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EPPLER 585 AIRFOIL (e585-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 585 AIRFOIL (e585-il)
Reynolds number: 200,000
Max Cl/Cd: 81.43 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e585-il-200000.txt
Download as CSV file: xf-e585-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 585 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  -0.2125   0.11730   0.11390  -0.0712   0.9810   0.0341
 -10.750  -0.2041   0.11237   0.10899  -0.0777   0.9759   0.0360
 -10.500  -0.2006   0.10613   0.10277  -0.0888   0.9720   0.0367
 -10.250  -0.1844   0.10190   0.09854  -0.0873   0.9676   0.0378
 -10.000  -0.1653   0.09861   0.09524  -0.0892   0.9636   0.0392
  -9.750  -0.1488   0.09445   0.09107  -0.0936   0.9606   0.0407
  -9.500  -0.1366   0.08978   0.08640  -0.0989   0.9562   0.0428
  -8.750  -0.1027   0.07426   0.07088  -0.1173   0.9406   0.0486
  -8.500  -0.0880   0.07006   0.06666  -0.1225   0.9344   0.0515
  -8.250  -0.0877   0.06366   0.06020  -0.1319   0.9245   0.0534
  -8.000  -0.1012   0.05898   0.05535  -0.1368   0.9124   0.0548
  -7.750  -0.1199   0.05659   0.05248  -0.1380   0.9006   0.0561
  -7.250  -0.1047   0.04909   0.04503  -0.1375   0.8874   0.0595
  -7.000  -0.0961   0.04698   0.04283  -0.1367   0.8811   0.0618
  -6.750  -0.0969   0.04761   0.04273  -0.1344   0.8726   0.0686
  -5.500  -0.0264   0.02607   0.01905  -0.1265   0.8466   0.0290
  -5.250  -0.0018   0.02385   0.01657  -0.1260   0.8429   0.0281
  -5.000   0.0266   0.02207   0.01451  -0.1259   0.8401   0.0277
  -4.750   0.0477   0.02101   0.01329  -0.1245   0.8351   0.0280
  -4.500   0.0710   0.02009   0.01224  -0.1234   0.8303   0.0288
  -4.250   0.0965   0.01891   0.01102  -0.1229   0.8269   0.0304
  -4.000   0.1249   0.01831   0.01039  -0.1231   0.8242   0.0362
  -3.750   0.1410   0.01775   0.00992  -0.1213   0.8184   0.0428
  -3.500   0.1630   0.01692   0.00916  -0.1205   0.8139   0.0645
  -3.250   0.1860   0.01544   0.00841  -0.1205   0.8107   0.2117
  -3.000   0.1990   0.01392   0.00871  -0.1183   0.8074   0.6459
  -2.750   0.2140   0.01456   0.00943  -0.1150   0.8014   0.7309
  -2.500   0.2364   0.01504   0.00981  -0.1129   0.7976   0.7653
  -2.250   0.2596   0.01544   0.01010  -0.1108   0.7947   0.7876
  -2.000   0.2766   0.01589   0.01051  -0.1077   0.7905   0.8052
  -1.750   0.2909   0.01627   0.01085  -0.1044   0.7850   0.8202
  -1.500   0.3112   0.01646   0.01095  -0.1020   0.7814   0.8345
  -1.250   0.3353   0.01654   0.01092  -0.1004   0.7787   0.8478
  -1.000   0.3458   0.01685   0.01122  -0.0966   0.7730   0.8613
  -0.750   0.3562   0.01701   0.01136  -0.0921   0.7681   0.8779
  -0.500   0.3744   0.01697   0.01126  -0.0889   0.7649   0.8941
  -0.250   0.4030   0.01689   0.01106  -0.0887   0.7625   0.9044
   0.000   0.4108   0.01707   0.01126  -0.0851   0.7553   0.9110
   0.250   0.4374   0.01698   0.01110  -0.0852   0.7515   0.9161
   0.500   0.4700   0.01682   0.01083  -0.0862   0.7487   0.9196
   0.750   0.4908   0.01688   0.01087  -0.0852   0.7440   0.9236
   1.000   0.5108   0.01693   0.01091  -0.0841   0.7383   0.9282
   1.250   0.5418   0.01681   0.01071  -0.0850   0.7350   0.9314
   1.500   0.5777   0.01663   0.01044  -0.0867   0.7324   0.9338
   1.750   0.5910   0.01683   0.01069  -0.0845   0.7253   0.9382
   2.000   0.6204   0.01672   0.01054  -0.0850   0.7210   0.9416
   2.250   0.6564   0.01652   0.01028  -0.0867   0.7180   0.9442
   2.500   0.6755   0.01664   0.01043  -0.0856   0.7117   0.9482
   2.750   0.7039   0.01658   0.01038  -0.0860   0.7066   0.9516
   3.000   0.7410   0.01637   0.01012  -0.0879   0.7032   0.9543
   3.250   0.7633   0.01646   0.01023  -0.0873   0.6974   0.9588
   3.500   0.7923   0.01641   0.01020  -0.0879   0.6915   0.9621
   3.750   0.8325   0.01617   0.00993  -0.0904   0.6878   0.9641
   4.000   0.8574   0.01627   0.01009  -0.0903   0.6808   0.9692
   4.250   0.8907   0.01613   0.00995  -0.0917   0.6751   0.9729
   4.500   0.9339   0.01585   0.00965  -0.0947   0.6712   0.9744
   4.750   0.9585   0.01601   0.00992  -0.0948   0.6624   0.9798
   5.000   0.9982   0.01576   0.00965  -0.0972   0.6574   0.9825
   5.250   1.0292   0.01584   0.00983  -0.0985   0.6489   0.9876
   5.500   1.0695   0.01561   0.00960  -0.1011   0.6427   0.9910
   5.750   1.0986   0.01565   0.00975  -0.1020   0.6334   1.0000
   6.000   1.1256   0.01543   0.00950  -0.1020   0.6268   1.0000
   6.250   1.1358   0.01553   0.00970  -0.0992   0.6169   1.0000
   6.500   1.1625   0.01547   0.00966  -0.0993   0.6081   1.0000
   6.750   1.1894   0.01541   0.00964  -0.0995   0.5981   1.0000
   7.000   1.2110   0.01549   0.00980  -0.0988   0.5863   1.0000
   7.250   1.2350   0.01556   0.00992  -0.0985   0.5743   1.0000
   7.500   1.2588   0.01564   0.01005  -0.0981   0.5613   1.0000
   7.750   1.2812   0.01578   0.01022  -0.0976   0.5472   1.0000
   8.000   1.3012   0.01598   0.01045  -0.0965   0.5318   1.0000
   8.250   1.3178   0.01623   0.01071  -0.0949   0.5150   1.0000
   8.500   1.3327   0.01656   0.01105  -0.0930   0.4971   1.0000
   8.750   1.3465   0.01699   0.01142  -0.0909   0.4783   1.0000
   9.000   1.3564   0.01754   0.01197  -0.0883   0.4582   1.0000
   9.250   1.3651   0.01820   0.01259  -0.0857   0.4374   1.0000
   9.500   1.3722   0.01900   0.01330  -0.0829   0.4163   1.0000
   9.750   1.3771   0.01992   0.01420  -0.0799   0.3943   1.0000
  10.000   1.3806   0.02099   0.01519  -0.0770   0.3729   1.0000
  10.250   1.3835   0.02217   0.01634  -0.0741   0.3511   1.0000
  10.500   1.3847   0.02352   0.01761  -0.0713   0.3298   1.0000
  10.750   1.3864   0.02496   0.01900  -0.0687   0.3092   1.0000
  11.000   1.3875   0.02652   0.02052  -0.0662   0.2887   1.0000
  11.250   1.3874   0.02825   0.02218  -0.0638   0.2693   1.0000
  11.500   1.3885   0.03000   0.02392  -0.0618   0.2501   1.0000
  11.750   1.3888   0.03189   0.02578  -0.0598   0.2309   1.0000
  12.000   1.3886   0.03391   0.02775  -0.0579   0.2131   1.0000
  12.250   1.3876   0.03608   0.02987  -0.0562   0.1961   1.0000
  12.500   1.3884   0.03821   0.03199  -0.0547   0.1793   1.0000
  12.750   1.3885   0.04050   0.03426  -0.0534   0.1627   1.0000
  13.000   1.3879   0.04293   0.03668  -0.0521   0.1471   1.0000
  13.250   1.3867   0.04551   0.03924  -0.0510   0.1321   1.0000
  13.500   1.3849   0.04826   0.04197  -0.0501   0.1179   1.0000
  13.750   1.3824   0.05117   0.04487  -0.0492   0.1044   1.0000
  14.000   1.3796   0.05422   0.04791  -0.0485   0.0919   1.0000
  14.250   1.3766   0.05742   0.05110  -0.0480   0.0806   1.0000
  14.500   1.3729   0.06080   0.05449  -0.0476   0.0708   1.0000
  14.750   1.3674   0.06447   0.05816  -0.0473   0.0627   1.0000
  15.000   1.3620   0.06827   0.06197  -0.0472   0.0558   1.0000
  15.250   1.3595   0.07183   0.06562  -0.0473   0.0494   1.0000
  15.500   1.3512   0.07618   0.06995  -0.0475   0.0447   1.0000
  15.750   1.3504   0.07972   0.07363  -0.0479   0.0398   1.0000
  16.000   1.3419   0.08425   0.07814  -0.0484   0.0363   1.0000
  16.250   1.3412   0.08799   0.08205  -0.0491   0.0326   1.0000
  16.500   1.3349   0.09242   0.08651  -0.0500   0.0299   1.0000
  16.750   1.3321   0.09649   0.09072  -0.0508   0.0270   1.0000
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