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EPPLER 521 AIRFOIL (e521-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 521 AIRFOIL (e521-il)
Reynolds number: 200,000
Max Cl/Cd: 44.42 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e521-il-200000.txt
Download as CSV file: xf-e521-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 521 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.7198   0.10012   0.09666  -0.0189   1.0000   0.0225
 -14.750  -0.9025   0.08019   0.07590  -0.0302   1.0000   0.0177
 -14.500  -0.9208   0.07378   0.06929  -0.0337   1.0000   0.0177
 -14.250  -0.9152   0.07180   0.06738  -0.0350   1.0000   0.0189
 -14.000  -0.9373   0.06557   0.06088  -0.0377   1.0000   0.0188
 -13.750  -0.9601   0.05939   0.05435  -0.0392   1.0000   0.0182
 -13.500  -0.9562   0.05779   0.05276  -0.0399   1.0000   0.0195
 -13.250  -0.9636   0.05453   0.04934  -0.0403   1.0000   0.0202
 -13.000  -0.9737   0.05080   0.04537  -0.0401   1.0000   0.0204
 -12.750  -0.9791   0.04774   0.04209  -0.0396   1.0000   0.0208
 -12.500  -0.9829   0.04487   0.03898  -0.0387   1.0000   0.0214
 -12.250  -0.9839   0.04228   0.03613  -0.0376   1.0000   0.0220
 -12.000  -0.9826   0.04017   0.03377  -0.0363   1.0000   0.0227
 -11.750  -0.9763   0.03649   0.02990  -0.0351   1.0000   0.0242
 -11.500  -0.9685   0.03484   0.02823  -0.0341   1.0000   0.0258
 -11.250  -0.9605   0.03350   0.02680  -0.0330   1.0000   0.0279
 -11.000  -0.9515   0.03228   0.02539  -0.0316   1.0000   0.0302
 -10.750  -0.9383   0.02981   0.02287  -0.0306   1.0000   0.0332
 -10.500  -0.9275   0.02863   0.02167  -0.0294   1.0000   0.0364
 -10.250  -0.9147   0.02769   0.02057  -0.0281   1.0000   0.0400
 -10.000  -0.9022   0.02582   0.01871  -0.0269   1.0000   0.0442
  -9.750  -0.8887   0.02488   0.01773  -0.0257   1.0000   0.0489
  -9.500  -0.8765   0.02359   0.01641  -0.0242   1.0000   0.0542
  -9.250  -0.8647   0.02271   0.01553  -0.0226   1.0000   0.0605
  -9.000  -0.8577   0.02174   0.01458  -0.0202   1.0000   0.0670
  -8.750  -0.8677   0.02145   0.01430  -0.0146   1.0000   0.0711
  -8.500  -0.8620   0.02072   0.01354  -0.0119   0.9964   0.0793
  -8.250  -0.8347   0.01964   0.01252  -0.0133   0.9898   0.0961
  -8.000  -0.8052   0.01867   0.01157  -0.0149   0.9843   0.1175
  -7.750  -0.7746   0.01777   0.01075  -0.0167   0.9798   0.1436
  -7.500  -0.7472   0.01698   0.01007  -0.0178   0.9742   0.1713
  -7.250  -0.7176   0.01621   0.00945  -0.0193   0.9699   0.2030
  -7.000  -0.6911   0.01556   0.00892  -0.0201   0.9649   0.2359
  -6.750  -0.6658   0.01499   0.00844  -0.0204   0.9593   0.2715
  -6.500  -0.6381   0.01439   0.00800  -0.0213   0.9552   0.3110
  -6.250  -0.6166   0.01394   0.00768  -0.0207   0.9497   0.3488
  -6.000  -0.5940   0.01352   0.00739  -0.0203   0.9443   0.3897
  -5.750  -0.5688   0.01310   0.00712  -0.0202   0.9404   0.4327
  -5.500  -0.5496   0.01281   0.00697  -0.0189   0.9349   0.4724
  -5.250  -0.5273   0.01255   0.00686  -0.0180   0.9299   0.5138
  -5.000  -0.5020   0.01238   0.00683  -0.0175   0.9262   0.5545
  -4.750  -0.4797   0.01237   0.00693  -0.0164   0.9215   0.5911
  -4.500  -0.4557   0.01245   0.00706  -0.0156   0.9167   0.6223
  -4.250  -0.4287   0.01262   0.00724  -0.0151   0.9130   0.6481
  -4.000  -0.4024   0.01287   0.00748  -0.0144   0.9091   0.6689
  -3.750  -0.3780   0.01316   0.00774  -0.0136   0.9039   0.6861
  -3.500  -0.3515   0.01344   0.00797  -0.0129   0.8997   0.7011
  -3.250  -0.3239   0.01374   0.00822  -0.0123   0.8963   0.7143
  -3.000  -0.3004   0.01404   0.00850  -0.0114   0.8904   0.7262
  -2.750  -0.2751   0.01428   0.00868  -0.0106   0.8857   0.7381
  -2.500  -0.2472   0.01458   0.00895  -0.0099   0.8821   0.7468
  -2.250  -0.2233   0.01484   0.00921  -0.0090   0.8760   0.7559
  -2.000  -0.1988   0.01498   0.00930  -0.0081   0.8709   0.7665
  -1.750  -0.1711   0.01524   0.00955  -0.0072   0.8671   0.7728
  -1.500  -0.1486   0.01539   0.00968  -0.0062   0.8600   0.7823
  -1.250  -0.1219   0.01556   0.00985  -0.0052   0.8552   0.7889
  -1.000  -0.0985   0.01567   0.00994  -0.0042   0.8493   0.7973
  -0.750  -0.0732   0.01579   0.01007  -0.0032   0.8431   0.8039
  -0.500  -0.0483   0.01578   0.01002  -0.0021   0.8386   0.8116
  -0.250  -0.0244   0.01591   0.01018  -0.0011   0.8306   0.8176
   0.000   0.0000   0.01582   0.01006   0.0000   0.8253   0.8253
   0.250   0.0244   0.01591   0.01018   0.0011   0.8176   0.8306
   0.500   0.0483   0.01578   0.01002   0.0021   0.8116   0.8386
   0.750   0.0732   0.01580   0.01007   0.0032   0.8039   0.8431
   1.000   0.0985   0.01567   0.00994   0.0042   0.7973   0.8493
   1.250   0.1219   0.01556   0.00985   0.0052   0.7889   0.8552
   1.500   0.1486   0.01539   0.00969   0.0062   0.7823   0.8600
   1.750   0.1711   0.01524   0.00955   0.0072   0.7728   0.8671
   2.000   0.1988   0.01498   0.00930   0.0081   0.7665   0.8709
   2.250   0.2234   0.01484   0.00921   0.0090   0.7559   0.8760
   2.500   0.2472   0.01457   0.00895   0.0099   0.7467   0.8821
   2.750   0.2751   0.01428   0.00868   0.0106   0.7381   0.8857
   3.000   0.3005   0.01404   0.00850   0.0114   0.7262   0.8904
   3.250   0.3240   0.01374   0.00823   0.0123   0.7142   0.8963
   3.500   0.3515   0.01344   0.00798   0.0129   0.7012   0.8996
   3.750   0.3781   0.01316   0.00775   0.0135   0.6861   0.9039
   4.000   0.4024   0.01287   0.00748   0.0144   0.6689   0.9091
   4.250   0.4287   0.01262   0.00724   0.0151   0.6481   0.9130
   4.500   0.4557   0.01246   0.00705   0.0155   0.6224   0.9167
   4.750   0.4797   0.01237   0.00693   0.0164   0.5912   0.9215
   5.000   0.5020   0.01238   0.00683   0.0175   0.5547   0.9262
   5.250   0.5273   0.01255   0.00686   0.0180   0.5138   0.9299
   5.500   0.5497   0.01281   0.00697   0.0189   0.4727   0.9348
   5.750   0.5688   0.01311   0.00712   0.0202   0.4327   0.9403
   6.000   0.5940   0.01352   0.00739   0.0203   0.3897   0.9443
   6.250   0.6166   0.01394   0.00768   0.0207   0.3488   0.9497
   6.500   0.6381   0.01439   0.00800   0.0213   0.3110   0.9552
   6.750   0.6657   0.01499   0.00844   0.0205   0.2715   0.9593
   7.000   0.6911   0.01556   0.00892   0.0201   0.2362   0.9649
   7.250   0.7176   0.01621   0.00945   0.0193   0.2032   0.9699
   7.500   0.7472   0.01698   0.01007   0.0178   0.1714   0.9741
   7.750   0.7747   0.01777   0.01075   0.0167   0.1433   0.9798
   8.000   0.8052   0.01867   0.01156   0.0149   0.1175   0.9843
   8.250   0.8347   0.01963   0.01251   0.0133   0.0959   0.9897
   8.500   0.8619   0.02073   0.01354   0.0119   0.0791   0.9965
   8.750   0.8677   0.02146   0.01430   0.0146   0.0710   1.0000
   9.000   0.8576   0.02173   0.01457   0.0202   0.0670   1.0000
   9.250   0.8645   0.02270   0.01552   0.0227   0.0604   1.0000
   9.500   0.8763   0.02358   0.01640   0.0243   0.0542   1.0000
   9.750   0.8885   0.02491   0.01775   0.0257   0.0491   1.0000
  10.000   0.9021   0.02582   0.01871   0.0269   0.0443   1.0000
  10.250   0.9141   0.02763   0.02051   0.0282   0.0400   1.0000
  10.500   0.9275   0.02866   0.02170   0.0294   0.0366   1.0000
  10.750   0.9381   0.02981   0.02287   0.0306   0.0332   1.0000
  11.000   0.9513   0.03227   0.02538   0.0317   0.0302   1.0000
  11.250   0.9611   0.03361   0.02691   0.0330   0.0280   1.0000
  11.500   0.9693   0.03497   0.02838   0.0342   0.0260   1.0000
  11.750   0.9762   0.03651   0.02992   0.0352   0.0241   1.0000
  12.000   0.9827   0.04017   0.03376   0.0363   0.0227   1.0000
  12.250   0.9843   0.04223   0.03607   0.0376   0.0221   1.0000
  12.500   0.9839   0.04483   0.03893   0.0387   0.0215   1.0000
  12.750   0.9799   0.04753   0.04186   0.0396   0.0206   1.0000
  13.000   0.9738   0.05078   0.04535   0.0401   0.0204   1.0000
  13.250   0.9694   0.05349   0.04821   0.0402   0.0194   1.0000
  13.500   0.9627   0.05679   0.05170   0.0399   0.0190   1.0000
  13.750   0.9490   0.06127   0.05641   0.0391   0.0189   1.0000
  14.000   0.9268   0.06722   0.06265   0.0371   0.0193   1.0000
  14.250   0.9192   0.07121   0.06676   0.0352   0.0188   1.0000
  14.500   0.9104   0.07561   0.07125   0.0328   0.0182   1.0000
  14.750   0.8595   0.08847   0.08453   0.0251   0.0196   1.0000
  15.000   0.8187   0.10119   0.09750   0.0168   0.0209   1.0000
  15.250   0.7790   0.11514   0.11161   0.0080   0.0219   1.0000
  15.500   0.7505   0.12700   0.12350   0.0015   0.0228   1.0000
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