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EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E662 AIRFOIL (e662-il)
Reynolds number: 200,000
Max Cl/Cd: 71.37 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e662-il-200000.txt
Download as CSV file: xf-e662-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E662 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1066   0.09996   0.09617  -0.1224   0.9489   0.0575
 -10.750  -0.1155   0.09367   0.08992  -0.1343   0.9468   0.0596
 -10.500  -0.1088   0.08754   0.08379  -0.1374   0.9459   0.0607
 -10.250  -0.0986   0.08598   0.08223  -0.1346   0.9426   0.0618
 -10.000  -0.0878   0.08380   0.08004  -0.1346   0.9400   0.0631
  -9.750  -0.0796   0.08093   0.07717  -0.1361   0.9378   0.0653
  -9.500  -0.0756   0.07697   0.07321  -0.1398   0.9356   0.0676
  -9.250  -0.0941   0.06834   0.06457  -0.1528   0.9321   0.0713
  -9.000  -0.1247   0.06741   0.06366  -0.1480   0.9246   0.0712
  -8.750  -0.1619   0.06535   0.06151  -0.1464   0.9188   0.0717
  -8.500  -0.1910   0.06579   0.06202  -0.1378   0.9124   0.0713
  -8.250  -0.2219   0.06592   0.06218  -0.1299   0.9062   0.0709
  -7.000  -0.2940   0.05634   0.05219  -0.1119   0.8868   0.0762
  -6.000  -0.3059   0.04183   0.03562  -0.0973   0.8717   0.0487
  -5.750  -0.3227   0.04086   0.03471  -0.0905   0.8657   0.0475
  -5.500  -0.3054   0.03772   0.03126  -0.0898   0.8626   0.0457
  -5.250  -0.2779   0.03487   0.02795  -0.0901   0.8606   0.0436
  -5.000  -0.2459   0.03285   0.02551  -0.0908   0.8590   0.0428
  -4.750  -0.2108   0.03143   0.02383  -0.0921   0.8576   0.0433
  -4.500  -0.1726   0.03049   0.02272  -0.0940   0.8564   0.0454
  -4.250  -0.1804   0.03073   0.02290  -0.0883   0.8490   0.0463
  -4.000  -0.1536   0.03008   0.02213  -0.0882   0.8460   0.0474
  -3.750  -0.1207   0.02930   0.02127  -0.0890   0.8439   0.0486
  -3.500  -0.0864   0.02818   0.02021  -0.0904   0.8424   0.0518
  -3.250  -0.0477   0.02760   0.01963  -0.0925   0.8411   0.0568
  -3.000  -0.0533   0.02804   0.02003  -0.0874   0.8324   0.0594
  -2.750  -0.0215   0.02743   0.01946  -0.0885   0.8297   0.0715
  -2.500   0.0166   0.02602   0.01878  -0.0914   0.8280   0.2009
  -2.250   0.0532   0.02417   0.01870  -0.0943   0.8268   0.5903
  -2.000   0.0448   0.02499   0.01999  -0.0869   0.8187   0.7208
  -1.750   0.0662   0.02560   0.02054  -0.0847   0.8145   0.7810
  -1.500   0.0875   0.02619   0.02108  -0.0816   0.8120   0.8156
  -1.250   0.0904   0.02686   0.02173  -0.0767   0.8045   0.8329
  -1.000   0.0999   0.02718   0.02202  -0.0720   0.7993   0.8499
  -0.750   0.1214   0.02722   0.02198  -0.0694   0.7968   0.8652
  -0.500   0.1231   0.02762   0.02235  -0.0644   0.7890   0.8788
  -0.250   0.1351   0.02760   0.02228  -0.0606   0.7839   0.8932
   0.000   0.1564   0.02737   0.02198  -0.0581   0.7815   0.9070
   0.250   0.1726   0.02695   0.02151  -0.0541   0.7798   0.9247
   0.500   0.1556   0.02710   0.02169  -0.0460   0.7681   0.9432
   0.750   0.1904   0.02681   0.02134  -0.0459   0.7663   0.9659
   1.000   0.2360   0.02666   0.02110  -0.0491   0.7652   0.9709
   1.250   0.2789   0.02644   0.02080  -0.0519   0.7643   0.9724
   1.500   0.2930   0.02700   0.02134  -0.0512   0.7528   0.9761
   1.750   0.3359   0.02672   0.02100  -0.0540   0.7514   0.9772
   2.000   0.3787   0.02638   0.02061  -0.0567   0.7503   0.9782
   2.250   0.3924   0.02687   0.02110  -0.0557   0.7394   0.9823
   2.500   0.4326   0.02648   0.02067  -0.0579   0.7376   0.9835
   2.750   0.4759   0.02604   0.02021  -0.0606   0.7364   0.9841
   3.000   0.5207   0.02550   0.01965  -0.0634   0.7356   0.9848
   3.250   0.5384   0.02604   0.02020  -0.0632   0.7244   0.9881
   3.500   0.5808   0.02542   0.01959  -0.0656   0.7230   0.9889
   3.750   0.6249   0.02472   0.01889  -0.0682   0.7221   0.9899
   4.000   0.6694   0.02394   0.01813  -0.0708   0.7213   0.9908
   4.250   0.7143   0.02305   0.01727  -0.0733   0.7207   0.9915
   4.500   0.7276   0.02348   0.01774  -0.0721   0.7088   0.9975
   4.750   0.7717   0.02245   0.01675  -0.0744   0.7080   0.9989
   5.000   0.8182   0.02135   0.01569  -0.0771   0.7074   1.0000
   5.750   0.8646   0.02049   0.01495  -0.0711   0.6833   1.0000
   6.000   0.9093   0.01932   0.01383  -0.0734   0.6810   1.0000
   6.250   0.9591   0.01806   0.01262  -0.0764   0.6788   1.0000
   6.500   0.9762   0.01804   0.01267  -0.0751   0.6668   1.0000
   6.750   1.0039   0.01773   0.01241  -0.0752   0.6559   1.0000
   7.000   1.0433   0.01698   0.01170  -0.0769   0.6457   1.0000
   7.250   1.0791   0.01649   0.01123  -0.0781   0.6322   1.0000
   7.500   1.1073   0.01636   0.01111  -0.0784   0.6144   1.0000
   7.750   1.1373   0.01625   0.01097  -0.0789   0.5948   1.0000
   8.000   1.1648   0.01632   0.01098  -0.0791   0.5730   1.0000
   8.250   1.1847   0.01670   0.01130  -0.0783   0.5486   1.0000
   8.500   1.2024   0.01722   0.01175  -0.0772   0.5236   1.0000
   8.750   1.2186   0.01786   0.01228  -0.0760   0.4984   1.0000
   9.000   1.2306   0.01868   0.01305  -0.0744   0.4726   1.0000
   9.250   1.2414   0.01961   0.01390  -0.0726   0.4466   1.0000
   9.500   1.2511   0.02063   0.01482  -0.0708   0.4210   1.0000
   9.750   1.2593   0.02176   0.01588  -0.0689   0.3950   1.0000
  10.000   1.2673   0.02296   0.01701  -0.0671   0.3695   1.0000
  10.250   1.2742   0.02427   0.01822  -0.0653   0.3447   1.0000
  10.500   1.2807   0.02564   0.01951  -0.0635   0.3198   1.0000
  10.750   1.2876   0.02705   0.02087  -0.0619   0.2963   1.0000
  11.000   1.2933   0.02858   0.02231  -0.0601   0.2733   1.0000
  11.250   1.2998   0.03012   0.02380  -0.0586   0.2509   1.0000
  11.500   1.3049   0.03180   0.02540  -0.0570   0.2295   1.0000
  11.750   1.3105   0.03351   0.02705  -0.0556   0.2090   1.0000
  12.000   1.3156   0.03531   0.02880  -0.0542   0.1892   1.0000
  12.250   1.3193   0.03728   0.03069  -0.0528   0.1708   1.0000
  12.500   1.3236   0.03926   0.03263  -0.0515   0.1529   1.0000
  12.750   1.3282   0.04128   0.03462  -0.0504   0.1359   1.0000
  13.000   1.3323   0.04341   0.03670  -0.0494   0.1205   1.0000
  13.250   1.3362   0.04561   0.03887  -0.0484   0.1068   1.0000
  13.500   1.3403   0.04785   0.04112  -0.0476   0.0958   1.0000
  13.750   1.3428   0.05031   0.04356  -0.0467   0.0865   1.0000
  14.000   1.3461   0.05276   0.04603  -0.0460   0.0779   1.0000
  14.250   1.3506   0.05517   0.04853  -0.0455   0.0696   1.0000
  14.500   1.3509   0.05807   0.05144  -0.0449   0.0626   1.0000
  14.750   1.3516   0.06100   0.05439  -0.0446   0.0551   1.0000
  15.000   1.3527   0.06401   0.05750  -0.0443   0.0477   1.0000
  15.250   1.3479   0.06778   0.06130  -0.0440   0.0414   1.0000
  15.500   1.3412   0.07191   0.06544  -0.0440   0.0364   1.0000
  15.750   1.3378   0.07575   0.06941  -0.0441   0.0319   1.0000
  16.000   1.3324   0.07991   0.07360  -0.0444   0.0293   1.0000
  16.250   1.3286   0.08390   0.07769  -0.0446   0.0272   1.0000
  16.500   1.3285   0.08753   0.08145  -0.0452   0.0252   1.0000
  16.750   1.3272   0.09131   0.08531  -0.0459   0.0237   1.0000
  17.000   1.3242   0.09519   0.08919  -0.0465   0.0223   1.0000
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