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EPPLER 297 AIRFOIL (e297-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 297 AIRFOIL (e297-il)
Reynolds number: 100,000
Max Cl/Cd: 34.85 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e297-il-100000-n5.txt
Download as CSV file: xf-e297-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6623   0.10009   0.09534  -0.0131   1.0000   0.0158
 -11.750  -0.6852   0.08803   0.08327  -0.0207   1.0000   0.0150
 -11.500  -0.7472   0.07039   0.06528  -0.0326   1.0000   0.0122
 -11.000  -0.7833   0.06035   0.05487  -0.0365   1.0000   0.0123
 -10.750  -0.7968   0.05669   0.05104  -0.0367   1.0000   0.0125
 -10.500  -0.8099   0.05319   0.04732  -0.0359   1.0000   0.0125
 -10.250  -0.8216   0.04977   0.04359  -0.0341   1.0000   0.0123
 -10.000  -0.8270   0.04777   0.04149  -0.0322   1.0000   0.0130
  -9.750  -0.8305   0.04552   0.03897  -0.0299   1.0000   0.0134
  -9.500  -0.8287   0.04350   0.03673  -0.0280   1.0000   0.0145
  -9.250  -0.8245   0.04079   0.03370  -0.0260   1.0000   0.0150
  -9.000  -0.8167   0.03807   0.03062  -0.0241   1.0000   0.0156
  -8.750  -0.8050   0.03532   0.02750  -0.0224   1.0000   0.0164
  -8.500  -0.7896   0.03284   0.02468  -0.0209   1.0000   0.0174
  -8.250  -0.7721   0.03076   0.02231  -0.0196   1.0000   0.0185
  -8.000  -0.7587   0.02882   0.02030  -0.0181   1.0000   0.0214
  -7.750  -0.7432   0.02759   0.01898  -0.0166   1.0000   0.0248
  -7.500  -0.7280   0.02613   0.01732  -0.0147   1.0000   0.0279
  -7.250  -0.7189   0.02478   0.01598  -0.0121   1.0000   0.0326
  -7.000  -0.7094   0.02393   0.01502  -0.0093   1.0000   0.0386
  -6.750  -0.7051   0.02290   0.01396  -0.0057   1.0000   0.0431
  -6.500  -0.6974   0.02224   0.01314  -0.0025   1.0000   0.0520
  -6.250  -0.6852   0.02122   0.01213  -0.0004   0.9977   0.0628
  -6.000  -0.6594   0.02006   0.01104  -0.0010   0.9910   0.0847
  -5.750  -0.6333   0.01900   0.01018  -0.0017   0.9848   0.1255
  -5.500  -0.6071   0.01797   0.00945  -0.0025   0.9794   0.1872
  -5.250  -0.5834   0.01699   0.00885  -0.0028   0.9733   0.2667
  -5.000  -0.5572   0.01605   0.00835  -0.0035   0.9686   0.3624
  -4.750  -0.5352   0.01536   0.00804  -0.0028   0.9625   0.4526
  -4.500  -0.5086   0.01494   0.00790  -0.0026   0.9579   0.5393
  -4.250  -0.4778   0.01488   0.00802  -0.0027   0.9545   0.6073
  -4.000  -0.4522   0.01501   0.00816  -0.0018   0.9489   0.6522
  -3.750  -0.4223   0.01520   0.00829  -0.0018   0.9445   0.6850
  -3.500  -0.3904   0.01539   0.00836  -0.0023   0.9410   0.7116
  -3.250  -0.3662   0.01555   0.00836  -0.0014   0.9348   0.7336
  -3.000  -0.3368   0.01575   0.00846  -0.0013   0.9304   0.7513
  -2.750  -0.3044   0.01593   0.00853  -0.0019   0.9270   0.7664
  -2.500  -0.2807   0.01608   0.00859  -0.0009   0.9207   0.7797
  -2.250  -0.2514   0.01620   0.00859  -0.0009   0.9162   0.7921
  -2.000  -0.2230   0.01629   0.00860  -0.0009   0.9117   0.8039
  -1.750  -0.1958   0.01643   0.00869  -0.0005   0.9060   0.8127
  -1.500  -0.1655   0.01650   0.00869  -0.0008   0.9016   0.8216
  -1.250  -0.1411   0.01653   0.00864  -0.0001   0.8955   0.8315
  -1.000  -0.1109   0.01662   0.00870  -0.0004   0.8903   0.8380
  -0.750  -0.0810   0.01661   0.00865  -0.0007   0.8860   0.8463
  -0.500  -0.0558   0.01668   0.00871  -0.0001   0.8787   0.8531
  -0.250  -0.0270   0.01666   0.00866  -0.0002   0.8735   0.8604
   0.000   0.0000   0.01670   0.00871   0.0000   0.8665   0.8665
   0.250   0.0271   0.01665   0.00866   0.0002   0.8604   0.8735
   0.500   0.0558   0.01668   0.00871   0.0001   0.8531   0.8787
   0.750   0.0810   0.01660   0.00864   0.0007   0.8463   0.8860
   1.000   0.1108   0.01661   0.00870   0.0004   0.8381   0.8903
   1.250   0.1410   0.01653   0.00864   0.0002   0.8315   0.8956
   1.500   0.1655   0.01649   0.00868   0.0008   0.8215   0.9016
   1.750   0.1958   0.01643   0.00868   0.0005   0.8127   0.9060
   2.000   0.2227   0.01629   0.00859   0.0010   0.8039   0.9118
   2.250   0.2514   0.01620   0.00859   0.0010   0.7921   0.9163
   2.500   0.2806   0.01608   0.00859   0.0009   0.7798   0.9208
   2.750   0.3043   0.01593   0.00852   0.0019   0.7665   0.9271
   3.000   0.3367   0.01574   0.00845   0.0014   0.7513   0.9305
   3.250   0.3660   0.01554   0.00835   0.0014   0.7336   0.9350
   3.500   0.3903   0.01538   0.00835   0.0023   0.7117   0.9411
   3.750   0.4222   0.01519   0.00828   0.0018   0.6850   0.9446
   4.000   0.4519   0.01499   0.00815   0.0019   0.6518   0.9492
   4.250   0.4779   0.01487   0.00801   0.0027   0.6074   0.9547
   4.500   0.5086   0.01493   0.00789   0.0026   0.5393   0.9581
   4.750   0.5350   0.01535   0.00803   0.0029   0.4529   0.9628
   5.000   0.5572   0.01605   0.00833   0.0034   0.3617   0.9688
   5.250   0.5834   0.01698   0.00884   0.0028   0.2666   0.9735
   5.500   0.6071   0.01796   0.00944   0.0025   0.1870   0.9798
   5.750   0.6335   0.01900   0.01017   0.0017   0.1250   0.9851
   6.000   0.6596   0.02005   0.01104   0.0010   0.0847   0.9914
   6.250   0.6855   0.02122   0.01212   0.0004   0.0626   0.9981
   6.500   0.6966   0.02221   0.01312   0.0027   0.0523   1.0000
   6.750   0.7043   0.02288   0.01394   0.0058   0.0434   1.0000
   7.000   0.7089   0.02391   0.01500   0.0094   0.0386   1.0000
   7.250   0.7187   0.02478   0.01597   0.0122   0.0328   1.0000
   7.500   0.7282   0.02613   0.01732   0.0146   0.0279   1.0000
   7.750   0.7436   0.02759   0.01898   0.0166   0.0247   1.0000
   8.000   0.7592   0.02884   0.02032   0.0180   0.0213   1.0000
   8.250   0.7728   0.03083   0.02237   0.0194   0.0185   1.0000
   8.500   0.7904   0.03295   0.02481   0.0208   0.0172   1.0000
   8.750   0.8059   0.03537   0.02755   0.0222   0.0164   1.0000
   9.000   0.8175   0.03817   0.03073   0.0240   0.0155   1.0000
   9.250   0.8254   0.04079   0.03370   0.0258   0.0147   1.0000
   9.500   0.8302   0.04337   0.03658   0.0277   0.0143   1.0000
   9.750   0.8315   0.04567   0.03913   0.0297   0.0135   1.0000
  10.000   0.8297   0.04737   0.04102   0.0318   0.0127   1.0000
  10.250   0.8182   0.05100   0.04502   0.0343   0.0131   1.0000
  10.500   0.8111   0.05330   0.04744   0.0356   0.0125   1.0000
  10.750   0.7981   0.05657   0.05082   0.0362   0.0120   1.0000
  11.000   0.7846   0.06035   0.05483   0.0361   0.0120   1.0000
  11.250   0.7670   0.06499   0.05966   0.0349   0.0120   1.0000
  11.500   0.7488   0.07037   0.06521   0.0323   0.0120   1.0000
  11.750   0.6849   0.08873   0.08397   0.0200   0.0153   1.0000
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