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EPPLER 694 AIRFOIL (e694-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 694 AIRFOIL (e694-il)
Reynolds number: 100,000
Max Cl/Cd: 36.4 at α=10°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e694-il-100000-n5.txt
Download as CSV file: xf-e694-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 694 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1979   0.11959   0.11420  -0.1046   0.9333   0.0317
 -10.750  -0.1966   0.11765   0.11227  -0.1029   0.9286   0.0312
 -10.500  -0.1917   0.11434   0.10896  -0.1041   0.9259   0.0306
 -10.250  -0.1878   0.11016   0.10480  -0.1065   0.9237   0.0304
 -10.000  -0.1828   0.10576   0.10040  -0.1095   0.9220   0.0302
  -9.750  -0.1961   0.10310   0.09780  -0.1076   0.9154   0.0305
  -9.500  -0.1975   0.09944   0.09417  -0.1086   0.9117   0.0296
  -9.250  -0.1981   0.09464   0.08939  -0.1116   0.9091   0.0295
  -9.000  -0.1995   0.08884   0.08360  -0.1159   0.9070   0.0293
  -8.750  -0.2760   0.07496   0.06968  -0.1207   0.8950   0.0260
  -8.500  -0.2846   0.07142   0.06607  -0.1222   0.8923   0.0258
  -8.250  -0.3268   0.07076   0.06544  -0.1148   0.8824   0.0258
  -8.000  -0.3388   0.06656   0.06105  -0.1158   0.8786   0.0257
  -7.750  -0.3591   0.06494   0.05936  -0.1115   0.8725   0.0256
  -7.500  -0.3718   0.06173   0.05593  -0.1095   0.8676   0.0256
  -7.250  -0.3695   0.05774   0.05163  -0.1099   0.8647   0.0255
  -7.000  -0.3597   0.05362   0.04707  -0.1109   0.8628   0.0255
  -6.750  -0.3668   0.05170   0.04490  -0.1073   0.8580   0.0255
  -6.500  -0.3580   0.04890   0.04172  -0.1064   0.8546   0.0255
  -6.250  -0.3395   0.04596   0.03830  -0.1069   0.8523   0.0255
  -6.000  -0.3162   0.04335   0.03519  -0.1077   0.8508   0.0256
  -5.750  -0.2898   0.04112   0.03249  -0.1086   0.8496   0.0258
  -5.500  -0.2613   0.03931   0.03034  -0.1095   0.8485   0.0262
  -5.250  -0.2319   0.03787   0.02872  -0.1106   0.8476   0.0269
  -5.000  -0.2278   0.03748   0.02825  -0.1072   0.8424   0.0273
  -4.750  -0.2056   0.03673   0.02736  -0.1069   0.8398   0.0285
  -4.500  -0.1794   0.03599   0.02644  -0.1071   0.8378   0.0307
  -4.250  -0.1513   0.03513   0.02545  -0.1076   0.8362   0.0325
  -4.000  -0.1220   0.03437   0.02466  -0.1085   0.8349   0.0344
  -3.750  -0.0907   0.03371   0.02391  -0.1096   0.8338   0.0368
  -3.500  -0.0778   0.03357   0.02367  -0.1077   0.8292   0.0391
  -3.250  -0.0543   0.03321   0.02331  -0.1078   0.8263   0.0433
  -3.000  -0.0256   0.03277   0.02287  -0.1087   0.8242   0.0556
  -2.750   0.0067   0.03215   0.02242  -0.1102   0.8225   0.0917
  -2.500   0.0402   0.03135   0.02223  -0.1125   0.8212   0.2051
  -2.250   0.0733   0.03009   0.02241  -0.1149   0.8203   0.5038
  -2.000   0.0758   0.03045   0.02318  -0.1101   0.8149   0.6042
  -1.750   0.0833   0.03085   0.02379  -0.1050   0.8110   0.6780
  -1.500   0.1077   0.03125   0.02407  -0.1038   0.8087   0.7325
  -1.250   0.1346   0.03158   0.02423  -0.1032   0.8070   0.7652
  -1.000   0.1396   0.03223   0.02482  -0.0992   0.8005   0.7842
  -0.750   0.1573   0.03256   0.02505  -0.0967   0.7972   0.8067
  -0.500   0.1747   0.03271   0.02511  -0.0938   0.7948   0.8291
  -0.250   0.1802   0.03305   0.02540  -0.0894   0.7894   0.8463
   0.000   0.1951   0.03321   0.02548  -0.0869   0.7849   0.8599
   0.250   0.2216   0.03322   0.02537  -0.0868   0.7823   0.8708
   0.500   0.2451   0.03303   0.02507  -0.0855   0.7804   0.8812
   0.750   0.2493   0.03344   0.02545  -0.0818   0.7728   0.8920
   1.000   0.2718   0.03344   0.02537  -0.0810   0.7693   0.9018
   1.250   0.3002   0.03331   0.02515  -0.0812   0.7670   0.9091
   1.500   0.3324   0.03317   0.02492  -0.0822   0.7653   0.9150
   1.750   0.3380   0.03379   0.02552  -0.0793   0.7561   0.9219
   2.000   0.3674   0.03378   0.02545  -0.0799   0.7531   0.9273
   2.250   0.3989   0.03359   0.02520  -0.0807   0.7509   0.9323
   2.500   0.4337   0.03340   0.02495  -0.0822   0.7492   0.9372
   2.750   0.4386   0.03414   0.02572  -0.0794   0.7386   0.9436
   3.000   0.4709   0.03401   0.02555  -0.0805   0.7359   0.9490
   3.250   0.5054   0.03377   0.02529  -0.0818   0.7339   0.9544
   3.750   0.5493   0.03439   0.02596  -0.0814   0.7205   0.9676
   4.000   0.5870   0.03414   0.02571  -0.0835   0.7183   0.9737
   4.500   0.6350   0.03463   0.02628  -0.0840   0.7043   1.0000
   4.750   0.6527   0.03533   0.02703  -0.0835   0.6950   1.0000
   5.000   0.6850   0.03530   0.02702  -0.0848   0.6906   1.0000
   5.250   0.7222   0.03500   0.02678  -0.0866   0.6882   1.0000
   5.500   0.7361   0.03588   0.02772  -0.0857   0.6768   1.0000
   5.750   0.7736   0.03543   0.02733  -0.0873   0.6740   1.0000
   6.000   0.7900   0.03614   0.02811  -0.0866   0.6627   1.0000
   6.250   0.8286   0.03539   0.02745  -0.0882   0.6594   1.0000
   6.500   0.8465   0.03594   0.02808  -0.0876   0.6476   1.0000
   6.750   0.8842   0.03513   0.02736  -0.0889   0.6444   1.0000
   7.000   0.9012   0.03581   0.02815  -0.0882   0.6324   1.0000
   7.500   0.9559   0.03579   0.02834  -0.0889   0.6171   1.0000
   7.750   0.9794   0.03606   0.02873  -0.0888   0.6068   1.0000
   8.000   1.0158   0.03523   0.02802  -0.0898   0.6002   1.0000
   8.250   1.0403   0.03531   0.02821  -0.0897   0.5869   1.0000
   8.500   1.0681   0.03515   0.02817  -0.0899   0.5733   1.0000
   8.750   1.0986   0.03479   0.02790  -0.0902   0.5588   1.0000
   9.000   1.1304   0.03433   0.02751  -0.0907   0.5424   1.0000
   9.250   1.1648   0.03368   0.02692  -0.0914   0.5228   1.0000
   9.500   1.1910   0.03372   0.02698  -0.0913   0.4989   1.0000
   9.750   1.2182   0.03368   0.02691  -0.0912   0.4719   1.0000
  10.000   1.2401   0.03407   0.02724  -0.0907   0.4425   1.0000
  10.250   1.2565   0.03487   0.02798  -0.0896   0.4116   1.0000
  10.500   1.2687   0.03601   0.02904  -0.0881   0.3804   1.0000
  10.750   1.2770   0.03747   0.03039  -0.0864   0.3473   1.0000
  11.000   1.2823   0.03921   0.03200  -0.0845   0.3130   1.0000
  11.250   1.2852   0.04120   0.03383  -0.0826   0.2777   1.0000
  11.500   1.2856   0.04348   0.03591  -0.0805   0.2444   1.0000
  11.750   1.2872   0.04579   0.03806  -0.0788   0.2125   1.0000
  12.000   1.2892   0.04817   0.04030  -0.0774   0.1776   1.0000
  12.250   1.2899   0.05075   0.04270  -0.0759   0.1461   1.0000
  12.500   1.2925   0.05323   0.04505  -0.0748   0.1201   1.0000
  12.750   1.2957   0.05573   0.04749  -0.0737   0.0992   1.0000
  13.000   1.2990   0.05829   0.05001  -0.0727   0.0792   1.0000
  13.250   1.3001   0.06114   0.05281  -0.0717   0.0617   1.0000
  13.500   1.3002   0.06417   0.05581  -0.0708   0.0475   1.0000
  13.750   1.2997   0.06735   0.05901  -0.0699   0.0387   1.0000
  14.000   1.2987   0.07067   0.06237  -0.0692   0.0335   1.0000
  14.250   1.2988   0.07394   0.06577  -0.0688   0.0302   1.0000
  14.500   1.2960   0.07764   0.06954  -0.0684   0.0282   1.0000
  14.750   1.2960   0.08106   0.07316  -0.0682   0.0266   1.0000
  15.000   1.2953   0.08464   0.07692  -0.0682   0.0253   1.0000
  15.250   1.2942   0.08833   0.08076  -0.0683   0.0242   1.0000
  15.500   1.2926   0.09214   0.08472  -0.0687   0.0234   1.0000
  15.750   1.2902   0.09610   0.08879  -0.0692   0.0228   1.0000
  16.000   1.2907   0.09968   0.09252  -0.0697   0.0221   1.0000
  16.250   1.2925   0.10309   0.09611  -0.0702   0.0213   1.0000
  16.500   1.2944   0.10653   0.09972  -0.0709   0.0205   1.0000
  16.750   1.2959   0.11004   0.10337  -0.0718   0.0198   1.0000
  17.000   1.2972   0.11361   0.10707  -0.0729   0.0191   1.0000
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