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EPPLER 341 AIRFOIL (e341-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 341 AIRFOIL (e341-il)
Reynolds number: 200,000
Max Cl/Cd: 60.13 at α=10.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e341-il-200000-n5.txt
Download as CSV file: xf-e341-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 341 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4790   0.09350   0.09037  -0.0141   1.0000   0.0275
  -9.500  -0.4868   0.08707   0.08392  -0.0198   1.0000   0.0275
  -9.250  -0.4977   0.08191   0.07871  -0.0226   1.0000   0.0275
  -9.000  -0.5099   0.07752   0.07426  -0.0234   1.0000   0.0275
  -8.750  -0.5191   0.07338   0.06999  -0.0237   0.9106   0.0275
  -8.250  -0.5473   0.05925   0.05524  -0.0193   0.8064   0.0146
  -8.000  -0.5470   0.05674   0.05250  -0.0173   0.7750   0.0144
  -7.750  -0.5453   0.05388   0.04940  -0.0153   0.7509   0.0142
  -7.500  -0.5416   0.05073   0.04597  -0.0132   0.7308   0.0140
  -7.250  -0.5363   0.04731   0.04225  -0.0110   0.7133   0.0136
  -7.000  -0.5298   0.04358   0.03815  -0.0086   0.6979   0.0132
  -6.750  -0.5227   0.03914   0.03325  -0.0056   0.6842   0.0127
  -6.250  -0.5006   0.02941   0.02198   0.0012   0.6601   0.0116
  -6.000  -0.4804   0.02734   0.01950   0.0027   0.6462   0.0116
  -5.500  -0.4338   0.02397   0.01545   0.0047   0.6198   0.0117
  -5.250  -0.4087   0.02269   0.01396   0.0053   0.6076   0.0119
  -5.000  -0.3830   0.02161   0.01268   0.0058   0.5957   0.0122
  -4.750  -0.3569   0.02066   0.01155   0.0063   0.5840   0.0126
  -4.500  -0.3307   0.01977   0.01051   0.0068   0.5728   0.0130
  -4.250  -0.3049   0.01898   0.00957   0.0073   0.5628   0.0135
  -4.000  -0.2798   0.01825   0.00872   0.0080   0.5529   0.0142
  -3.750  -0.2553   0.01763   0.00800   0.0087   0.5438   0.0150
  -3.500  -0.2307   0.01722   0.00754   0.0093   0.5345   0.0167
  -3.250  -0.2062   0.01676   0.00700   0.0100   0.5256   0.0188
  -3.000  -0.1822   0.01634   0.00650   0.0108   0.5171   0.0207
  -2.750  -0.1580   0.01591   0.00600   0.0116   0.5089   0.0235
  -2.500  -0.1339   0.01554   0.00558   0.0124   0.5015   0.0292
  -2.250  -0.1104   0.01513   0.00521   0.0133   0.4945   0.0456
  -2.000  -0.0877   0.01470   0.00492   0.0142   0.4873   0.0866
  -1.750  -0.0696   0.01392   0.00463   0.0158   0.4811   0.2076
  -1.500  -0.0327   0.01315   0.00644   0.0166   0.4733   0.8566
  -1.250  -0.0098   0.01382   0.00693   0.0186   0.4674   0.8834
  -1.000   0.0304   0.01459   0.00755   0.0174   0.4604   0.9034
  -0.750   0.0806   0.01526   0.00801   0.0139   0.4534   0.9186
  -0.500   0.1247   0.01558   0.00816   0.0112   0.4470   0.9282
  -0.250   0.1555   0.01559   0.00806   0.0105   0.4409   0.9319
   0.000   0.1793   0.01562   0.00794   0.0112   0.4360   0.9358
   0.250   0.2059   0.01561   0.00784   0.0114   0.4312   0.9386
   0.500   0.2383   0.01558   0.00773   0.0103   0.4261   0.9401
   0.750   0.2693   0.01558   0.00761   0.0095   0.4214   0.9417
   1.000   0.2990   0.01559   0.00752   0.0089   0.4170   0.9437
   1.250   0.3272   0.01559   0.00748   0.0087   0.4120   0.9458
   1.500   0.3529   0.01562   0.00745   0.0090   0.4077   0.9484
   1.750   0.3743   0.01568   0.00743   0.0101   0.4043   0.9512
   2.000   0.4056   0.01570   0.00738   0.0092   0.4004   0.9523
   2.250   0.4361   0.01570   0.00737   0.0084   0.3959   0.9534
   2.500   0.4653   0.01573   0.00736   0.0079   0.3917   0.9547
   2.750   0.4940   0.01578   0.00735   0.0075   0.3883   0.9562
   3.000   0.5214   0.01585   0.00738   0.0073   0.3849   0.9577
   3.250   0.5475   0.01590   0.00745   0.0075   0.3809   0.9593
   3.500   0.5715   0.01598   0.00754   0.0080   0.3771   0.9613
   3.750   0.5961   0.01607   0.00759   0.0084   0.3739   0.9627
   4.000   0.6248   0.01616   0.00763   0.0079   0.3709   0.9635
   4.250   0.6542   0.01623   0.00774   0.0073   0.3672   0.9645
   4.500   0.6828   0.01630   0.00787   0.0069   0.3633   0.9656
   4.750   0.7099   0.01640   0.00797   0.0067   0.3597   0.9666
   5.000   0.7359   0.01652   0.00806   0.0068   0.3566   0.9676
   5.250   0.7618   0.01665   0.00822   0.0068   0.3533   0.9688
   5.500   0.7869   0.01678   0.00843   0.0071   0.3497   0.9703
   5.750   0.8099   0.01692   0.00861   0.0077   0.3462   0.9716
   6.000   0.8343   0.01706   0.00878   0.0081   0.3428   0.9725
   6.250   0.8617   0.01722   0.00891   0.0078   0.3396   0.9732
   6.500   0.8896   0.01736   0.00916   0.0073   0.3357   0.9741
   6.750   0.9164   0.01751   0.00941   0.0071   0.3316   0.9751
   7.000   0.9417   0.01766   0.00961   0.0072   0.3279   0.9760
   7.250   0.9664   0.01785   0.00979   0.0075   0.3246   0.9768
   7.500   0.9903   0.01804   0.01011   0.0078   0.3203   0.9778
   7.750   1.0135   0.01822   0.01040   0.0083   0.3158   0.9788
   8.000   1.0363   0.01841   0.01063   0.0088   0.3117   0.9803
   8.250   1.0598   0.01863   0.01089   0.0092   0.3079   0.9813
   8.500   1.0845   0.01884   0.01126   0.0093   0.3028   0.9820
   8.750   1.1085   0.01903   0.01153   0.0095   0.2976   0.9828
   9.000   1.1318   0.01926   0.01180   0.0099   0.2931   0.9837
   9.250   1.1543   0.01951   0.01222   0.0103   0.2872   0.9847
   9.500   1.1758   0.01974   0.01252   0.0109   0.2815   0.9859
   9.750   1.1969   0.02003   0.01291   0.0116   0.2754   0.9873
  10.000   1.2180   0.02032   0.01332   0.0122   0.2687   0.9887
  10.250   1.2402   0.02063   0.01372   0.0125   0.2621   0.9897
  10.500   1.2610   0.02097   0.01417   0.0130   0.2542   0.9909
  10.750   1.2804   0.02137   0.01467   0.0137   0.2464   0.9922
  11.000   1.2978   0.02182   0.01519   0.0146   0.2380   0.9937
  11.250   1.3145   0.02233   0.01582   0.0156   0.2289   0.9953
  11.500   1.3320   0.02295   0.01650   0.0162   0.2189   0.9967
  11.750   1.3461   0.02371   0.01731   0.0171   0.2086   0.9986
  12.000   1.3533   0.02449   0.01819   0.0192   0.1986   1.0000
  12.250   1.3370   0.02520   0.01893   0.0257   0.1933   1.0000
  12.500   1.3209   0.02606   0.01986   0.0314   0.1875   1.0000
  12.750   1.3020   0.02729   0.02112   0.0367   0.1824   1.0000
  13.000   1.2879   0.02872   0.02261   0.0406   0.1762   1.0000
  13.250   1.2745   0.03069   0.02462   0.0432   0.1695   1.0000
  13.500   1.2679   0.03304   0.02703   0.0440   0.1616   1.0000
  13.750   1.2595   0.03606   0.03008   0.0439   0.1542   1.0000
  14.000   1.2542   0.03911   0.03321   0.0433   0.1462   1.0000
  14.250   1.2451   0.04269   0.03684   0.0424   0.1395   1.0000
  14.500   1.2363   0.04638   0.04059   0.0415   0.1325   1.0000
  14.750   1.2253   0.05036   0.04462   0.0404   0.1265   1.0000
  15.000   1.2149   0.05434   0.04867   0.0392   0.1201   1.0000
  15.250   1.2026   0.05863   0.05299   0.0379   0.1149   1.0000
  15.500   1.1937   0.06270   0.05714   0.0366   0.1089   1.0000
  16.000   1.1742   0.07133   0.06589   0.0336   0.0984   1.0000
  16.250   1.1635   0.07589   0.07048   0.0320   0.0935   1.0000
  16.500   1.1561   0.08008   0.07474   0.0305   0.0889   1.0000
  16.750   1.1483   0.08439   0.07910   0.0289   0.0842   1.0000
  17.000   1.1388   0.08898   0.08372   0.0272   0.0802   1.0000
  17.250   1.1336   0.09307   0.08789   0.0256   0.0758   1.0000
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