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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 200,000
Max Cl/Cd: 86.82 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e67-il-200000.txt
Download as CSV file: xf-e67-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4163   0.09843   0.09525  -0.0338   1.0000   0.0589
  -8.500  -0.4288   0.09592   0.09280  -0.0329   1.0000   0.0604
  -8.250  -0.4479   0.09321   0.09017  -0.0326   1.0000   0.0621
  -7.250  -0.4693   0.04807   0.04423  -0.0802   0.9719   0.0430
  -7.000  -0.4646   0.03557   0.03024  -0.0840   0.9641   0.0315
  -6.750  -0.4327   0.03297   0.02720  -0.0863   0.9608   0.0311
  -6.500  -0.3998   0.02929   0.02296  -0.0890   0.9588   0.0311
  -6.250  -0.3784   0.02616   0.01941  -0.0890   0.9535   0.0317
  -6.000  -0.3476   0.02406   0.01710  -0.0903   0.9501   0.0330
  -5.750  -0.3123   0.02277   0.01570  -0.0921   0.9475   0.0354
  -5.500  -0.2734   0.02200   0.01475  -0.0945   0.9454   0.0401
  -5.250  -0.2514   0.02061   0.01331  -0.0938   0.9392   0.0441
  -5.000  -0.2174   0.01956   0.01219  -0.0952   0.9357   0.0535
  -4.750  -0.1797   0.01865   0.01133  -0.0975   0.9332   0.0742
  -4.500  -0.1398   0.01802   0.01075  -0.1003   0.9314   0.1014
  -4.250  -0.1191   0.01762   0.01041  -0.0992   0.9235   0.1245
  -4.000  -0.0822   0.01709   0.00995  -0.1013   0.9204   0.1602
  -3.750  -0.0424   0.01652   0.00953  -0.1040   0.9184   0.2051
  -3.500  -0.0182   0.01621   0.00937  -0.1036   0.9116   0.2449
  -3.250   0.0166   0.01578   0.00910  -0.1053   0.9077   0.2980
  -3.000   0.0555   0.01533   0.00883  -0.1076   0.9053   0.3593
  -2.750   0.0963   0.01490   0.00858  -0.1102   0.9036   0.4233
  -2.500   0.1171   0.01481   0.00860  -0.1089   0.8952   0.4708
  -2.250   0.1550   0.01445   0.00840  -0.1108   0.8925   0.5273
  -2.000   0.1955   0.01408   0.00815  -0.1131   0.8906   0.5800
  -1.750   0.2255   0.01391   0.00808  -0.1133   0.8855   0.6241
  -1.500   0.2562   0.01373   0.00799  -0.1136   0.8801   0.6661
  -1.250   0.2941   0.01342   0.00777  -0.1151   0.8775   0.7075
  -1.000   0.3325   0.01310   0.00751  -0.1166   0.8754   0.7452
  -0.750   0.3516   0.01309   0.00758  -0.1145   0.8666   0.7773
  -0.500   0.3854   0.01281   0.00735  -0.1150   0.8631   0.8113
  -0.250   0.4204   0.01250   0.00707  -0.1157   0.8605   0.8436
   0.000   0.4339   0.01249   0.00712  -0.1122   0.8506   0.8753
   0.250   0.4651   0.01216   0.00680  -0.1120   0.8470   0.9081
   0.500   0.4888   0.01206   0.00673  -0.1107   0.8384   0.9470
   0.750   0.5426   0.01175   0.00638  -0.1157   0.8346   0.9801
   1.000   0.5823   0.01161   0.00619  -0.1183   0.8278   1.0000
   1.250   0.6142   0.01149   0.00602  -0.1192   0.8203   1.0000
   1.500   0.6430   0.01147   0.00595  -0.1195   0.8118   1.0000
   1.750   0.6772   0.01134   0.00576  -0.1207   0.8046   1.0000
   2.000   0.7036   0.01137   0.00577  -0.1204   0.7945   1.0000
   2.250   0.7356   0.01131   0.00566  -0.1211   0.7862   1.0000
   2.500   0.7649   0.01129   0.00560  -0.1212   0.7763   1.0000
   2.750   0.7913   0.01132   0.00562  -0.1208   0.7651   1.0000
   3.000   0.8194   0.01133   0.00563  -0.1207   0.7540   1.0000
   3.250   0.8484   0.01134   0.00560  -0.1208   0.7429   1.0000
   3.500   0.8774   0.01135   0.00558  -0.1208   0.7312   1.0000
   3.750   0.9030   0.01142   0.00566  -0.1202   0.7177   1.0000
   4.000   0.9286   0.01150   0.00572  -0.1196   0.7036   1.0000
   4.250   0.9543   0.01158   0.00579  -0.1190   0.6890   1.0000
   4.500   0.9797   0.01169   0.00588  -0.1183   0.6734   1.0000
   4.750   1.0030   0.01183   0.00604  -0.1173   0.6564   1.0000
   5.000   1.0261   0.01198   0.00619  -0.1162   0.6382   1.0000
   5.250   1.0495   0.01215   0.00634  -0.1152   0.6193   1.0000
   5.500   1.0721   0.01236   0.00651  -0.1140   0.5991   1.0000
   5.750   1.0931   0.01259   0.00672  -0.1126   0.5767   1.0000
   6.000   1.1135   0.01286   0.00698  -0.1110   0.5533   1.0000
   6.250   1.1329   0.01318   0.00723  -0.1093   0.5279   1.0000
   6.500   1.1507   0.01355   0.00753  -0.1073   0.5001   1.0000
   6.750   1.1669   0.01397   0.00788  -0.1051   0.4697   1.0000
   7.000   1.1819   0.01445   0.00828  -0.1027   0.4377   1.0000
   7.250   1.1951   0.01501   0.00874  -0.1000   0.4037   1.0000
   7.500   1.2059   0.01565   0.00925  -0.0970   0.3693   1.0000
   7.750   1.2143   0.01634   0.00980  -0.0936   0.3326   1.0000
   8.000   1.2212   0.01718   0.01046  -0.0901   0.2964   1.0000
   8.250   1.2279   0.01810   0.01120  -0.0867   0.2581   1.0000
   8.500   1.2343   0.01911   0.01202  -0.0835   0.2223   1.0000
   8.750   1.2414   0.02017   0.01292  -0.0805   0.1891   1.0000
   9.000   1.2487   0.02129   0.01392  -0.0777   0.1604   1.0000
   9.250   1.2561   0.02246   0.01498  -0.0750   0.1352   1.0000
   9.500   1.2624   0.02375   0.01616  -0.0723   0.1133   1.0000
   9.750   1.2684   0.02513   0.01745  -0.0696   0.0929   1.0000
  10.000   1.2714   0.02676   0.01897  -0.0668   0.0762   1.0000
  10.250   1.2751   0.02844   0.02063  -0.0641   0.0618   1.0000
  10.500   1.2752   0.03044   0.02260  -0.0612   0.0523   1.0000
  10.750   1.2807   0.03212   0.02435  -0.0590   0.0455   1.0000
  11.000   1.2809   0.03434   0.02659  -0.0565   0.0411   1.0000
  11.250   1.2884   0.03596   0.02834  -0.0548   0.0369   1.0000
  11.500   1.2904   0.03817   0.03056  -0.0529   0.0341   1.0000
  11.750   1.2948   0.04049   0.03298  -0.0510   0.0319   1.0000
  12.000   1.3030   0.04232   0.03496  -0.0496   0.0297   1.0000
  12.250   1.3096   0.04425   0.03697  -0.0484   0.0276   1.0000
  12.500   1.3143   0.04657   0.03931  -0.0471   0.0257   1.0000
  12.750   1.3246   0.04933   0.04220  -0.0458   0.0243   1.0000
  13.000   1.3326   0.05159   0.04467  -0.0446   0.0235   1.0000
  13.250   1.3397   0.05413   0.04742  -0.0435   0.0226   1.0000
  13.500   1.3453   0.05690   0.05040  -0.0425   0.0218   1.0000
  13.750   1.3478   0.05980   0.05351  -0.0417   0.0211   1.0000
  14.000   1.3477   0.06288   0.05678  -0.0410   0.0204   1.0000
  14.250   1.3463   0.06602   0.06005  -0.0406   0.0197   1.0000
  14.500   1.3449   0.06938   0.06352  -0.0404   0.0191   1.0000
  14.750   1.3404   0.07373   0.06804  -0.0403   0.0185   1.0000
  15.000   1.3283   0.07924   0.07382  -0.0406   0.0182   1.0000
  15.250   1.3144   0.08477   0.07962  -0.0415   0.0181   1.0000
  15.500   1.2979   0.09075   0.08586  -0.0430   0.0181   1.0000
  15.750   1.2806   0.09703   0.09239  -0.0451   0.0181   1.0000
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