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NACA 23021 (naca23021-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 23021 (naca23021-il)
Reynolds number: 50,000
Max Cl/Cd: 18.64 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca23021-il-50000.txt
Download as CSV file: xf-naca23021-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 23021                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4365   0.11729   0.10854  -0.0267   1.0000   0.2573
 -12.250  -0.6588   0.07884   0.07014  -0.0456   1.0000   0.2435
 -12.000  -0.7843   0.06312   0.05427  -0.0472   1.0000   0.2407
 -11.750  -0.8568   0.05692   0.04788  -0.0418   1.0000   0.2401
 -11.500  -0.9097   0.05356   0.04437  -0.0340   1.0000   0.2411
 -11.250  -0.8903   0.05276   0.04371  -0.0323   1.0000   0.2509
 -11.000  -0.9176   0.05055   0.04141  -0.0260   1.0000   0.2561
 -10.750  -0.9569   0.04795   0.03855  -0.0182   1.0000   0.2601
 -10.500  -0.9295   0.04772   0.03859  -0.0171   1.0000   0.2734
 -10.250  -0.9406   0.04616   0.03698  -0.0119   1.0000   0.2823
 -10.000  -0.9420   0.04520   0.03604  -0.0076   1.0000   0.2941
  -9.750  -0.9266   0.04484   0.03587  -0.0051   1.0000   0.3084
  -9.500  -0.9395   0.04335   0.03429   0.0005   1.0000   0.3199
  -9.250  -0.9390   0.04260   0.03357   0.0047   1.0000   0.3345
  -9.000  -0.9218   0.04263   0.03380   0.0073   1.0000   0.3520
  -8.750  -0.9073   0.04270   0.03404   0.0102   1.0000   0.3697
  -8.500  -0.8938   0.04292   0.03439   0.0134   1.0000   0.3881
  -8.250  -0.8795   0.04333   0.03492   0.0165   1.0000   0.4070
  -8.000  -0.8656   0.04377   0.03545   0.0197   1.0000   0.4258
  -7.750  -0.8609   0.04357   0.03528   0.0236   1.0000   0.4432
  -7.500  -0.8708   0.04243   0.03403   0.0286   1.0000   0.4597
  -7.250  -0.8340   0.04408   0.03586   0.0297   1.0000   0.4766
  -7.000  -0.8117   0.04480   0.03665   0.0319   1.0000   0.4915
  -6.750  -0.8216   0.04333   0.03510   0.0363   1.0000   0.5060
  -6.500  -0.8029   0.04383   0.03563   0.0386   1.0000   0.5202
  -6.250  -0.7878   0.04402   0.03586   0.0411   1.0000   0.5333
  -6.000  -0.7988   0.04230   0.03400   0.0452   1.0000   0.5483
  -5.750  -0.7678   0.04377   0.03560   0.0465   1.0000   0.5603
  -5.500  -0.7664   0.04296   0.03474   0.0497   1.0000   0.5746
  -5.250  -0.7582   0.04281   0.03457   0.0524   1.0000   0.5897
  -5.000  -0.7360   0.04386   0.03571   0.0544   1.0000   0.6027
  -4.750  -0.7348   0.04308   0.03489   0.0574   1.0000   0.6185
  -4.500  -0.7189   0.04361   0.03545   0.0595   1.0000   0.6323
  -4.250  -0.6680   0.04483   0.03666   0.0558   0.9905   0.6480
  -4.000  -0.6187   0.04510   0.03683   0.0508   0.9759   0.6653
  -3.750  -0.5788   0.04492   0.03654   0.0470   0.9614   0.6835
  -3.500  -0.5008   0.04711   0.03874   0.0404   0.9457   0.6948
  -3.250  -0.4689   0.04684   0.03841   0.0385   0.9302   0.7107
  -3.000  -0.4288   0.04711   0.03863   0.0359   0.9144   0.7266
  -2.750  -0.3544   0.04855   0.04004   0.0291   0.8988   0.7385
  -2.500  -0.2918   0.04879   0.04019   0.0230   0.8850   0.7554
  -2.250  -0.2340   0.04946   0.04083   0.0183   0.8678   0.7689
  -2.000  -0.1703   0.05000   0.04134   0.0126   0.8509   0.7818
  -1.750  -0.1244   0.04977   0.04106   0.0092   0.8359   0.7987
  -1.500   0.0671   0.04951   0.04072  -0.0158   0.8219   0.8112
  -1.250   0.1102   0.04913   0.04033  -0.0185   0.8040   0.8255
  -1.000   0.1339   0.04871   0.03987  -0.0182   0.7882   0.8420
  -0.750   0.2693   0.04649   0.03758  -0.0336   0.7759   0.8556
  -0.500   0.3007   0.04616   0.03725  -0.0345   0.7572   0.8697
  -0.250   0.3191   0.04605   0.03712  -0.0334   0.7401   0.8854
   0.000   0.3905   0.04483   0.03587  -0.0398   0.7229   0.8992
   0.250   0.4483   0.04330   0.03426  -0.0437   0.7082   0.9139
   0.500   0.4778   0.04319   0.03415  -0.0447   0.6893   0.9289
   0.750   0.5130   0.04293   0.03387  -0.0464   0.6714   0.9440
   1.000   0.5642   0.04207   0.03297  -0.0506   0.6535   0.9582
   1.250   0.6181   0.04077   0.03155  -0.0547   0.6379   0.9726
   1.500   0.6644   0.04018   0.03095  -0.0588   0.6189   0.9867
   1.750   0.7126   0.03977   0.03056  -0.0637   0.6000   0.9999
   2.000   0.7240   0.04011   0.03087  -0.0621   0.5870   1.0000
   2.250   0.7384   0.04007   0.03076  -0.0605   0.5751   1.0000
   2.500   0.7440   0.04101   0.03176  -0.0586   0.5623   1.0000
   2.750   0.7610   0.04082   0.03146  -0.0571   0.5521   1.0000
   3.000   0.7609   0.04222   0.03296  -0.0546   0.5399   1.0000
   3.250   0.7780   0.04212   0.03277  -0.0531   0.5307   1.0000
   3.500   0.7726   0.04390   0.03466  -0.0500   0.5201   1.0000
   3.750   0.7838   0.04429   0.03502  -0.0480   0.5109   1.0000
   4.000   0.7871   0.04537   0.03610  -0.0453   0.5025   1.0000
   4.250   0.7632   0.04814   0.03901  -0.0403   0.4932   1.0000
   4.500   0.7956   0.04727   0.03801  -0.0399   0.4862   1.0000
   4.750   0.7367   0.05209   0.04300  -0.0318   0.4788   1.0000
   5.000   0.4913   0.06629   0.05717  -0.0103   0.4752   1.0000
   5.250   0.4405   0.07047   0.06127  -0.0049   0.4705   1.0000
   5.500   0.6122   0.06211   0.05296  -0.0117   0.4616   1.0000
   5.750   0.4348   0.07432   0.06501   0.0003   0.4608   1.0000
   6.000   0.3862   0.07947   0.07006   0.0036   0.4594   1.0000
   6.250   0.3610   0.08349   0.07403   0.0056   0.4589   1.0000
   6.500   0.3499   0.08707   0.07757   0.0067   0.4600   1.0000
   6.750   0.3490   0.09042   0.08089   0.0072   0.4614   1.0000
   7.000   0.3598   0.09363   0.08411   0.0071   0.4629   1.0000
   7.500   0.2215   0.10689   0.09738   0.0059   0.5612   1.0000
   7.750   0.2483   0.11001   0.10049   0.0050   0.5526   1.0000
   8.000   0.2590   0.11322   0.10368   0.0048   0.5479   1.0000
   8.250   0.2511   0.11365   0.10410   0.0065   0.5354   1.0000
   8.500   0.2923   0.11867   0.10914   0.0045   0.5286   1.0000
   8.750   0.2670   0.11834   0.10878   0.0069   0.5186   1.0000
   9.000   0.2934   0.12166   0.11212   0.0061   0.5090   1.0000
   9.250   0.2892   0.12348   0.11393   0.0068   0.5003   1.0000
   9.500   0.3456   0.12967   0.12016   0.0047   0.4844   1.0000
   9.750   0.3128   0.12771   0.11818   0.0073   0.4696   1.0000
  10.000   0.3240   0.12973   0.12022   0.0078   0.4497   1.0000
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