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EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 297 AIRFOIL (e297-il)
Reynolds number: 500,000
Max Cl/Cd: 51.09 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e297-il-500000-n5.txt
Download as CSV file: xf-e297-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.8315   0.08056   0.07813  -0.0170   1.0000   0.0024
 -13.250  -0.8537   0.07070   0.06811  -0.0238   1.0000   0.0024
 -13.000  -0.8761   0.06242   0.05964  -0.0293   1.0000   0.0024
 -12.750  -0.8975   0.05567   0.05268  -0.0329   1.0000   0.0024
 -12.500  -0.9178   0.05004   0.04684  -0.0349   1.0000   0.0024
 -12.250  -0.9329   0.04568   0.04227  -0.0355   1.0000   0.0023
 -12.000  -0.9475   0.04172   0.03807  -0.0351   1.0000   0.0023
 -11.750  -0.9580   0.03845   0.03457  -0.0339   1.0000   0.0023
 -11.500  -0.9647   0.03570   0.03160  -0.0323   1.0000   0.0023
 -11.250  -0.9685   0.03328   0.02896  -0.0303   1.0000   0.0023
 -11.000  -0.9713   0.03096   0.02640  -0.0280   1.0000   0.0023
 -10.750  -0.9693   0.02913   0.02438  -0.0256   1.0000   0.0024
 -10.500  -0.9654   0.02746   0.02252  -0.0232   1.0000   0.0024
 -10.250  -0.9591   0.02595   0.02083  -0.0207   1.0000   0.0024
 -10.000  -0.9497   0.02453   0.01923  -0.0186   1.0000   0.0024
  -9.750  -0.9369   0.02321   0.01776  -0.0169   1.0000   0.0024
  -9.500  -0.9226   0.02191   0.01629  -0.0155   0.9943   0.0025
  -9.250  -0.8956   0.02060   0.01481  -0.0166   0.9589   0.0025
  -9.000  -0.8734   0.01950   0.01354  -0.0164   0.9386   0.0026
  -8.750  -0.8563   0.01861   0.01248  -0.0149   0.9225   0.0027
  -8.500  -0.8390   0.01781   0.01150  -0.0134   0.9111   0.0028
  -8.250  -0.8204   0.01710   0.01064  -0.0121   0.9021   0.0029
  -8.000  -0.8009   0.01639   0.00980  -0.0109   0.8947   0.0031
  -7.750  -0.7804   0.01578   0.00907  -0.0098   0.8880   0.0033
  -7.500  -0.7588   0.01523   0.00840  -0.0090   0.8823   0.0036
  -7.250  -0.7379   0.01454   0.00761  -0.0079   0.8769   0.0046
  -6.750  -0.6926   0.01356   0.00655  -0.0066   0.8677   0.0092
  -6.500  -0.6686   0.01319   0.00609  -0.0061   0.8633   0.0128
  -6.250  -0.6450   0.01281   0.00569  -0.0056   0.8595   0.0177
  -6.000  -0.6211   0.01238   0.00531  -0.0051   0.8557   0.0272
  -5.750  -0.5974   0.01193   0.00494  -0.0047   0.8517   0.0431
  -5.500  -0.5734   0.01152   0.00458  -0.0042   0.8480   0.0613
  -5.000  -0.5240   0.01081   0.00397  -0.0036   0.8413   0.1022
  -4.750  -0.4991   0.01045   0.00367  -0.0033   0.8376   0.1282
  -4.500  -0.4748   0.01003   0.00340  -0.0029   0.8343   0.1660
  -4.250  -0.4515   0.00952   0.00311  -0.0025   0.8313   0.2244
  -4.000  -0.4273   0.00905   0.00286  -0.0022   0.8277   0.2807
  -3.750  -0.4027   0.00864   0.00264  -0.0019   0.8241   0.3324
  -3.500  -0.3781   0.00825   0.00243  -0.0015   0.8207   0.3875
  -3.250  -0.3537   0.00787   0.00222  -0.0011   0.8176   0.4456
  -3.000  -0.3286   0.00751   0.00206  -0.0008   0.8140   0.5011
  -2.750  -0.3033   0.00721   0.00194  -0.0005   0.8102   0.5518
  -2.500  -0.2773   0.00699   0.00185  -0.0002   0.8067   0.5937
  -2.250  -0.2510   0.00684   0.00177   0.0000   0.8034   0.6290
  -2.000  -0.2238   0.00673   0.00176   0.0001   0.7992   0.6580
  -1.750  -0.1964   0.00667   0.00175   0.0002   0.7950   0.6826
  -1.500  -0.1689   0.00665   0.00174   0.0003   0.7912   0.7015
  -1.250  -0.1409   0.00664   0.00173   0.0003   0.7869   0.7156
  -1.000  -0.1127   0.00663   0.00173   0.0002   0.7818   0.7269
  -0.750  -0.0847   0.00663   0.00171   0.0002   0.7771   0.7368
  -0.500  -0.0564   0.00663   0.00172   0.0001   0.7717   0.7457
  -0.250  -0.0282   0.00663   0.00171   0.0001   0.7659   0.7531
   0.000   0.0000   0.00663   0.00170   0.0000   0.7603   0.7603
   0.250   0.0282   0.00663   0.00171  -0.0001   0.7531   0.7660
   0.500   0.0564   0.00663   0.00172  -0.0001   0.7456   0.7717
   0.750   0.0847   0.00663   0.00171  -0.0002   0.7368   0.7771
   1.000   0.1127   0.00663   0.00173  -0.0002   0.7269   0.7818
   1.250   0.1409   0.00664   0.00173  -0.0003   0.7156   0.7869
   1.500   0.1689   0.00665   0.00174  -0.0003   0.7016   0.7912
   1.750   0.1964   0.00667   0.00175  -0.0002   0.6826   0.7950
   2.000   0.2239   0.00673   0.00176  -0.0002   0.6581   0.7992
   2.250   0.2510   0.00684   0.00177   0.0000   0.6289   0.8034
   2.500   0.2774   0.00699   0.00185   0.0002   0.5937   0.8066
   2.750   0.3033   0.00721   0.00194   0.0005   0.5517   0.8102
   3.000   0.3287   0.00751   0.00206   0.0008   0.5016   0.8140
   3.250   0.3538   0.00787   0.00222   0.0011   0.4458   0.8177
   3.500   0.3783   0.00825   0.00243   0.0015   0.3871   0.8207
   3.750   0.4029   0.00864   0.00264   0.0018   0.3322   0.8240
   4.000   0.4274   0.00906   0.00286   0.0021   0.2789   0.8276
   4.500   0.4751   0.01003   0.00340   0.0029   0.1664   0.8343
   4.750   0.4994   0.01045   0.00367   0.0032   0.1285   0.8376
   5.000   0.5244   0.01081   0.00397   0.0035   0.1024   0.8413
   5.500   0.5739   0.01152   0.00459   0.0041   0.0613   0.8480
   5.750   0.5979   0.01194   0.00494   0.0046   0.0426   0.8516
   6.000   0.6217   0.01238   0.00532   0.0050   0.0276   0.8556
   6.250   0.6456   0.01281   0.00570   0.0054   0.0177   0.8595
   6.500   0.6694   0.01319   0.00610   0.0059   0.0129   0.8632
   6.750   0.6933   0.01357   0.00655   0.0064   0.0093   0.8676
   7.250   0.7388   0.01455   0.00762   0.0078   0.0045   0.8768
   7.500   0.7598   0.01523   0.00840   0.0088   0.0036   0.8821
   7.750   0.7815   0.01579   0.00908   0.0096   0.0033   0.8878
   8.000   0.8020   0.01641   0.00982   0.0107   0.0031   0.8945
   8.250   0.8216   0.01712   0.01066   0.0118   0.0029   0.9018
   8.500   0.8400   0.01787   0.01155   0.0132   0.0028   0.9108
   8.750   0.8577   0.01862   0.01249   0.0146   0.0027   0.9220
   9.000   0.8748   0.01954   0.01357   0.0161   0.0026   0.9378
   9.250   0.8965   0.02066   0.01487   0.0164   0.0025   0.9580
   9.500   0.9236   0.02196   0.01636   0.0153   0.0025   0.9904
   9.750   0.9386   0.02324   0.01778   0.0166   0.0024   1.0000
  10.000   0.9514   0.02458   0.01928   0.0182   0.0024   1.0000
  10.250   0.9616   0.02597   0.02084   0.0202   0.0024   1.0000
  10.500   0.9677   0.02749   0.02254   0.0227   0.0024   1.0000
  10.750   0.9706   0.02928   0.02455   0.0253   0.0023   1.0000
  11.000   0.9728   0.03109   0.02655   0.0276   0.0023   1.0000
  11.250   0.9712   0.03326   0.02894   0.0299   0.0023   1.0000
  11.500   0.9666   0.03576   0.03167   0.0319   0.0023   1.0000
  11.750   0.9601   0.03852   0.03465   0.0335   0.0023   1.0000
  12.000   0.9472   0.04208   0.03846   0.0347   0.0023   1.0000
  12.250   0.9344   0.04583   0.04243   0.0351   0.0024   1.0000
  12.500   0.9190   0.05024   0.04705   0.0345   0.0024   1.0000
  12.750   0.8998   0.05573   0.05275   0.0325   0.0024   1.0000
  13.000   0.8784   0.06250   0.05972   0.0288   0.0024   1.0000
  13.250   0.8578   0.07040   0.06780   0.0236   0.0024   1.0000
  13.500   0.8285   0.08205   0.07964   0.0156   0.0024   1.0000
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