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EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 403 AIRFOIL (e403-il)
Reynolds number: 200,000
Max Cl/Cd: 66.92 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e403-il-200000.txt
Download as CSV file: xf-e403-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 403 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4776   0.09437   0.09154  -0.0364   1.0000   0.0718
  -9.250  -0.5006   0.08715   0.08436  -0.0392   1.0000   0.0730
  -9.000  -0.5426   0.07801   0.07520  -0.0431   1.0000   0.0726
  -8.750  -0.5914   0.07075   0.06787  -0.0447   1.0000   0.0715
  -8.500  -0.7466   0.07413   0.07072  -0.0432   1.0000   0.0647
  -8.250  -0.7782   0.07275   0.06884  -0.0426   1.0000   0.0661
  -6.750  -0.7213   0.03902   0.03243  -0.0426   1.0000   0.0348
  -6.500  -0.7012   0.03510   0.02840  -0.0423   0.9999   0.0329
  -6.250  -0.6144   0.03176   0.02447  -0.0534   0.9803   0.0310
  -6.000  -0.5758   0.03028   0.02274  -0.0556   0.9748   0.0307
  -5.750  -0.5401   0.02927   0.02161  -0.0572   0.9677   0.0323
  -5.500  -0.5106   0.02851   0.02075  -0.0579   0.9641   0.0335
  -5.250  -0.4744   0.02785   0.02002  -0.0597   0.9608   0.0344
  -5.000  -0.4440   0.02670   0.01887  -0.0608   0.9559   0.0355
  -4.750  -0.4149   0.02567   0.01788  -0.0622   0.9518   0.0374
  -4.500  -0.3778   0.02502   0.01719  -0.0650   0.9487   0.0409
  -4.250  -0.3337   0.02432   0.01644  -0.0693   0.9464   0.0510
  -4.000  -0.2725   0.02102   0.01560  -0.0804   0.9463   0.5324
  -3.750  -0.2483   0.02155   0.01611  -0.0795   0.9408   0.5703
  -3.500  -0.2244   0.02248   0.01703  -0.0780   0.9355   0.5986
  -3.250  -0.1920   0.02369   0.01817  -0.0779   0.9321   0.6216
  -3.000  -0.1795   0.02470   0.01927  -0.0736   0.9250   0.6340
  -2.750  -0.1599   0.02575   0.02036  -0.0705   0.9199   0.6454
  -2.500  -0.1287   0.02673   0.02130  -0.0699   0.9168   0.6572
  -2.250  -0.1144   0.02696   0.02151  -0.0672   0.9091   0.6638
  -2.000  -0.0786   0.02698   0.02140  -0.0693   0.9053   0.6706
  -1.750  -0.0437   0.02724   0.02161  -0.0703   0.9026   0.6737
  -1.500  -0.0228   0.02722   0.02155  -0.0694   0.8954   0.6777
  -1.250   0.0190   0.02701   0.02118  -0.0735   0.8915   0.6843
  -1.000   0.0547   0.02702   0.02116  -0.0748   0.8885   0.6864
  -0.750   0.0777   0.02704   0.02116  -0.0741   0.8819   0.6889
  -0.500   0.1097   0.02695   0.02104  -0.0751   0.8767   0.6921
  -0.250   0.1522   0.02678   0.02080  -0.0784   0.8741   0.6961
   0.000   0.1926   0.02658   0.02052  -0.0816   0.8704   0.7004
   0.250   0.2145   0.02647   0.02043  -0.0806   0.8625   0.7025
   0.500   0.2537   0.02624   0.02020  -0.0826   0.8597   0.7048
   0.750   0.2944   0.02598   0.01993  -0.0851   0.8571   0.7077
   1.000   0.3180   0.02584   0.01978  -0.0849   0.8478   0.7117
   1.250   0.3642   0.02540   0.01931  -0.0889   0.8454   0.7153
   1.500   0.4020   0.02501   0.01897  -0.0905   0.8425   0.7173
   1.750   0.4226   0.02489   0.01889  -0.0892   0.8332   0.7198
   2.000   0.4641   0.02440   0.01844  -0.0916   0.8308   0.7226
   2.250   0.5074   0.02384   0.01791  -0.0944   0.8285   0.7257
   2.500   0.5342   0.02363   0.01772  -0.0948   0.8187   0.7294
   2.750   0.5771   0.02286   0.01702  -0.0972   0.8164   0.7319
   3.000   0.6203   0.02200   0.01625  -0.0993   0.8145   0.7342
   3.250   0.6421   0.02172   0.01603  -0.0981   0.8036   0.7369
   3.500   0.6875   0.02069   0.01508  -0.1008   0.8015   0.7397
   3.750   0.7152   0.02029   0.01476  -0.1008   0.7914   0.7433
   4.000   0.7600   0.01921   0.01376  -0.1034   0.7881   0.7464
   4.250   0.7868   0.01866   0.01331  -0.1027   0.7778   0.7487
   4.500   0.8314   0.01754   0.01230  -0.1050   0.7718   0.7511
   4.750   0.8626   0.01694   0.01178  -0.1052   0.7574   0.7540
   5.000   0.8962   0.01639   0.01129  -0.1059   0.7387   0.7575
   5.250   0.9360   0.01581   0.01074  -0.1079   0.7151   0.7610
   5.500   0.9743   0.01533   0.01025  -0.1093   0.6839   0.7633
   5.750   1.0084   0.01521   0.01001  -0.1101   0.6425   0.7658
   6.000   1.0339   0.01545   0.01005  -0.1095   0.5945   0.7686
   6.250   1.0509   0.01597   0.01032  -0.1076   0.5461   0.7720
   6.500   1.0644   0.01665   0.01074  -0.1053   0.4985   0.7758
   6.750   1.0719   0.01731   0.01124  -0.1017   0.4550   0.7785
   7.000   1.0801   0.01805   0.01179  -0.0985   0.4127   0.7815
   7.250   1.0888   0.01886   0.01241  -0.0955   0.3705   0.7847
   7.500   1.0994   0.01972   0.01308  -0.0932   0.3293   0.7882
   7.750   1.1106   0.02060   0.01379  -0.0910   0.2881   0.7915
   8.000   1.1194   0.02150   0.01453  -0.0883   0.2499   0.7945
   8.250   1.1303   0.02243   0.01533  -0.0861   0.2128   0.7981
   8.500   1.1419   0.02350   0.01620  -0.0842   0.1762   0.8018
   8.750   1.1551   0.02463   0.01715  -0.0828   0.1383   0.8054
   9.000   1.1627   0.02600   0.01828  -0.0803   0.0960   0.8082
   9.250   1.1630   0.02815   0.02008  -0.0769   0.0527   0.8113
   9.500   1.1690   0.02988   0.02180  -0.0743   0.0415   0.8150
   9.750   1.1746   0.03171   0.02365  -0.0720   0.0369   0.8190
  10.000   1.1860   0.03298   0.02504  -0.0702   0.0337   0.8226
  10.250   1.1946   0.03442   0.02656  -0.0682   0.0314   0.8263
  10.500   1.1982   0.03658   0.02875  -0.0659   0.0297   0.8300
  10.750   1.2109   0.03813   0.03042  -0.0646   0.0287   0.8341
  11.000   1.2233   0.03969   0.03211  -0.0632   0.0278   0.8378
  11.250   1.2361   0.04129   0.03384  -0.0618   0.0269   0.8421
  11.500   1.2513   0.04297   0.03565  -0.0608   0.0261   0.8470
  11.750   1.2679   0.04472   0.03750  -0.0600   0.0254   0.8517
  12.000   1.2848   0.04649   0.03939  -0.0590   0.0249   0.8564
  12.250   1.3035   0.04849   0.04149  -0.0585   0.0243   0.8615
  12.500   1.3290   0.05122   0.04432  -0.0588   0.0235   0.8664
  12.750   1.3395   0.05412   0.04751  -0.0575   0.0231   0.8717
  13.000   1.3411   0.05657   0.05025  -0.0556   0.0228   0.8782
  13.250   1.3414   0.05937   0.05335  -0.0536   0.0226   0.8846
  13.500   1.3399   0.06267   0.05696  -0.0519   0.0226   0.8918
  13.750   1.3340   0.06616   0.06075  -0.0500   0.0226   0.8994
  14.000   1.3250   0.07002   0.06491  -0.0485   0.0226   0.9085
  14.250   1.3124   0.07398   0.06917  -0.0468   0.0227   0.9207
  14.500   1.2951   0.07766   0.07312  -0.0448   0.0228   0.9617
  14.750   1.2807   0.08291   0.07863  -0.0452   0.0229   1.0000
  15.000   1.2656   0.08877   0.08473  -0.0463   0.0230   1.0000
  15.250   1.2507   0.09523   0.09140  -0.0480   0.0232   1.0000
  15.500   1.2376   0.10102   0.09741  -0.0504   0.0234   1.0000
  15.750   1.2214   0.10705   0.10366  -0.0536   0.0235   1.0000
  16.000   1.2012   0.11429   0.11114  -0.0582   0.0237   1.0000
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