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NACA 0021 (naca0021-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0021 (naca0021-il)
Reynolds number: 50,000
Max Cl/Cd: 25.19 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0021-il-50000-n5.txt
Download as CSV file: xf-naca0021-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.6667   0.10156   0.09168  -0.0381   1.0000   0.1803
 -13.500  -0.6363   0.10347   0.09361  -0.0363   1.0000   0.1821
 -13.250  -0.7672   0.07934   0.06924  -0.0463   1.0000   0.1952
 -13.000  -0.7088   0.08477   0.07480  -0.0430   1.0000   0.1972
 -12.750  -0.6887   0.08472   0.07477  -0.0421   1.0000   0.2010
 -12.500  -0.8465   0.06192   0.05146  -0.0489   1.0000   0.2110
 -12.250  -0.8120   0.06309   0.05276  -0.0478   1.0000   0.2158
 -12.000  -0.8439   0.05771   0.04721  -0.0474   1.0000   0.2214
 -11.750  -0.8795   0.05278   0.04205  -0.0457   1.0000   0.2264
 -11.500  -0.8530   0.05291   0.04233  -0.0449   1.0000   0.2319
 -11.250  -0.8659   0.05025   0.03956  -0.0428   1.0000   0.2376
 -11.000  -0.8862   0.04743   0.03658  -0.0397   1.0000   0.2430
 -10.750  -0.8660   0.04715   0.03644  -0.0385   1.0000   0.2489
 -10.500  -0.8759   0.04538   0.03457  -0.0352   1.0000   0.2549
 -10.250  -0.8889   0.04369   0.03279  -0.0310   1.0000   0.2606
 -10.000  -0.8754   0.04327   0.03249  -0.0290   1.0000   0.2667
  -9.750  -0.8871   0.04205   0.03122  -0.0243   1.0000   0.2728
  -9.500  -0.8994   0.04096   0.03008  -0.0190   1.0000   0.2785
  -9.250  -0.8902   0.04057   0.02980  -0.0162   1.0000   0.2848
  -9.000  -0.8984   0.03962   0.02878  -0.0113   1.0000   0.2915
  -8.750  -0.8988   0.03888   0.02804  -0.0074   1.0000   0.2981
  -8.500  -0.8933   0.03841   0.02764  -0.0041   1.0000   0.3051
  -8.250  -0.9011   0.03748   0.02659   0.0008   1.0000   0.3127
  -8.000  -0.8913   0.03714   0.02638   0.0036   1.0000   0.3197
  -7.750  -0.8897   0.03656   0.02578   0.0074   1.0000   0.3277
  -7.500  -0.8875   0.03595   0.02513   0.0110   1.0000   0.3357
  -7.250  -0.8793   0.03562   0.02487   0.0139   1.0000   0.3437
  -7.000  -0.8796   0.03492   0.02406   0.0178   1.0000   0.3529
  -6.750  -0.8672   0.03474   0.02402   0.0201   1.0000   0.3609
  -6.500  -0.8577   0.03413   0.02327   0.0222   0.9979   0.3719
  -6.250  -0.8182   0.03399   0.02326   0.0195   0.9902   0.3836
  -6.000  -0.7838   0.03358   0.02282   0.0175   0.9808   0.3967
  -5.750  -0.7504   0.03321   0.02241   0.0157   0.9713   0.4101
  -5.500  -0.7104   0.03305   0.02233   0.0130   0.9630   0.4227
  -5.250  -0.6811   0.03263   0.02186   0.0121   0.9518   0.4360
  -5.000  -0.6443   0.03243   0.02169   0.0101   0.9428   0.4495
  -4.750  -0.6102   0.03222   0.02152   0.0087   0.9322   0.4620
  -4.500  -0.5808   0.03185   0.02109   0.0079   0.9212   0.4764
  -4.250  -0.5413   0.03174   0.02107   0.0058   0.9118   0.4893
  -4.000  -0.5109   0.03152   0.02087   0.0052   0.9004   0.5024
  -3.500  -0.4417   0.03115   0.02055   0.0028   0.8793   0.5296
  -3.250  -0.4032   0.03085   0.02026   0.0009   0.8703   0.5440
  -3.000  -0.3775   0.03068   0.02010   0.0014   0.8574   0.5575
  -2.750  -0.3360   0.03051   0.01999  -0.0006   0.8487   0.5707
  -2.500  -0.3145   0.03028   0.01974   0.0006   0.8350   0.5848
  -2.250  -0.2724   0.03012   0.01963  -0.0013   0.8265   0.5981
  -2.000  -0.2483   0.03004   0.01959  -0.0003   0.8124   0.6108
  -1.750  -0.2131   0.02966   0.01916  -0.0012   0.8037   0.6265
  -1.500  -0.1843   0.02980   0.01940  -0.0007   0.7892   0.6373
  -1.250  -0.1500   0.02951   0.01909  -0.0013   0.7797   0.6519
  -1.000  -0.1228   0.02956   0.01918  -0.0006   0.7656   0.6643
  -0.750  -0.0907   0.02947   0.01910  -0.0007   0.7539   0.6772
  -0.500  -0.0648   0.02929   0.01889   0.0001   0.7415   0.6921
  -0.250  -0.0304   0.02945   0.01911  -0.0002   0.7284   0.7028
   0.000   0.0000   0.02923   0.01884   0.0000   0.7173   0.7173
   0.250   0.0304   0.02945   0.01911   0.0002   0.7028   0.7284
   0.500   0.0649   0.02929   0.01889  -0.0001   0.6921   0.7415
   0.750   0.0907   0.02947   0.01910   0.0007   0.6772   0.7539
   1.000   0.1228   0.02956   0.01918   0.0006   0.6644   0.7656
   1.250   0.1499   0.02951   0.01908   0.0013   0.6519   0.7797
   1.500   0.1843   0.02980   0.01940   0.0007   0.6373   0.7893
   1.750   0.2131   0.02966   0.01916   0.0012   0.6265   0.8037
   2.000   0.2483   0.03004   0.01959   0.0003   0.6108   0.8124
   2.250   0.2724   0.03012   0.01963   0.0013   0.5981   0.8265
   2.500   0.3144   0.03028   0.01974  -0.0005   0.5848   0.8350
   2.750   0.3359   0.03050   0.01998   0.0006   0.5707   0.8487
   3.000   0.3774   0.03067   0.02009  -0.0013   0.5576   0.8574
   3.250   0.4032   0.03085   0.02026  -0.0009   0.5440   0.8703
   3.500   0.4417   0.03114   0.02055  -0.0027   0.5296   0.8794
   3.750   0.4754   0.03114   0.02044  -0.0035   0.5179   0.8910
   4.000   0.5108   0.03152   0.02086  -0.0052   0.5024   0.9004
   4.250   0.5413   0.03174   0.02107  -0.0058   0.4894   0.9119
   4.500   0.5807   0.03184   0.02109  -0.0079   0.4764   0.9213
   4.750   0.6102   0.03221   0.02152  -0.0087   0.4621   0.9322
   5.000   0.6442   0.03243   0.02168  -0.0101   0.4495   0.9429
   5.250   0.6812   0.03263   0.02185  -0.0121   0.4360   0.9519
   5.500   0.7106   0.03304   0.02232  -0.0131   0.4227   0.9631
   5.750   0.7504   0.03320   0.02240  -0.0157   0.4101   0.9714
   6.000   0.7840   0.03357   0.02281  -0.0175   0.3967   0.9809
   6.250   0.8183   0.03398   0.02325  -0.0196   0.3836   0.9903
   6.500   0.8579   0.03412   0.02326  -0.0222   0.3719   0.9980
   6.750   0.8670   0.03473   0.02400  -0.0201   0.3609   1.0000
   7.000   0.8794   0.03491   0.02405  -0.0177   0.3530   1.0000
   7.250   0.8792   0.03561   0.02486  -0.0139   0.3438   1.0000
   7.500   0.8874   0.03594   0.02512  -0.0110   0.3357   1.0000
   7.750   0.8896   0.03655   0.02576  -0.0073   0.3277   1.0000
   8.000   0.8912   0.03713   0.02636  -0.0036   0.3198   1.0000
   8.250   0.9011   0.03746   0.02657  -0.0008   0.3127   1.0000
   8.500   0.8933   0.03840   0.02763   0.0041   0.3051   1.0000
   8.750   0.8989   0.03886   0.02803   0.0074   0.2981   1.0000
   9.000   0.8985   0.03960   0.02876   0.0113   0.2915   1.0000
   9.250   0.8904   0.04056   0.02978   0.0162   0.2848   1.0000
   9.500   0.8998   0.04095   0.03006   0.0190   0.2784   1.0000
   9.750   0.8874   0.04204   0.03120   0.0242   0.2727   1.0000
  10.000   0.8759   0.04325   0.03247   0.0290   0.2667   1.0000
  10.250   0.8896   0.04366   0.03276   0.0310   0.2605   1.0000
  10.500   0.8764   0.04536   0.03455   0.0351   0.2549   1.0000
  10.750   0.8669   0.04712   0.03640   0.0384   0.2489   1.0000
  11.000   0.8875   0.04738   0.03652   0.0395   0.2430   1.0000
  11.250   0.8667   0.05023   0.03954   0.0427   0.2375   1.0000
  11.500   0.8545   0.05284   0.04226   0.0448   0.2318   1.0000
  11.750   0.8816   0.05268   0.04194   0.0456   0.2263   1.0000
  12.000   0.8451   0.05767   0.04717   0.0473   0.2213   1.0000
  12.250   0.8147   0.06290   0.05257   0.0477   0.2157   1.0000
  12.500   0.8500   0.06167   0.05120   0.0488   0.2109   1.0000
  12.750   0.6927   0.08431   0.07435   0.0421   0.2011   1.0000
  13.000   0.7124   0.08443   0.07445   0.0430   0.1973   1.0000
  13.250   0.7718   0.07889   0.06878   0.0463   0.1952   1.0000
  13.500   0.6389   0.10329   0.09343   0.0361   0.1821   1.0000
  13.750   0.6696   0.10133   0.09145   0.0380   0.1803   1.0000
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