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EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 297 AIRFOIL (e297-il)
Reynolds number: 100,000
Max Cl/Cd: 43.07 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e297-il-100000.txt
Download as CSV file: xf-e297-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5018   0.12612   0.12169  -0.0054   1.0000   0.1155
 -11.750  -0.5340   0.12147   0.11711  -0.0114   1.0000   0.1171
 -11.500  -0.6001   0.12107   0.11626  -0.0033   1.0000   0.1117
 -11.250  -0.5274   0.10353   0.09919  -0.0154   1.0000   0.0719
 -11.000  -0.5525   0.09193   0.08765  -0.0215   1.0000   0.0585
  -9.750  -0.7649   0.06444   0.05931  -0.0349   1.0000   0.0501
  -9.500  -0.7782   0.06049   0.05520  -0.0330   1.0000   0.0492
  -9.250  -0.7865   0.05627   0.05077  -0.0313   1.0000   0.0472
  -9.000  -0.7964   0.05155   0.04568  -0.0288   1.0000   0.0446
  -8.750  -0.8097   0.04673   0.03998  -0.0246   1.0000   0.0413
  -8.500  -0.8021   0.04403   0.03681  -0.0221   1.0000   0.0405
  -8.250  -0.7923   0.04098   0.03336  -0.0199   1.0000   0.0402
  -8.000  -0.7823   0.03668   0.02865  -0.0178   1.0000   0.0407
  -7.750  -0.7670   0.03312   0.02486  -0.0162   1.0000   0.0423
  -7.500  -0.7534   0.03144   0.02310  -0.0143   1.0000   0.0470
  -7.250  -0.7418   0.03009   0.02132  -0.0112   1.0000   0.0519
  -7.000  -0.7232   0.02712   0.01842  -0.0097   1.0000   0.0580
  -6.750  -0.7113   0.02565   0.01684  -0.0070   1.0000   0.0675
  -6.500  -0.6981   0.02436   0.01536  -0.0042   1.0000   0.0774
  -6.250  -0.6880   0.02295   0.01407  -0.0015   1.0000   0.0919
  -6.000  -0.6792   0.02154   0.01284   0.0016   1.0000   0.1083
  -5.750  -0.6722   0.02021   0.01171   0.0050   1.0000   0.1363
  -5.500  -0.6670   0.01876   0.01068   0.0084   1.0000   0.1894
  -5.250  -0.6634   0.01713   0.00979   0.0118   1.0000   0.2871
  -5.000  -0.6594   0.01577   0.00928   0.0155   1.0000   0.4248
  -4.750  -0.6509   0.01511   0.00928   0.0195   1.0000   0.5533
  -4.500  -0.6379   0.01521   0.00967   0.0233   1.0000   0.6404
  -4.250  -0.6235   0.01565   0.01012   0.0270   1.0000   0.6952
  -4.000  -0.6094   0.01616   0.01052   0.0305   1.0000   0.7344
  -3.750  -0.5952   0.01672   0.01093   0.0343   1.0000   0.7640
  -3.500  -0.5816   0.01719   0.01130   0.0380   1.0000   0.7901
  -3.250  -0.5666   0.01771   0.01173   0.0418   1.0000   0.8116
  -3.000  -0.5527   0.01804   0.01194   0.0454   1.0000   0.8332
  -2.750  -0.5356   0.01840   0.01220   0.0485   1.0000   0.8529
  -2.500  -0.5192   0.01863   0.01231   0.0513   1.0000   0.8733
  -2.250  -0.4894   0.01909   0.01260   0.0518   1.0000   0.8909
  -2.000  -0.4508   0.01956   0.01292   0.0503   1.0000   0.9075
  -1.750  -0.4008   0.02006   0.01324   0.0462   1.0000   0.9212
  -1.500  -0.3410   0.02052   0.01352   0.0398   1.0000   0.9323
  -1.250  -0.2891   0.02078   0.01365   0.0346   1.0000   0.9433
  -1.000  -0.2442   0.02096   0.01372   0.0304   1.0000   0.9546
  -0.750  -0.1778   0.02116   0.01381   0.0219   0.9968   0.9610
  -0.500  -0.1211   0.02135   0.01394   0.0152   0.9920   0.9690
  -0.250  -0.0590   0.02138   0.01392   0.0073   0.9869   0.9750
   0.000  -0.0001   0.02152   0.01405   0.0000   0.9816   0.9816
   0.250   0.0590   0.02137   0.01392  -0.0073   0.9750   0.9869
   0.500   0.1210   0.02134   0.01393  -0.0151   0.9691   0.9920
   0.750   0.1778   0.02115   0.01380  -0.0219   0.9610   0.9968
   1.000   0.2440   0.02095   0.01371  -0.0303   0.9547   1.0000
   1.250   0.2886   0.02078   0.01364  -0.0345   0.9434   1.0000
   1.500   0.3408   0.02051   0.01350  -0.0398   0.9324   1.0000
   1.750   0.4005   0.02004   0.01323  -0.0461   0.9213   1.0000
   2.000   0.4507   0.01954   0.01290  -0.0502   0.9076   1.0000
   2.250   0.4891   0.01907   0.01258  -0.0518   0.8909   1.0000
   2.500   0.5186   0.01861   0.01230  -0.0512   0.8733   1.0000
   2.750   0.5351   0.01840   0.01219  -0.0484   0.8530   1.0000
   3.000   0.5520   0.01803   0.01193  -0.0452   0.8332   1.0000
   3.250   0.5658   0.01771   0.01172  -0.0417   0.8117   1.0000
   3.500   0.5808   0.01720   0.01131  -0.0379   0.7904   1.0000
   3.750   0.5943   0.01672   0.01093  -0.0341   0.7641   1.0000
   4.000   0.6087   0.01615   0.01052  -0.0304   0.7350   1.0000
   4.250   0.6226   0.01565   0.01012  -0.0268   0.6957   1.0000
   4.500   0.6369   0.01520   0.00966  -0.0232   0.6408   1.0000
   4.750   0.6500   0.01509   0.00926  -0.0193   0.5547   1.0000
   5.000   0.6586   0.01574   0.00926  -0.0154   0.4273   1.0000
   5.250   0.6628   0.01709   0.00977  -0.0117   0.2897   1.0000
   5.500   0.6662   0.01873   0.01066  -0.0082   0.1903   1.0000
   5.750   0.6715   0.02018   0.01168  -0.0048   0.1368   1.0000
   6.000   0.6784   0.02151   0.01281  -0.0015   0.1088   1.0000
   6.250   0.6872   0.02291   0.01404   0.0016   0.0921   1.0000
   6.500   0.6973   0.02434   0.01532   0.0043   0.0776   1.0000
   6.750   0.7104   0.02561   0.01680   0.0072   0.0677   1.0000
   7.000   0.7224   0.02709   0.01839   0.0098   0.0580   1.0000
   7.250   0.7411   0.03007   0.02129   0.0113   0.0520   1.0000
   7.500   0.7533   0.03147   0.02312   0.0143   0.0474   1.0000
   7.750   0.7670   0.03311   0.02484   0.0162   0.0423   1.0000
   8.000   0.7823   0.03681   0.02877   0.0177   0.0407   1.0000
   8.250   0.7927   0.04103   0.03341   0.0198   0.0402   1.0000
   8.500   0.8017   0.04438   0.03718   0.0220   0.0404   1.0000
   8.750   0.8103   0.04671   0.03999   0.0246   0.0414   1.0000
   9.000   0.7969   0.05165   0.04578   0.0287   0.0446   1.0000
   9.250   0.7866   0.05636   0.05087   0.0312   0.0469   1.0000
   9.500   0.7776   0.06055   0.05528   0.0329   0.0490   1.0000
   9.750   0.7673   0.06462   0.05948   0.0345   0.0502   1.0000
  10.000   0.7546   0.06863   0.06358   0.0358   0.0509   1.0000
  10.250   0.6780   0.06396   0.05934   0.0388   0.0536   1.0000
  10.500   0.6438   0.06929   0.06484   0.0370   0.0540   1.0000
  10.750   0.6072   0.07668   0.07236   0.0326   0.0544   1.0000
  11.000   0.5523   0.09212   0.08784   0.0212   0.0586   1.0000
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