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EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 297 AIRFOIL (e297-il)
Reynolds number: 200,000
Max Cl/Cd: 39.58 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e297-il-200000-n5.txt
Download as CSV file: xf-e297-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7035   0.10102   0.09765  -0.0079   1.0000   0.0060
 -12.500  -0.7336   0.08659   0.08314  -0.0164   1.0000   0.0058
 -12.250  -0.7545   0.07657   0.07300  -0.0236   1.0000   0.0057
 -12.000  -0.7757   0.06843   0.06470  -0.0294   1.0000   0.0056
 -11.750  -0.7968   0.06178   0.05786  -0.0333   1.0000   0.0056
 -11.500  -0.8140   0.05667   0.05256  -0.0354   1.0000   0.0055
 -11.250  -0.8308   0.05218   0.04785  -0.0361   1.0000   0.0055
 -11.000  -0.8481   0.04796   0.04337  -0.0357   1.0000   0.0055
 -10.750  -0.8600   0.04457   0.03972  -0.0344   1.0000   0.0055
 -10.500  -0.8691   0.04153   0.03641  -0.0325   1.0000   0.0055
 -10.250  -0.8746   0.03884   0.03344  -0.0301   1.0000   0.0055
 -10.000  -0.8773   0.03625   0.03055  -0.0274   1.0000   0.0056
  -9.750  -0.8746   0.03391   0.02792  -0.0249   1.0000   0.0057
  -9.500  -0.8670   0.03153   0.02522  -0.0229   1.0000   0.0059
  -9.250  -0.8554   0.02953   0.02297  -0.0213   1.0000   0.0060
  -9.000  -0.8420   0.02768   0.02083  -0.0197   1.0000   0.0062
  -8.750  -0.8271   0.02608   0.01902  -0.0182   1.0000   0.0065
  -8.500  -0.8141   0.02435   0.01713  -0.0165   1.0000   0.0069
  -8.250  -0.8012   0.02294   0.01560  -0.0148   1.0000   0.0074
  -8.000  -0.7866   0.02198   0.01457  -0.0131   1.0000   0.0084
  -7.750  -0.7663   0.02113   0.01363  -0.0126   0.9930   0.0098
  -7.500  -0.7386   0.02005   0.01241  -0.0135   0.9809   0.0126
  -7.250  -0.7117   0.01893   0.01121  -0.0143   0.9708   0.0166
  -7.000  -0.6847   0.01798   0.01020  -0.0149   0.9620   0.0232
  -6.750  -0.6568   0.01719   0.00928  -0.0156   0.9547   0.0311
  -6.500  -0.6316   0.01648   0.00853  -0.0157   0.9468   0.0413
  -6.250  -0.6066   0.01574   0.00783  -0.0157   0.9403   0.0577
  -6.000  -0.5834   0.01516   0.00726  -0.0153   0.9329   0.0777
  -5.750  -0.5596   0.01456   0.00675  -0.0150   0.9272   0.1063
  -5.500  -0.5383   0.01395   0.00630  -0.0143   0.9204   0.1467
  -5.250  -0.5174   0.01330   0.00587  -0.0135   0.9148   0.2001
  -5.000  -0.4972   0.01268   0.00549  -0.0126   0.9090   0.2601
  -4.750  -0.4772   0.01209   0.00510  -0.0116   0.9033   0.3256
  -4.500  -0.4569   0.01154   0.00480  -0.0104   0.8987   0.3934
  -4.250  -0.4363   0.01107   0.00457  -0.0093   0.8931   0.4596
  -4.000  -0.4149   0.01068   0.00441  -0.0082   0.8885   0.5230
  -3.750  -0.3921   0.01042   0.00433  -0.0071   0.8844   0.5791
  -3.500  -0.3679   0.01029   0.00433  -0.0063   0.8796   0.6241
  -3.250  -0.3427   0.01027   0.00433  -0.0055   0.8754   0.6576
  -3.000  -0.3169   0.01029   0.00435  -0.0048   0.8719   0.6838
  -2.750  -0.2909   0.01034   0.00437  -0.0044   0.8670   0.7051
  -2.500  -0.2648   0.01039   0.00438  -0.0039   0.8626   0.7227
  -2.250  -0.2384   0.01045   0.00437  -0.0034   0.8590   0.7373
  -2.000  -0.2121   0.01050   0.00439  -0.0030   0.8541   0.7500
  -1.750  -0.1857   0.01055   0.00439  -0.0026   0.8495   0.7610
  -1.500  -0.1591   0.01060   0.00441  -0.0021   0.8456   0.7701
  -1.250  -0.1327   0.01064   0.00441  -0.0018   0.8404   0.7791
  -1.000  -0.1062   0.01067   0.00442  -0.0014   0.8353   0.7876
  -0.750  -0.0795   0.01069   0.00441  -0.0010   0.8312   0.7943
  -0.500  -0.0531   0.01071   0.00443  -0.0008   0.8251   0.8018
  -0.250  -0.0265   0.01072   0.00442  -0.0004   0.8198   0.8076
   0.000   0.0000   0.01072   0.00443   0.0000   0.8141   0.8141
   0.250   0.0265   0.01072   0.00442   0.0004   0.8076   0.8198
   0.500   0.0531   0.01071   0.00443   0.0008   0.8018   0.8251
   0.750   0.0795   0.01069   0.00441   0.0010   0.7943   0.8312
   1.000   0.1063   0.01067   0.00441   0.0014   0.7876   0.8354
   1.250   0.1327   0.01064   0.00441   0.0018   0.7792   0.8404
   1.500   0.1591   0.01060   0.00441   0.0021   0.7701   0.8456
   1.750   0.1857   0.01055   0.00439   0.0026   0.7610   0.8495
   2.000   0.2121   0.01050   0.00438   0.0030   0.7500   0.8541
   2.250   0.2385   0.01045   0.00437   0.0034   0.7373   0.8590
   2.500   0.2648   0.01039   0.00438   0.0039   0.7228   0.8627
   2.750   0.2909   0.01034   0.00437   0.0044   0.7051   0.8670
   3.000   0.3170   0.01029   0.00435   0.0048   0.6838   0.8719
   3.250   0.3428   0.01027   0.00433   0.0055   0.6575   0.8754
   3.500   0.3680   0.01029   0.00433   0.0062   0.6239   0.8796
   3.750   0.3922   0.01042   0.00433   0.0071   0.5787   0.8845
   4.000   0.4151   0.01067   0.00441   0.0081   0.5232   0.8886
   4.250   0.4365   0.01107   0.00457   0.0093   0.4597   0.8932
   4.500   0.4571   0.01155   0.00480   0.0104   0.3928   0.8987
   4.750   0.4774   0.01209   0.00510   0.0115   0.3249   0.9034
   5.000   0.4975   0.01268   0.00549   0.0125   0.2596   0.9089
   5.250   0.5178   0.01331   0.00587   0.0134   0.1996   0.9148
   5.500   0.5388   0.01395   0.00630   0.0142   0.1463   0.9204
   5.750   0.5601   0.01457   0.00675   0.0149   0.1058   0.9272
   6.000   0.5839   0.01516   0.00727   0.0152   0.0776   0.9329
   6.250   0.6072   0.01575   0.00784   0.0156   0.0575   0.9403
   6.500   0.6323   0.01649   0.00853   0.0155   0.0413   0.9468
   6.750   0.6574   0.01720   0.00928   0.0155   0.0309   0.9547
   7.000   0.6854   0.01798   0.01020   0.0148   0.0230   0.9621
   7.250   0.7125   0.01893   0.01121   0.0141   0.0166   0.9709
   7.500   0.7395   0.02003   0.01240   0.0134   0.0128   0.9812
   8.000   0.7875   0.02193   0.01450   0.0130   0.0082   1.0000
   8.250   0.8019   0.02296   0.01562   0.0146   0.0073   1.0000
   8.500   0.8131   0.02469   0.01749   0.0166   0.0067   1.0000
   8.750   0.8283   0.02612   0.01906   0.0180   0.0065   1.0000
   9.000   0.8433   0.02777   0.02093   0.0195   0.0062   1.0000
   9.250   0.8568   0.02963   0.02309   0.0210   0.0059   1.0000
   9.500   0.8684   0.03164   0.02535   0.0226   0.0058   1.0000
   9.750   0.8763   0.03397   0.02799   0.0246   0.0057   1.0000
  10.000   0.8787   0.03641   0.03073   0.0271   0.0056   1.0000
  10.250   0.8774   0.03879   0.03338   0.0297   0.0056   1.0000
  10.500   0.8709   0.04161   0.03650   0.0321   0.0055   1.0000
  10.750   0.8598   0.04491   0.04009   0.0342   0.0055   1.0000
  11.000   0.8484   0.04824   0.04367   0.0354   0.0055   1.0000
  11.250   0.8323   0.05232   0.04799   0.0357   0.0055   1.0000
  11.500   0.8145   0.05696   0.05287   0.0349   0.0055   1.0000
  11.750   0.7984   0.06193   0.05801   0.0329   0.0056   1.0000
  12.000   0.7770   0.06865   0.06492   0.0289   0.0057   1.0000
  12.250   0.7571   0.07654   0.07297   0.0233   0.0057   1.0000
  12.500   0.7339   0.08726   0.08383   0.0156   0.0058   1.0000
  12.750   0.7061   0.10102   0.09765   0.0075   0.0060   1.0000
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