1008
 -13.500  -0.9149   0.06582   0.05882  -0.0566   1.0000   0.1004
 -13.250  -0.9419   0.06204   0.05481  -0.0544   1.0000   0.1003
 -13.000  -0.9658   0.05891   0.05145  -0.0509   1.0000   0.1003
 -12.750  -0.9872   0.05628   0.04860  -0.0464   1.0000   0.1004
 -12.500  -1.0030   0.05373   0.04578  -0.0422   1.0000   0.1006
 -12.250  -1.0158   0.05140   0.04315  -0.0378   1.0000   0.1011
 -12.000  -1.0268   0.04936   0.04077  -0.0331   1.0000   0.1018
 -11.750  -1.0198   0.04688   0.03820  -0.0309   1.0000   0.1031
 -11.500  -1.0024   0.04508   0.03643  -0.0298   1.0000   0.1049
 -11.250  -0.9925   0.04343   0.03470  -0.0274   1.0000   0.1064
 -11.000  -0.9855   0.04179   0.03289  -0.0246   1.0000   0.1078
 -10.750  -0.9796   0.04027   0.03117  -0.0214   1.0000   0.1095
 -10.500  -0.9749   0.03890   0.02953  -0.0179   1.0000   0.1113
 -10.250  -0.9682   0.03752   0.02789  -0.0146   1.0000   0.1129
 -10.000  -0.9462   0.03583   0.02633  -0.0139   1.0000   0.1154
  -9.750  -0.9305   0.03465   0.02512  -0.0120   1.0000   0.1178
  -9.500  -0.9162   0.03357   0.02394  -0.0098   1.0000   0.1207
  -9.250  -0.9046   0.03262   0.02280  -0.0071   1.0000   0.1235
  -9.000  -0.8831   0.03126   0.02155  -0.0061   1.0000   0.1268
  -8.750  -0.8655   0.03029   0.02065  -0.0045   1.0000   0.1304
  -8.500  -0.8511   0.02946   0.01974  -0.0022   1.0000   0.1345
  -8.250  -0.8341   0.02847   0.01879  -0.0005   1.0000   0.1390
  -8.000  -0.8186   0.02763   0.01809   0.0015   1.0000   0.1441
  -7.750  -0.8052   0.02697   0.01733   0.0039   1.0000   0.1500
  -7.500  -0.7917   0.02604   0.01665   0.0060   1.0000   0.1568
  -7.250  -0.7801   0.02533   0.01598   0.0086   1.0000   0.1655
  -7.000  -0.7704   0.02455   0.01536   0.0114   1.0000   0.1761
  -6.750  -0.7620   0.02373   0.01473   0.0142   1.0000   0.1911
  -6.500  -0.7549   0.02282   0.01412   0.0172   1.0000   0.2153
  -6.250  -0.7497   0.02176   0.01355   0.0204   1.0000   0.2663
  -6.000  -0.7444   0.02098   0.01332   0.0236   1.0000   0.3459
  -5.750  -0.7276   0.02080   0.01338   0.0250   0.9982   0.4057
  -5.500  -0.6838   0.02099   0.01359   0.0216   0.9889   0.4559
  -5.250  -0.6373   0.02123   0.01393   0.0180   0.9799   0.4913
  -5.000  -0.5962   0.02132   0.01403   0.0153   0.9688   0.5199
  -4.750  -0.5556   0.02141   0.01420   0.0130   0.9576   0.5446
  -4.500  -0.5120   0.02151   0.01436   0.0103   0.9474   0.5698
  -4.250  -0.4705   0.02160   0.01451   0.0081   0.9363   0.5964
  -4.000  -0.4347   0.02165   0.01461   0.0071   0.9237   0.6206
  -3.750  -0.3843   0.02172   0.01476   0.0038   0.9161   0.6467
  -3.500  -0.3511   0.02178   0.01490   0.0036   0.9023   0.6685
  -3.250  -0.2951   0.02168   0.01484  -0.0006   0.8964   0.6896
  -3.000  -0.2636   0.02154   0.01472  -0.0005   0.8816   0.7055
  -2.750  -0.2186   0.02136   0.01458  -0.0026   0.8720   0.7201
  -2.500  -0.1796   0.02110   0.01432  -0.0036   0.8598   0.7356
  -2.250  -0.1477   0.02088   0.01407  -0.0034   0.8459   0.7522
  -2.000  -0.1012   0.02063   0.01381  -0.0052   0.8363   0.7663
  -1.750  -0.0693   0.02055   0.01374  -0.0046   0.8200   0.7799
  -1.500  -0.0383   0.02039   0.01353  -0.0040   0.8048   0.7956
  -1.250   0.0022   0.02030   0.01339  -0.0046   0.7913   0.8083
  -1.000   0.0381   0.02028   0.01331  -0.0046   0.7747   0.8206
  -0.750   0.0651   0.02025   0.01321  -0.0034   0.7567   0.8362
  -0.500   0.1082   0.02046   0.01335  -0.0048   0.7382   0.8449
  -0.250   0.1398   0.02051   0.01331  -0.0045   0.7201   0.8587
   0.000   0.1826   0.02071   0.01339  -0.0062   0.7008   0.8682
   0.250   0.2191   0.02081   0.01338  -0.0070   0.6818   0.8801
   0.500   0.2624   0.02098   0.01342  -0.0091   0.6612   0.8901
   0.750   0.3038   0.02109   0.01339  -0.0111   0.6404   0.9005
   1.000   0.3422   0.02120   0.01337  -0.0127   0.6196   0.9125
   1.250   0.3881   0.02130   0.01334  -0.0158   0.5969   0.9213
   1.500   0.4228   0.02141   0.01331  -0.0170   0.5762   0.9344
   1.750   0.4700   0.02150   0.01327  -0.0206   0.5529   0.9433
   2.000   0.5101   0.02160   0.01323  -0.0230   0.5312   0.9543
   2.250   0.5492   0.02174   0.01323  -0.0254   0.5102   0.9661
   2.500   0.5967   0.02178   0.01313  -0.0296   0.4882   0.9748
   2.750   0.6417   0.02184   0.01306  -0.0333   0.4679   0.9844
   3.000   0.6870   0.02191   0.01302  -0.0372   0.4493   0.9936
   3.250   0.7288   0.02197   0.01295  -0.0406   0.4328   1.0000
   3.500   0.7470   0.02212   0.01300  -0.0395   0.4207   1.0000
   3.750   0.7649   0.02237   0.01324  -0.0384   0.4093   1.0000
   4.000   0.7841   0.02259   0.01332  -0.0373   0.3995   1.0000
   4.250   0.8015   0.02291   0.01368  -0.0361   0.3892   1.0000
   4.500   0.8210   0.02317   0.01382  -0.0350   0.3804   1.0000
   4.750   0.8384   0.02357   0.01427  -0.0336   0.3718   1.0000
   5.000   0.8568   0.02390   0.01456  -0.0323   0.3636   1.0000
   5.250   0.8759   0.02436   0.01493  -0.0312   0.3565   1.0000
   5.500   0.8910   0.02480   0.01549  -0.0293   0.3485   1.0000
   5.750   0.9105   0.02520   0.01576  -0.0281   0.3418   1.0000
   6.000   0.9261   0.02577   0.01639  -0.0263   0.3348   1.0000
   6.250   0.9411   0.02620   0.01687  -0.0244   0.3272   1.0000
   6.500   0.9626   0.02666   0.01713  -0.0235   0.3208   1.0000
   6.750   0.9731   0.02728   0.01795  -0.0208   0.3140   1.0000
   7.000   0.9885   0.02776   0.01844  -0.0189   0.3074   1.0000
   7.250   1.0117   0.02836   0.01883  -0.0182   0.3016   1.0000
   7.500   1.0190   0.02908   0.01981  -0.0150   0.2956   1.0000
   7.750   1.0327   0.02968   0.02046  -0.0128   0.2896   1.0000
   8.000   1.0557   0.03024   0.02085  -0.0121   0.2841   1.0000
   8.250   1.0636   0.03115   0.02195  -0.0091   0.2786   1.0000
   8.500   1.0739   0.03189   0.02280  -0.0065   0.2728   1.0000
   8.750   1.0952   0.03242   0.02321  -0.0055   0.2673   1.0000
   9.000   1.1064   0.03344   0.02433  -0.0031   0.2621   1.0000
   9.250   1.1122   0.03437   0.02543   0.0001   0.2564   1.0000
   9.500   1.1301   0.03497   0.02599   0.0016   0.2510   1.0000
   9.750   1.1479   0.03598   0.02696   0.0028   0.2459   1.0000
  10.000   1.1467   0.03717   0.02840   0.0069   0.2406   1.0000
  10.250   1.1595   0.03794   0.02921   0.0089   0.2353   1.0000
  10.500   1.1890   0.03879   0.02985   0.0084   0.2301   1.0000
  10.750   1.1767   0.04041   0.03184   0.0136   0.2257   1.0000
  11.000   1.1808   0.04160   0.03316   0.0165   0.2207   1.0000
  11.250   1.2097   0.04206   0.03346   0.0162   0.2157   1.0000
  11.500   1.2066   0.04390   0.03548   0.0196   0.2118   1.0000
  11.750   1.1874   0.04600   0.03786   0.0247   0.2082   1.0000
  12.000   1.1851   0.04742   0.03938   0.0279   0.2043   1.0000
  12.250   1.2457   0.04724   0.03885   0.0239   0.1984   1.0000
  12.500   1.2034   0.05001   0.04199   0.0310   0.1966   1.0000
  12.750   1.1554   0.05413   0.04645   0.0362   0.1948   1.0000
  13.000   1.0715   0.06257   0.05529   0.0389   0.1941   1.0000
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