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NACA 23024 (naca23024-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 23024 (naca23024-il)
Reynolds number: 100,000
Max Cl/Cd: 34.16 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23024-il-100000.txt
Download as CSV file: xf-naca23024-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23024                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -16.750  -0.9507   0.06823   0.06056  -0.0725   1.0000   0.1800
 -16.500  -1.0170   0.06055   0.05253  -0.0718   1.0000   0.1824
 -16.250  -1.0641   0.05550   0.04717  -0.0696   1.0000   0.1850
 -16.000  -1.0011   0.05805   0.05013  -0.0694   1.0000   0.1915
 -15.750  -1.0319   0.05421   0.04610  -0.0672   1.0000   0.1950
 -15.500  -1.0763   0.05016   0.04174  -0.0636   1.0000   0.1980
 -15.250  -1.0285   0.05136   0.04331  -0.0636   1.0000   0.2049
 -15.000  -1.0505   0.04878   0.04059  -0.0605   1.0000   0.2093
 -14.750  -1.0913   0.04573   0.03725  -0.0554   1.0000   0.2127
 -14.500  -1.0477   0.04644   0.03832  -0.0558   1.0000   0.2200
 -14.250  -1.0707   0.04443   0.03619  -0.0514   1.0000   0.2249
 -14.000  -1.0901   0.04269   0.03434  -0.0467   1.0000   0.2295
 -13.750  -1.0679   0.04272   0.03458  -0.0455   1.0000   0.2365
 -13.500  -1.0938   0.04116   0.03288  -0.0397   1.0000   0.2412
 -13.250  -1.1004   0.04021   0.03194  -0.0355   1.0000   0.2467
 -13.000  -1.0923   0.03994   0.03180  -0.0327   1.0000   0.2533
 -12.750  -1.1203   0.03883   0.03056  -0.0256   1.0000   0.2579
 -12.500  -1.1296   0.03810   0.02983  -0.0205   1.0000   0.2633
 -12.250  -1.1221   0.03795   0.02982  -0.0174   1.0000   0.2698
 -12.000  -1.1484   0.03725   0.02901  -0.0097   1.0000   0.2746
 -11.750  -1.1884   0.03659   0.02816   0.0003   1.0000   0.2779
 -11.500  -1.1585   0.03655   0.02842   0.0001   1.0000   0.2860
 -11.250  -1.1796   0.03620   0.02801   0.0076   1.0000   0.2909
 -11.000  -1.2134   0.03569   0.02732   0.0171   1.0000   0.2950
 -10.750  -1.1997   0.03552   0.02733   0.0192   1.0000   0.3019
 -10.500  -1.2053   0.03526   0.02709   0.0243   1.0000   0.3081
 -10.250  -1.2279   0.03469   0.02632   0.0321   1.0000   0.3136
 -10.000  -1.2147   0.03453   0.02633   0.0342   1.0000   0.3205
  -9.750  -1.1927   0.03454   0.02628   0.0344   0.9935   0.3304
  -9.500  -1.1539   0.03453   0.02636   0.0319   0.9848   0.3406
  -9.250  -1.1277   0.03450   0.02622   0.0315   0.9752   0.3512
  -9.000  -1.0879   0.03446   0.02631   0.0290   0.9666   0.3610
  -8.750  -1.0673   0.03426   0.02602   0.0298   0.9558   0.3709
  -8.500  -1.0211   0.03424   0.02609   0.0263   0.9488   0.3812
  -8.250  -1.0043   0.03397   0.02578   0.0280   0.9370   0.3904
  -8.000  -0.9672   0.03376   0.02558   0.0262   0.9293   0.4004
  -7.750  -0.9415   0.03361   0.02547   0.0265   0.9182   0.4097
  -7.500  -0.9091   0.03323   0.02502   0.0255   0.9107   0.4200
  -7.250  -0.8827   0.03317   0.02507   0.0259   0.8989   0.4285
  -7.000  -0.8527   0.03264   0.02436   0.0254   0.8920   0.4397
  -6.750  -0.8275   0.03263   0.02453   0.0260   0.8796   0.4472
  -6.500  -0.7991   0.03218   0.02397   0.0261   0.8715   0.4581
  -6.250  -0.7361   0.03184   0.02376   0.0202   0.8679   0.4691
  -6.000  -0.7417   0.03175   0.02365   0.0261   0.8516   0.4763
  -5.750  -0.6978   0.03113   0.02300   0.0236   0.8462   0.4874
  -5.500  -0.6810   0.03117   0.02311   0.0258   0.8334   0.4956
  -5.250  -0.6631   0.03055   0.02232   0.0279   0.8247   0.5065
  -5.000  -0.5909   0.03006   0.02204   0.0208   0.8216   0.5180
  -4.750  -0.6027   0.03006   0.02195   0.0278   0.8058   0.5264
  -4.500  -0.5451   0.02945   0.02144   0.0233   0.8012   0.5375
  -4.250  -0.5005   0.02861   0.02052   0.0212   0.7973   0.5510
  -4.000  -0.4919   0.02875   0.02075   0.0248   0.7826   0.5586
  -3.750  -0.4412   0.02809   0.02011   0.0216   0.7775   0.5717
  -3.500  -0.3627   0.02731   0.01941   0.0134   0.7747   0.5849
  -3.250  -0.3696   0.02742   0.01952   0.0200   0.7601   0.5941
  -3.000  -0.3040   0.02677   0.01890   0.0139   0.7546   0.6072
  -2.750  -0.2353   0.02600   0.01809   0.0074   0.7502   0.6222
  -2.500  -0.2230   0.02616   0.01834   0.0106   0.7363   0.6309
  -2.250  -0.1638   0.02567   0.01783   0.0057   0.7289   0.6446
  -2.000  -0.1006   0.02542   0.01759   0.0000   0.7197   0.6561
  -1.750  -0.0836   0.02541   0.01760   0.0025   0.7072   0.6674
  -1.500   0.0008   0.02504   0.01716  -0.0070   0.6985   0.6796
  -1.250   0.0044   0.02533   0.01753  -0.0020   0.6844   0.6897
  -1.000   0.0711   0.02499   0.01705  -0.0084   0.6749   0.7022
  -0.750   0.0959   0.02547   0.01764  -0.0072   0.6600   0.7106
  -0.500   0.1283   0.02510   0.01709  -0.0075   0.6508   0.7246
  -0.250   0.1784   0.02576   0.01786  -0.0108   0.6351   0.7308
   0.000   0.2435   0.02606   0.01804  -0.0168   0.6226   0.7395
   0.250   0.2464   0.02612   0.01813  -0.0119   0.6108   0.7514
   0.500   0.3317   0.02679   0.01870  -0.0214   0.5956   0.7552
   0.750   0.3778   0.02718   0.01903  -0.0240   0.5823   0.7631
   1.000   0.3912   0.02726   0.01909  -0.0211   0.5720   0.7748
   1.250   0.4578   0.02794   0.01965  -0.0271   0.5572   0.7781
   1.500   0.4905   0.02853   0.02027  -0.0274   0.5443   0.7855
   1.750   0.5060   0.02841   0.02005  -0.0250   0.5344   0.7980
   2.000   0.5522   0.02921   0.02086  -0.0275   0.5206   0.8022
   2.250   0.6051   0.02961   0.02106  -0.0314   0.5084   0.8085
   2.500   0.6005   0.02970   0.02125  -0.0257   0.4988   0.8223
   2.750   0.6599   0.03018   0.02155  -0.0308   0.4859   0.8267
   3.000   0.6458   0.03020   0.02167  -0.0234   0.4781   0.8436
   3.250   0.7031   0.03066   0.02199  -0.0283   0.4648   0.8473
   3.500   0.7367   0.03121   0.02259  -0.0292   0.4527   0.8544
   3.750   0.7442   0.03123   0.02255  -0.0257   0.4446   0.8687
   4.000   0.7900   0.03176   0.02306  -0.0288   0.4327   0.8740
   4.250   0.8230   0.03200   0.02322  -0.0298   0.4224   0.8834
   4.500   0.8442   0.03233   0.02351  -0.0289   0.4139   0.8940
   4.750   0.8795   0.03269   0.02389  -0.0305   0.4032   0.9019
   5.250   0.9349   0.03341   0.02462  -0.0312   0.3856   0.9211
   5.500   0.9635   0.03362   0.02467  -0.0317   0.3782   0.9320
   5.750   0.9969   0.03411   0.02526  -0.0334   0.3692   0.9399
   6.000   1.0213   0.03441   0.02556  -0.0333   0.3615   0.9503
   6.250   1.0692   0.03470   0.02569  -0.0376   0.3537   0.9576
   6.500   1.0857   0.03521   0.02641  -0.0365   0.3462   0.9682
   6.750   1.1219   0.03546   0.02655  -0.0387   0.3392   0.9776
   7.000   1.1627   0.03578   0.02687  -0.0421   0.3320   0.9852
   7.250   1.1900   0.03614   0.02738  -0.0433   0.3246   0.9950
   7.500   1.2342   0.03613   0.02718  -0.0471   0.3182   1.0000
   7.750   1.2368   0.03682   0.02790  -0.0436   0.3141   1.0000
   8.000   1.2189   0.03756   0.02884  -0.0368   0.3102   1.0000
   8.250   1.2088   0.03818   0.02954  -0.0313   0.3064   1.0000
   8.500   1.2134   0.03854   0.02987  -0.0280   0.3022   1.0000
   8.750   1.2517   0.03894   0.03000  -0.0303   0.2974   1.0000
   9.000   1.2199   0.03986   0.03115  -0.0214   0.2949   1.0000
   9.250   1.1876   0.04068   0.03214  -0.0124   0.2922   1.0000
   9.500   1.1556   0.04142   0.03300  -0.0035   0.2898   1.0000
   9.750   1.1340   0.04220   0.03385   0.0035   0.2871   1.0000
  10.000   1.1394   0.04259   0.03419   0.0066   0.2834   1.0000
  10.250   1.1808   0.04306   0.03446   0.0042   0.2786   1.0000
  10.500   1.1296   0.04442   0.03602   0.0151   0.2771   1.0000
  10.750   1.0748   0.04648   0.03828   0.0251   0.2752   1.0000
  11.000   1.0132   0.04960   0.04161   0.0343   0.2731   1.0000
  11.250   0.4140   0.11903   0.11196   0.0340   0.2602   1.0000
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