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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 200,000
Max Cl/Cd: 81.74 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e212-il-200000.txt
Download as CSV file: xf-e212-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E212  (10.55%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4461   0.09422   0.09072  -0.0382   1.0000   0.0644
  -9.000  -0.4382   0.09241   0.08893  -0.0364   1.0000   0.0658
  -8.750  -0.4383   0.08971   0.08627  -0.0359   1.0000   0.0671
  -8.500  -0.4425   0.08672   0.08333  -0.0358   1.0000   0.0687
  -8.250  -0.4527   0.08335   0.08003  -0.0359   1.0000   0.0705
  -8.000  -0.4702   0.07993   0.07670  -0.0360   1.0000   0.0720
  -7.250  -0.5765   0.04210   0.03772  -0.0599   1.0000   0.0395
  -7.000  -0.5640   0.03207   0.02649  -0.0638   1.0000   0.0331
  -6.750  -0.5413   0.03069   0.02471  -0.0635   1.0000   0.0321
  -6.500  -0.5177   0.02736   0.02102  -0.0643   1.0000   0.0316
  -6.250  -0.4925   0.02495   0.01824  -0.0648   1.0000   0.0315
  -6.000  -0.4671   0.02318   0.01620  -0.0649   1.0000   0.0317
  -5.750  -0.4420   0.02184   0.01465  -0.0648   1.0000   0.0320
  -5.500  -0.4161   0.01983   0.01255  -0.0650   1.0000   0.0331
  -5.250  -0.3912   0.01880   0.01152  -0.0651   1.0000   0.0348
  -5.000  -0.3658   0.01824   0.01089  -0.0651   0.9998   0.0382
  -4.750  -0.3260   0.01731   0.00988  -0.0679   0.9968   0.0416
  -4.500  -0.2854   0.01648   0.00903  -0.0709   0.9939   0.0495
  -4.250  -0.2448   0.01500   0.00795  -0.0743   0.9910   0.1227
  -4.000  -0.2051   0.01465   0.00781  -0.0773   0.9870   0.1875
  -3.750  -0.1653   0.01444   0.00778  -0.0802   0.9832   0.2437
  -3.500  -0.1283   0.01424   0.00773  -0.0825   0.9776   0.2986
  -3.250  -0.0870   0.01414   0.00773  -0.0855   0.9738   0.3462
  -3.000  -0.0515   0.01400   0.00763  -0.0872   0.9675   0.3856
  -2.750  -0.0118   0.01387   0.00759  -0.0897   0.9628   0.4251
  -2.500   0.0262   0.01376   0.00752  -0.0918   0.9576   0.4622
  -2.250   0.0627   0.01359   0.00743  -0.0935   0.9513   0.4956
  -2.000   0.1052   0.01342   0.00734  -0.0964   0.9477   0.5299
  -1.750   0.1371   0.01326   0.00724  -0.0971   0.9395   0.5602
  -1.500   0.1783   0.01304   0.00709  -0.0995   0.9351   0.5920
  -1.250   0.2121   0.01285   0.00698  -0.1005   0.9277   0.6214
  -1.000   0.2512   0.01259   0.00680  -0.1024   0.9224   0.6510
  -0.750   0.2947   0.01226   0.00654  -0.1051   0.9194   0.6804
  -0.500   0.3246   0.01206   0.00641  -0.1051   0.9099   0.7067
  -0.250   0.3670   0.01168   0.00613  -0.1075   0.9063   0.7337
   0.000   0.3997   0.01144   0.00597  -0.1079   0.8977   0.7592
   0.250   0.4393   0.01109   0.00569  -0.1096   0.8920   0.7857
   0.500   0.4694   0.01084   0.00552  -0.1094   0.8818   0.8098
   0.750   0.5047   0.01052   0.00526  -0.1101   0.8737   0.8345
   1.250   0.5578   0.01008   0.00491  -0.1080   0.8482   0.8861
   1.500   0.5806   0.00986   0.00472  -0.1061   0.8337   0.9161
   1.750   0.6078   0.00961   0.00448  -0.1052   0.8183   0.9548
   2.000   0.6490   0.00947   0.00431  -0.1078   0.8015   1.0000
   2.250   0.6814   0.00952   0.00429  -0.1087   0.7819   1.0000
   2.500   0.7126   0.00960   0.00430  -0.1093   0.7613   1.0000
   2.750   0.7435   0.00972   0.00430  -0.1098   0.7404   1.0000
   3.000   0.7713   0.00987   0.00440  -0.1097   0.7169   1.0000
   3.250   0.7993   0.01005   0.00448  -0.1095   0.6936   1.0000
   3.500   0.8258   0.01025   0.00460  -0.1091   0.6686   1.0000
   3.750   0.8516   0.01048   0.00476  -0.1085   0.6427   1.0000
   4.000   0.8769   0.01074   0.00493  -0.1079   0.6161   1.0000
   4.250   0.9016   0.01103   0.00511  -0.1071   0.5886   1.0000
   4.500   0.9256   0.01135   0.00533  -0.1063   0.5600   1.0000
   4.750   0.9492   0.01168   0.00559  -0.1053   0.5308   1.0000
   5.000   0.9723   0.01205   0.00587  -0.1043   0.5006   1.0000
   5.250   0.9948   0.01245   0.00617  -0.1033   0.4696   1.0000
   5.500   1.0167   0.01288   0.00651  -0.1021   0.4365   1.0000
   5.750   1.0381   0.01334   0.00688  -0.1009   0.4021   1.0000
   6.000   1.0591   0.01386   0.00728  -0.0997   0.3679   1.0000
   6.250   1.0793   0.01444   0.00772  -0.0984   0.3324   1.0000
   6.500   1.0987   0.01507   0.00822  -0.0970   0.2927   1.0000
   6.750   1.1175   0.01579   0.00875  -0.0955   0.2511   1.0000
   7.000   1.1358   0.01657   0.00934  -0.0941   0.2108   1.0000
   7.250   1.1541   0.01740   0.00999  -0.0927   0.1753   1.0000
   7.500   1.1721   0.01826   0.01071  -0.0913   0.1438   1.0000
   7.750   1.1901   0.01916   0.01148  -0.0899   0.1148   1.0000
   8.000   1.2064   0.02021   0.01237  -0.0883   0.0829   1.0000
   8.250   1.2155   0.02199   0.01386  -0.0855   0.0478   1.0000
   8.500   1.2253   0.02355   0.01539  -0.0826   0.0373   1.0000
   8.750   1.2335   0.02502   0.01693  -0.0795   0.0335   1.0000
   9.000   1.2445   0.02627   0.01826  -0.0769   0.0310   1.0000
   9.250   1.2540   0.02764   0.01970  -0.0743   0.0290   1.0000
   9.500   1.2600   0.02963   0.02170  -0.0715   0.0274   1.0000
   9.750   1.2734   0.03087   0.02308  -0.0695   0.0261   1.0000
  10.000   1.2859   0.03236   0.02469  -0.0675   0.0249   1.0000
  10.250   1.2987   0.03403   0.02647  -0.0657   0.0241   1.0000
  10.500   1.3121   0.03582   0.02836  -0.0640   0.0234   1.0000
  10.750   1.3258   0.03774   0.03039  -0.0625   0.0228   1.0000
  11.000   1.3404   0.03994   0.03272  -0.0613   0.0224   1.0000
  11.250   1.3553   0.04255   0.03549  -0.0601   0.0220   1.0000
  11.500   1.3684   0.04561   0.03876  -0.0589   0.0218   1.0000
  11.750   1.3756   0.04875   0.04216  -0.0572   0.0217   1.0000
  12.000   1.3772   0.05188   0.04557  -0.0550   0.0217   1.0000
  12.250   1.3743   0.05496   0.04893  -0.0527   0.0217   1.0000
  12.500   1.3673   0.05819   0.05245  -0.0505   0.0218   1.0000
  12.750   1.3567   0.06174   0.05630  -0.0487   0.0220   1.0000
  13.000   1.3427   0.06579   0.06066  -0.0474   0.0221   1.0000
  13.250   1.3254   0.07046   0.06563  -0.0468   0.0223   1.0000
  13.500   1.3038   0.07603   0.07153  -0.0473   0.0225   1.0000
  13.750   1.2660   0.08421   0.08015  -0.0500   0.0231   1.0000
  14.000   1.2293   0.09355   0.08985  -0.0546   0.0237   1.0000
  14.250   1.1960   0.10354   0.10012  -0.0606   0.0242   1.0000
  14.500   1.1635   0.11472   0.11152  -0.0682   0.0246   1.0000
  14.750   1.1286   0.12809   0.12509  -0.0778   0.0251   1.0000
  15.000   1.0847   0.14654   0.14366  -0.0907   0.0260   1.0000
  15.250   1.0606   0.16035   0.15748  -0.0989   0.0270   1.0000
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