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NACA 23024 (naca23024-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 23024 (naca23024-il)
Reynolds number: 50,000
Max Cl/Cd: 19.9 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca23024-il-50000-n5.txt
Download as CSV file: xf-naca23024-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.4795   0.12983   0.11999  -0.0462   1.0000   0.1734
 -15.500  -0.5008   0.12010   0.11026  -0.0486   1.0000   0.1853
 -15.000  -0.5221   0.11087   0.10102  -0.0503   1.0000   0.1985
 -14.750  -0.4984   0.11203   0.10222  -0.0485   1.0000   0.2009
 -14.500  -0.4856   0.11136   0.10157  -0.0474   1.0000   0.2049
 -14.250  -0.5176   0.10369   0.09389  -0.0494   1.0000   0.2148
 -13.750  -0.5394   0.09545   0.08564  -0.0498   1.0000   0.2298
 -13.250  -0.5647   0.08735   0.07755  -0.0496   1.0000   0.2458
 -13.000  -0.6426   0.07533   0.06544  -0.0516   1.0000   0.2607
 -12.750  -0.5990   0.07886   0.06906  -0.0488   1.0000   0.2626
 -12.250  -0.6505   0.06949   0.05967  -0.0470   1.0000   0.2801
 -12.000  -0.6146   0.07198   0.06225  -0.0446   1.0000   0.2833
 -11.750  -0.7370   0.05901   0.04908  -0.0423   1.0000   0.2975
 -11.500  -0.6861   0.06223   0.05244  -0.0407   1.0000   0.3014
 -11.250  -0.7317   0.05759   0.04776  -0.0371   1.0000   0.3096
 -11.000  -0.8029   0.05223   0.04228  -0.0307   1.0000   0.3167
 -10.750  -0.7747   0.05329   0.04346  -0.0292   1.0000   0.3222
 -10.500  -0.8168   0.05051   0.04062  -0.0231   1.0000   0.3286
 -10.250  -0.8894   0.04705   0.03696  -0.0131   1.0000   0.3338
 -10.000  -0.8602   0.04782   0.03791  -0.0123   1.0000   0.3397
  -9.750  -0.8755   0.04700   0.03709  -0.0071   1.0000   0.3454
  -9.500  -0.8935   0.04486   0.03470  -0.0037   0.9904   0.3543
  -9.250  -0.8347   0.04561   0.03562  -0.0079   0.9845   0.3626
  -9.000  -0.8334   0.04423   0.03406  -0.0061   0.9732   0.3718
  -8.750  -0.7931   0.04417   0.03405  -0.0085   0.9656   0.3801
  -8.500  -0.7735   0.04360   0.03343  -0.0081   0.9549   0.3886
  -8.250  -0.7715   0.04251   0.03220  -0.0054   0.9431   0.3972
  -8.000  -0.7234   0.04265   0.03243  -0.0086   0.9355   0.4056
  -7.750  -0.7289   0.04156   0.03118  -0.0044   0.9221   0.4143
  -7.500  -0.6833   0.04142   0.03110  -0.0074   0.9149   0.4226
  -7.250  -0.6671   0.04101   0.03066  -0.0058   0.9031   0.4310
  -7.000  -0.6519   0.04008   0.02961  -0.0046   0.8933   0.4404
  -6.750  -0.6165   0.04014   0.02974  -0.0055   0.8832   0.4480
  -6.500  -0.6058   0.03928   0.02877  -0.0033   0.8722   0.4579
  -6.250  -0.5667   0.03907   0.02859  -0.0051   0.8641   0.4663
  -6.000  -0.5477   0.03878   0.02830  -0.0036   0.8518   0.4747
  -5.750  -0.5219   0.03790   0.02732  -0.0036   0.8446   0.4853
  -5.500  -0.4980   0.03801   0.02750  -0.0025   0.8315   0.4926
  -5.250  -0.4788   0.03722   0.02661  -0.0012   0.8229   0.5035
  -5.000  -0.4479   0.03709   0.02652  -0.0015   0.8124   0.5117
  -4.750  -0.4195   0.03680   0.02624  -0.0013   0.8023   0.5213
  -4.500  -0.3824   0.03607   0.02545  -0.0027   0.7963   0.5325
  -4.250  -0.3658   0.03622   0.02565  -0.0005   0.7820   0.5401
  -4.000  -0.3489   0.03533   0.02462   0.0014   0.7741   0.5526
  -3.750  -0.3109   0.03560   0.02501   0.0002   0.7626   0.5604
  -3.500  -0.2815   0.03516   0.02453   0.0002   0.7534   0.5713
  -3.250  -0.2178   0.03472   0.02409  -0.0053   0.7482   0.5824
  -3.000  -0.2198   0.03490   0.02430   0.0000   0.7328   0.5913
  -2.750  -0.1781   0.03427   0.02359  -0.0020   0.7258   0.6034
  -2.500  -0.1551   0.03459   0.02398  -0.0007   0.7125   0.6119
  -2.250  -0.1415   0.03394   0.02323   0.0019   0.7035   0.6252
  -2.000  -0.0832   0.03421   0.02357  -0.0026   0.6932   0.6332
  -1.750  -0.0721   0.03403   0.02336   0.0005   0.6819   0.6453
  -1.500   0.0027   0.03373   0.02301  -0.0066   0.6747   0.6549
  -1.250   0.0020   0.03415   0.02350  -0.0016   0.6603   0.6649
  -1.000   0.0416   0.03372   0.02298  -0.0031   0.6519   0.6769
  -0.750   0.0693   0.03423   0.02356  -0.0026   0.6387   0.6852
  -0.500   0.0806   0.03379   0.02304   0.0005   0.6295   0.6994
  -0.250   0.1318   0.03430   0.02358  -0.0029   0.6170   0.7061
   0.000   0.1650   0.03427   0.02351  -0.0034   0.6063   0.7169
   0.250   0.1901   0.03438   0.02360  -0.0026   0.5954   0.7274
   0.500   0.2353   0.03468   0.02389  -0.0050   0.5831   0.7354
   0.750   0.2449   0.03451   0.02366  -0.0017   0.5738   0.7490
   1.000   0.2880   0.03505   0.02422  -0.0039   0.5606   0.7555
   1.250   0.3155   0.03499   0.02408  -0.0035   0.5510   0.7674
   1.500   0.3352   0.03546   0.02460  -0.0020   0.5388   0.7765
   1.750   0.3862   0.03560   0.02464  -0.0054   0.5282   0.7840
   2.000   0.3808   0.03593   0.02504   0.0001   0.5176   0.7979
   2.250   0.4434   0.03600   0.02495  -0.0052   0.5070   0.8033
   2.500   0.4257   0.03646   0.02554   0.0022   0.4973   0.8197
   2.750   0.4827   0.03670   0.02567  -0.0023   0.4863   0.8246
   3.000   0.4959   0.03730   0.02634  -0.0001   0.4756   0.8354
   3.250   0.5186   0.03747   0.02646   0.0008   0.4663   0.8465
   3.500   0.5522   0.03797   0.02695  -0.0003   0.4559   0.8543
   3.750   0.5560   0.03831   0.02732   0.0034   0.4472   0.8686
   4.000   0.6062   0.03853   0.02744  -0.0004   0.4373   0.8745
   4.250   0.6061   0.03921   0.02821   0.0037   0.4282   0.8887
   4.500   0.6542   0.03924   0.02811   0.0003   0.4191   0.8953
   4.750   0.6612   0.04009   0.02907   0.0029   0.4098   0.9073
   5.000   0.6890   0.04043   0.02939   0.0024   0.4012   0.9167
   5.250   0.7177   0.04085   0.02977   0.0016   0.3931   0.9264
   5.500   0.7286   0.04163   0.03066   0.0033   0.3843   0.9375
   5.750   0.7675   0.04172   0.03062   0.0012   0.3771   0.9467
   6.000   0.7773   0.04275   0.03179   0.0025   0.3689   0.9572
   6.250   0.7993   0.04337   0.03243   0.0022   0.3612   0.9672
   6.500   0.8444   0.04339   0.03232  -0.0011   0.3543   0.9744
   6.750   0.8445   0.04490   0.03405   0.0007   0.3464   0.9857
   7.000   0.8778   0.04530   0.03443  -0.0014   0.3394   0.9937
   7.250   0.9101   0.04574   0.03482  -0.0034   0.3330   1.0000
   7.500   0.8673   0.04749   0.03672   0.0051   0.3287   1.0000
   7.750   0.8402   0.04899   0.03828   0.0113   0.3242   1.0000
   8.000   0.8375   0.04967   0.03891   0.0148   0.3200   1.0000
   8.250   0.8697   0.04904   0.03809   0.0150   0.3160   1.0000
   8.500   0.7753   0.05421   0.04355   0.0258   0.3110   1.0000
   8.750   0.7027   0.06006   0.04955   0.0321   0.3044   1.0000
   9.000   0.7163   0.06016   0.04956   0.0340   0.3006   1.0000
   9.250   0.7601   0.05818   0.04744   0.0347   0.2979   1.0000
   9.500   0.5784   0.07680   0.06640   0.0389   0.2828   1.0000
   9.750   0.6022   0.07586   0.06538   0.0407   0.2807   1.0000
  10.250   0.5230   0.09043   0.08003   0.0407   0.2638   1.0000
  11.250   0.4500   0.11085   0.10046   0.0399   0.2393   1.0000
  11.500   0.4472   0.11403   0.10363   0.0400   0.2348   1.0000
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