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EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 297 AIRFOIL (e297-il)
Reynolds number: 50,000
Max Cl/Cd: 28.75 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e297-il-50000-n5.txt
Download as CSV file: xf-e297-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 297 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6528   0.09719   0.09051  -0.0203   1.0000   0.0360
 -11.250  -0.6684   0.08923   0.08255  -0.0257   1.0000   0.0353
 -11.000  -0.6892   0.08177   0.07504  -0.0306   1.0000   0.0348
 -10.750  -0.7096   0.07573   0.06890  -0.0341   1.0000   0.0343
 -10.500  -0.7298   0.07061   0.06365  -0.0360   1.0000   0.0339
 -10.250  -0.7482   0.06626   0.05913  -0.0365   1.0000   0.0336
 -10.000  -0.7651   0.06243   0.05510  -0.0356   1.0000   0.0336
  -9.750  -0.7787   0.05906   0.05150  -0.0337   1.0000   0.0336
  -9.500  -0.7876   0.05549   0.04763  -0.0318   1.0000   0.0340
  -9.250  -0.7903   0.05205   0.04383  -0.0298   1.0000   0.0345
  -9.000  -0.7882   0.04860   0.03998  -0.0279   1.0000   0.0355
  -8.750  -0.7810   0.04527   0.03619  -0.0261   1.0000   0.0371
  -8.500  -0.7707   0.04244   0.03279  -0.0242   1.0000   0.0403
  -8.250  -0.7571   0.04009   0.03043  -0.0232   1.0000   0.0445
  -8.000  -0.7367   0.03747   0.02745  -0.0220   1.0000   0.0491
  -7.750  -0.7155   0.03517   0.02499  -0.0211   1.0000   0.0554
  -7.500  -0.6950   0.03342   0.02299  -0.0199   1.0000   0.0653
  -7.250  -0.6741   0.03155   0.02110  -0.0187   1.0000   0.0746
  -7.000  -0.6570   0.03007   0.01943  -0.0172   1.0000   0.0900
  -6.750  -0.6444   0.02861   0.01811  -0.0152   1.0000   0.1083
  -6.500  -0.6345   0.02723   0.01686  -0.0127   1.0000   0.1335
  -6.250  -0.6283   0.02592   0.01578  -0.0098   1.0000   0.1683
  -6.000  -0.6246   0.02468   0.01485  -0.0065   1.0000   0.2136
  -5.750  -0.6228   0.02350   0.01405  -0.0027   1.0000   0.2718
  -5.500  -0.6212   0.02242   0.01340   0.0012   1.0000   0.3444
  -5.250  -0.6173   0.02156   0.01300   0.0053   1.0000   0.4283
  -5.000  -0.6082   0.02114   0.01299   0.0093   1.0000   0.5165
  -4.750  -0.5935   0.02129   0.01335   0.0131   1.0000   0.5910
  -4.500  -0.5781   0.02168   0.01371   0.0168   1.0000   0.6446
  -4.250  -0.5639   0.02205   0.01387   0.0203   1.0000   0.6853
  -4.000  -0.5514   0.02234   0.01397   0.0239   1.0000   0.7191
  -3.750  -0.5388   0.02260   0.01404   0.0273   1.0000   0.7486
  -3.500  -0.5214   0.02295   0.01421   0.0302   1.0000   0.7735
  -3.250  -0.5020   0.02325   0.01432   0.0326   1.0000   0.7960
  -3.000  -0.4854   0.02336   0.01426   0.0350   1.0000   0.8180
  -2.750  -0.4593   0.02360   0.01429   0.0359   1.0000   0.8362
  -2.500  -0.4349   0.02371   0.01417   0.0368   1.0000   0.8541
  -2.250  -0.4080   0.02378   0.01405   0.0368   0.9987   0.8712
  -2.000  -0.3664   0.02396   0.01402   0.0340   0.9944   0.8851
  -1.750  -0.3214   0.02411   0.01394   0.0304   0.9904   0.8966
  -1.500  -0.2757   0.02421   0.01387   0.0264   0.9861   0.9069
  -1.250  -0.2295   0.02430   0.01381   0.0222   0.9818   0.9167
  -1.000  -0.1872   0.02432   0.01369   0.0185   0.9764   0.9263
  -0.750  -0.1362   0.02434   0.01362   0.0132   0.9720   0.9330
  -0.500  -0.0924   0.02439   0.01360   0.0091   0.9666   0.9414
  -0.250  -0.0453   0.02436   0.01353   0.0044   0.9606   0.9476
   0.000   0.0000   0.02441   0.01356   0.0000   0.9548   0.9548
   0.250   0.0453   0.02436   0.01352  -0.0044   0.9476   0.9606
   0.500   0.0923   0.02438   0.01359  -0.0091   0.9414   0.9666
   0.750   0.1363   0.02434   0.01361  -0.0132   0.9331   0.9721
   1.000   0.1875   0.02431   0.01367  -0.0186   0.9264   0.9765
   1.250   0.2298   0.02429   0.01380  -0.0222   0.9167   0.9818
   1.500   0.2759   0.02419   0.01385  -0.0265   0.9069   0.9862
   1.750   0.3217   0.02409   0.01392  -0.0305   0.8967   0.9905
   2.000   0.3667   0.02394   0.01401  -0.0341   0.8852   0.9945
   2.250   0.4082   0.02376   0.01403  -0.0369   0.8713   0.9988
   2.500   0.4347   0.02370   0.01415  -0.0367   0.8543   1.0000
   2.750   0.4590   0.02359   0.01428  -0.0359   0.8363   1.0000
   3.000   0.4849   0.02336   0.01424  -0.0349   0.8181   1.0000
   3.250   0.5015   0.02323   0.01430  -0.0325   0.7961   1.0000
   3.500   0.5210   0.02294   0.01419  -0.0301   0.7736   1.0000
   3.750   0.5382   0.02259   0.01403  -0.0272   0.7486   1.0000
   4.000   0.5510   0.02233   0.01395  -0.0238   0.7194   1.0000
   4.250   0.5633   0.02204   0.01385  -0.0202   0.6855   1.0000
   4.500   0.5775   0.02167   0.01371  -0.0167   0.6448   1.0000
   4.750   0.5929   0.02129   0.01335  -0.0130   0.5917   1.0000
   5.000   0.6075   0.02113   0.01298  -0.0092   0.5173   1.0000
   5.250   0.6167   0.02154   0.01299  -0.0052   0.4294   1.0000
   5.500   0.6206   0.02241   0.01339  -0.0011   0.3448   1.0000
   5.750   0.6224   0.02348   0.01403   0.0028   0.2723   1.0000
   6.000   0.6243   0.02466   0.01483   0.0065   0.2139   1.0000
   6.250   0.6281   0.02591   0.01577   0.0098   0.1683   1.0000
   6.500   0.6346   0.02722   0.01684   0.0127   0.1336   1.0000
   6.750   0.6446   0.02861   0.01810   0.0152   0.1082   1.0000
   7.000   0.6574   0.03007   0.01945   0.0171   0.0898   1.0000
   7.250   0.6746   0.03155   0.02110   0.0187   0.0746   1.0000
   7.500   0.6955   0.03345   0.02301   0.0198   0.0651   1.0000
   7.750   0.7158   0.03517   0.02498   0.0210   0.0552   1.0000
   8.000   0.7375   0.03751   0.02750   0.0219   0.0490   1.0000
   8.250   0.7578   0.04013   0.03047   0.0231   0.0444   1.0000
   8.500   0.7713   0.04259   0.03288   0.0240   0.0401   1.0000
   8.750   0.7819   0.04533   0.03625   0.0259   0.0371   1.0000
   9.000   0.7889   0.04871   0.04010   0.0278   0.0354   1.0000
   9.250   0.7908   0.05218   0.04398   0.0297   0.0344   1.0000
   9.500   0.7883   0.05560   0.04775   0.0316   0.0340   1.0000
   9.750   0.7798   0.05914   0.05159   0.0335   0.0337   1.0000
  10.000   0.7656   0.06258   0.05526   0.0354   0.0335   1.0000
  10.250   0.7499   0.06630   0.05917   0.0362   0.0337   1.0000
  10.500   0.7310   0.07071   0.06375   0.0357   0.0339   1.0000
  10.750   0.7095   0.07605   0.06923   0.0337   0.0342   1.0000
  11.000   0.6896   0.08207   0.07534   0.0302   0.0348   1.0000
  11.250   0.6696   0.08945   0.08277   0.0252   0.0354   1.0000
  11.500   0.6538   0.09749   0.09081   0.0198   0.0360   1.0000
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