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E195 (11.82%) (e195-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: E195 (11.82%) (e195-il)
Reynolds number: 100,000
Max Cl/Cd: 56.26 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e195-il-100000-n5.txt
Download as CSV file: xf-e195-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E195  (11.82%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3861   0.09211   0.08715  -0.0429   1.0000   0.0303
  -9.500  -0.3902   0.08749   0.08261  -0.0448   1.0000   0.0297
  -9.250  -0.3978   0.08233   0.07753  -0.0471   1.0000   0.0291
  -8.750  -0.4790   0.06052   0.05582  -0.0613   1.0000   0.0263
  -8.500  -0.5014   0.05664   0.05182  -0.0607   1.0000   0.0261
  -8.250  -0.5168   0.05385   0.04896  -0.0585   1.0000   0.0260
  -8.000  -0.5084   0.04832   0.04307  -0.0628   0.9877   0.0258
  -7.750  -0.4911   0.04301   0.03723  -0.0670   0.9739   0.0258
  -7.500  -0.4706   0.03857   0.03222  -0.0697   0.9608   0.0259
  -7.250  -0.4470   0.03493   0.02800  -0.0715   0.9485   0.0260
  -7.000  -0.4214   0.03187   0.02452  -0.0729   0.9367   0.0263
  -6.750  -0.3930   0.02964   0.02205  -0.0743   0.9262   0.0273
  -6.500  -0.3638   0.02805   0.02019  -0.0754   0.9151   0.0289
  -6.250  -0.3353   0.02644   0.01829  -0.0761   0.9032   0.0306
  -6.000  -0.3063   0.02475   0.01628  -0.0765   0.8921   0.0316
  -5.750  -0.2768   0.02326   0.01454  -0.0768   0.8818   0.0326
  -5.500  -0.2487   0.02205   0.01310  -0.0769   0.8709   0.0338
  -5.250  -0.2237   0.02088   0.01185  -0.0766   0.8592   0.0355
  -5.000  -0.1979   0.02003   0.01089  -0.0763   0.8482   0.0380
  -4.750  -0.1711   0.01931   0.00998  -0.0760   0.8385   0.0430
  -4.500  -0.1463   0.01854   0.00916  -0.0756   0.8279   0.0511
  -4.250  -0.1215   0.01774   0.00830  -0.0750   0.8178   0.0674
  -4.000  -0.0960   0.01700   0.00767  -0.0747   0.8094   0.1031
  -3.750  -0.0719   0.01635   0.00730  -0.0744   0.7997   0.1679
  -3.500  -0.0479   0.01571   0.00701  -0.0740   0.7912   0.2522
  -3.250  -0.0230   0.01526   0.00673  -0.0736   0.7831   0.3227
  -3.000   0.0014   0.01494   0.00658  -0.0730   0.7749   0.3950
  -2.750   0.0267   0.01469   0.00643  -0.0723   0.7676   0.4628
  -2.500   0.0514   0.01450   0.00633  -0.0715   0.7598   0.5199
  -2.250   0.0770   0.01433   0.00620  -0.0708   0.7531   0.5713
  -2.000   0.1021   0.01420   0.00613  -0.0700   0.7458   0.6207
  -1.750   0.1275   0.01407   0.00606  -0.0691   0.7393   0.6706
  -1.500   0.1527   0.01397   0.00601  -0.0681   0.7328   0.7211
  -1.250   0.1786   0.01388   0.00599  -0.0672   0.7262   0.7744
  -1.000   0.2091   0.01382   0.00594  -0.0670   0.7208   0.8307
  -0.750   0.2472   0.01382   0.00593  -0.0686   0.7139   0.8857
  -0.500   0.2923   0.01383   0.00582  -0.0718   0.7085   0.9316
  -0.250   0.3368   0.01389   0.00576  -0.0753   0.7022   0.9686
   0.000   0.3848   0.01390   0.00564  -0.0796   0.6961   0.9956
   0.250   0.4120   0.01400   0.00560  -0.0798   0.6907   1.0000
   0.500   0.4339   0.01415   0.00568  -0.0790   0.6841   1.0000
   0.750   0.4577   0.01428   0.00570  -0.0783   0.6789   1.0000
   1.000   0.4804   0.01446   0.00582  -0.0775   0.6727   1.0000
   1.250   0.5039   0.01463   0.00592  -0.0768   0.6669   1.0000
   1.500   0.5287   0.01479   0.00600  -0.0762   0.6621   1.0000
   1.750   0.5515   0.01501   0.00621  -0.0755   0.6555   1.0000
   2.000   0.5763   0.01518   0.00633  -0.0749   0.6504   1.0000
   2.250   0.6005   0.01539   0.00654  -0.0743   0.6448   1.0000
   2.500   0.6245   0.01561   0.00676  -0.0737   0.6387   1.0000
   2.750   0.6504   0.01578   0.00689  -0.0733   0.6340   1.0000
   3.250   0.6987   0.01625   0.00743  -0.0721   0.6218   1.0000
   3.500   0.7237   0.01647   0.00767  -0.0716   0.6163   1.0000
   3.750   0.7475   0.01673   0.00798  -0.0710   0.6095   1.0000
   4.000   0.7740   0.01688   0.00815  -0.0707   0.6044   1.0000
   4.250   0.7966   0.01718   0.00855  -0.0699   0.5964   1.0000
   4.500   0.8228   0.01732   0.00871  -0.0694   0.5903   1.0000
   4.750   0.8454   0.01758   0.00908  -0.0686   0.5816   1.0000
   5.000   0.8717   0.01768   0.00922  -0.0681   0.5746   1.0000
   5.250   0.8939   0.01792   0.00958  -0.0672   0.5645   1.0000
   5.500   0.9177   0.01808   0.00983  -0.0664   0.5551   1.0000
   5.750   0.9430   0.01814   0.00994  -0.0657   0.5458   1.0000
   6.000   0.9649   0.01833   0.01028  -0.0646   0.5338   1.0000
   6.250   0.9871   0.01849   0.01056  -0.0636   0.5214   1.0000
   6.500   1.0093   0.01863   0.01081  -0.0624   0.5078   1.0000
   6.750   1.0310   0.01877   0.01106  -0.0613   0.4928   1.0000
   7.000   1.0523   0.01892   0.01131  -0.0600   0.4759   1.0000
   7.250   1.0723   0.01913   0.01162  -0.0585   0.4565   1.0000
   7.500   1.0909   0.01939   0.01196  -0.0569   0.4337   1.0000
   7.750   1.1078   0.01973   0.01233  -0.0550   0.4054   1.0000
   8.000   1.1222   0.02021   0.01276  -0.0528   0.3699   1.0000
   8.250   1.1330   0.02091   0.01332  -0.0501   0.3279   1.0000
   8.500   1.1391   0.02191   0.01412  -0.0470   0.2833   1.0000
   8.750   1.1402   0.02319   0.01515  -0.0435   0.2394   1.0000
   9.000   1.1364   0.02462   0.01633  -0.0394   0.2003   1.0000
   9.250   1.1330   0.02621   0.01769  -0.0358   0.1654   1.0000
   9.750   1.1282   0.02979   0.02087  -0.0302   0.1073   1.0000
  10.000   1.1279   0.03168   0.02263  -0.0282   0.0841   1.0000
  10.250   1.1297   0.03355   0.02446  -0.0264   0.0690   1.0000
  10.500   1.1309   0.03558   0.02649  -0.0249   0.0550   1.0000
  10.750   1.1304   0.03787   0.02876  -0.0234   0.0434   1.0000
  11.000   1.1291   0.04036   0.03125  -0.0221   0.0360   1.0000
  11.250   1.1294   0.04277   0.03373  -0.0211   0.0308   1.0000
  11.500   1.1284   0.04541   0.03642  -0.0202   0.0279   1.0000
  11.750   1.1300   0.04785   0.03901  -0.0194   0.0254   1.0000
  12.000   1.1305   0.05046   0.04173  -0.0189   0.0238   1.0000
  12.250   1.1298   0.05328   0.04465  -0.0184   0.0227   1.0000
  12.500   1.1270   0.05639   0.04783  -0.0180   0.0217   1.0000
  12.750   1.1287   0.05907   0.05068  -0.0177   0.0211   1.0000
  13.000   1.1306   0.06181   0.05358  -0.0173   0.0204   1.0000
  13.250   1.1327   0.06459   0.05650  -0.0170   0.0197   1.0000
  13.500   1.1349   0.06743   0.05949  -0.0168   0.0190   1.0000
  13.750   1.1380   0.07024   0.06247  -0.0167   0.0186   1.0000
  14.000   1.1399   0.07326   0.06563  -0.0167   0.0181   1.0000
  14.250   1.1404   0.07650   0.06898  -0.0171   0.0175   1.0000
  14.500   1.1415   0.07979   0.07238  -0.0175   0.0172   1.0000
  14.750   1.1409   0.08331   0.07599  -0.0181   0.0167   1.0000
  15.000   1.1396   0.08719   0.08007  -0.0188   0.0164   1.0000
  15.250   1.1343   0.09184   0.08500  -0.0202   0.0159   1.0000
  15.500   1.1289   0.09662   0.09001  -0.0218   0.0156   1.0000
  15.750   1.1219   0.10175   0.09536  -0.0238   0.0154   1.0000
  16.000   1.1128   0.10748   0.10132  -0.0263   0.0153   1.0000
  16.250   1.1018   0.11378   0.10785  -0.0294   0.0153   1.0000
  16.500   1.0889   0.12074   0.11503  -0.0331   0.0152   1.0000
  16.750   1.0742   0.12842   0.12292  -0.0374   0.0153   1.0000
  17.000   1.0575   0.13704   0.13175  -0.0426   0.0153   1.0000
  17.250   1.0401   0.14642   0.14130  -0.0485   0.0156   1.0000
  17.500   1.0193   0.15754   0.15257  -0.0554   0.0158   1.0000
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