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NACA 0021 (naca0021-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 0021 (naca0021-il)
Reynolds number: 50,000
Max Cl/Cd: 19.14 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca0021-il-50000.txt
Download as CSV file: xf-naca0021-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0021                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3112   0.12560   0.11631  -0.0086   1.0000   0.4567
 -10.250  -0.2843   0.12215   0.11285  -0.0091   1.0000   0.4677
 -10.000  -0.3247   0.12282   0.11357  -0.0069   1.0000   0.4753
  -9.750  -0.2690   0.11676   0.10748  -0.0091   1.0000   0.4852
  -9.500  -0.2967   0.11674   0.10749  -0.0069   1.0000   0.4959
  -9.250  -0.2590   0.11173   0.10247  -0.0085   1.0000   0.5031
  -9.000  -0.2672   0.11069   0.10145  -0.0071   1.0000   0.5161
  -8.750  -0.3659   0.09402   0.08467  -0.0151   1.0000   0.4012
  -8.500  -0.3767   0.09022   0.08089  -0.0147   1.0000   0.4051
  -8.250  -0.4033   0.08534   0.07605  -0.0140   1.0000   0.4082
  -8.000  -0.4715   0.07745   0.06824  -0.0124   1.0000   0.4117
  -7.750  -0.4041   0.08041   0.07119  -0.0111   1.0000   0.4230
  -7.500  -0.4468   0.07517   0.06603  -0.0087   1.0000   0.4287
  -7.250  -0.6906   0.05799   0.04907   0.0058   1.0000   0.4299
  -7.000  -0.8363   0.04920   0.04010   0.0218   1.0000   0.4330
  -6.750  -0.7209   0.05447   0.04562   0.0155   1.0000   0.4459
  -6.500  -0.8240   0.04776   0.03872   0.0279   1.0000   0.4524
  -6.250  -0.7822   0.04914   0.04024   0.0279   1.0000   0.4625
  -6.000  -0.8189   0.04596   0.03692   0.0346   1.0000   0.4728
  -5.750  -0.7958   0.04632   0.03739   0.0361   1.0000   0.4828
  -5.500  -0.8154   0.04402   0.03493   0.0410   1.0000   0.4947
  -5.250  -0.7909   0.04456   0.03561   0.0424   1.0000   0.5048
  -5.000  -0.8085   0.04222   0.03308   0.0468   1.0000   0.5182
  -4.750  -0.7788   0.04326   0.03431   0.0478   1.0000   0.5282
  -4.500  -0.7837   0.04171   0.03266   0.0511   1.0000   0.5417
  -4.250  -0.7645   0.04213   0.03318   0.0527   1.0000   0.5532
  -4.000  -0.7592   0.04136   0.03238   0.0552   1.0000   0.5662
  -3.750  -0.7521   0.04079   0.03179   0.0574   1.0000   0.5804
  -3.500  -0.7355   0.04107   0.03215   0.0591   1.0000   0.5920
  -3.250  -0.7304   0.04029   0.03132   0.0612   1.0000   0.6071
  -3.000  -0.6987   0.04088   0.03197   0.0601   0.9946   0.6226
  -2.750  -0.6416   0.04215   0.03328   0.0550   0.9804   0.6399
  -2.500  -0.5915   0.04298   0.03411   0.0507   0.9657   0.6576
  -2.250  -0.5503   0.04341   0.03453   0.0478   0.9511   0.6755
  -2.000  -0.5136   0.04365   0.03474   0.0454   0.9362   0.6940
  -1.750  -0.4532   0.04526   0.03640   0.0410   0.9214   0.7085
  -1.500  -0.3880   0.04646   0.03760   0.0352   0.9073   0.7247
  -1.250  -0.3540   0.04667   0.03780   0.0338   0.8918   0.7416
  -1.000  -0.3318   0.04665   0.03775   0.0340   0.8768   0.7596
  -0.750  -0.2325   0.04876   0.03989   0.0239   0.8613   0.7709
  -0.500  -0.1461   0.04940   0.04050   0.0147   0.8477   0.7869
  -0.250  -0.1393   0.04928   0.04038   0.0172   0.8314   0.8043
   0.000   0.0000   0.05040   0.04152   0.0000   0.8152   0.8152
   0.250   0.1392   0.04928   0.04038  -0.0172   0.8043   0.8314
   0.500   0.1463   0.04939   0.04050  -0.0147   0.7869   0.8477
   0.750   0.2325   0.04876   0.03988  -0.0238   0.7709   0.8613
   1.000   0.3317   0.04665   0.03775  -0.0339   0.7596   0.8768
   1.250   0.3539   0.04667   0.03779  -0.0338   0.7416   0.8918
   1.500   0.3878   0.04646   0.03760  -0.0352   0.7247   0.9073
   1.750   0.4531   0.04526   0.03639  -0.0410   0.7085   0.9215
   2.000   0.5135   0.04365   0.03474  -0.0454   0.6941   0.9363
   2.250   0.5504   0.04340   0.03452  -0.0478   0.6755   0.9512
   2.500   0.5915   0.04297   0.03410  -0.0507   0.6576   0.9657
   2.750   0.6416   0.04214   0.03327  -0.0550   0.6399   0.9805
   3.000   0.6987   0.04087   0.03195  -0.0601   0.6226   0.9947
   3.250   0.7301   0.04029   0.03132  -0.0612   0.6072   1.0000
   3.500   0.7353   0.04106   0.03215  -0.0591   0.5920   1.0000
   3.750   0.7520   0.04077   0.03176  -0.0574   0.5804   1.0000
   4.000   0.7589   0.04135   0.03237  -0.0551   0.5662   1.0000
   4.250   0.7643   0.04211   0.03316  -0.0527   0.5532   1.0000
   4.500   0.7834   0.04171   0.03265  -0.0511   0.5418   1.0000
   4.750   0.7786   0.04325   0.03430  -0.0478   0.5283   1.0000
   5.000   0.8081   0.04222   0.03308  -0.0468   0.5183   1.0000
   5.250   0.7906   0.04455   0.03560  -0.0423   0.5049   1.0000
   5.500   0.8155   0.04398   0.03490  -0.0410   0.4947   1.0000
   5.750   0.7955   0.04631   0.03737  -0.0360   0.4828   1.0000
   6.000   0.8190   0.04593   0.03689  -0.0346   0.4728   1.0000
   6.250   0.7819   0.04913   0.04023  -0.0279   0.4626   1.0000
   6.500   0.8243   0.04773   0.03868  -0.0279   0.4524   1.0000
   6.750   0.7216   0.05441   0.04555  -0.0156   0.4459   1.0000
   7.000   0.6677   0.05811   0.04924  -0.0076   0.4388   1.0000
   7.250   0.6916   0.05791   0.04899  -0.0058   0.4299   1.0000
   7.500   0.4474   0.07510   0.06595   0.0087   0.4287   1.0000
   7.750   0.4049   0.08033   0.07110   0.0111   0.4229   1.0000
   8.000   0.4721   0.07739   0.06817   0.0124   0.4117   1.0000
   8.250   0.4039   0.08528   0.07599   0.0140   0.4082   1.0000
   8.500   0.3775   0.09015   0.08082   0.0146   0.4050   1.0000
   8.750   0.3673   0.09391   0.08456   0.0150   0.4010   1.0000
   9.000   0.3997   0.09451   0.08514   0.0162   0.3902   1.0000
   9.250   0.3819   0.09944   0.09006   0.0159   0.3896   1.0000
   9.500   0.3752   0.10386   0.09448   0.0154   0.3901   1.0000
   9.750   0.3820   0.10800   0.09863   0.0147   0.3916   1.0000
  10.250   0.2855   0.12214   0.11284   0.0090   0.4676   1.0000
  10.500   0.3127   0.12563   0.11634   0.0084   0.4566   1.0000
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