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EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 200,000
Max Cl/Cd: 81.53 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e433-il-200000.txt
Download as CSV file: xf-e433-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 433 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  -0.2168   0.09933   0.09591  -0.0835   0.9643   0.0397
  -9.250  -0.2087   0.09460   0.09119  -0.0887   0.9615   0.0423
  -9.000  -0.2077   0.08910   0.08571  -0.0961   0.9571   0.0437
  -8.750  -0.1052   0.07343   0.07019  -0.1005   0.9396   0.0508
  -8.500  -0.1146   0.06734   0.06411  -0.1065   0.9355   0.0534
  -8.250  -0.1192   0.06063   0.05739  -0.1132   0.9330   0.0534
  -8.000  -0.2635   0.07187   0.06810  -0.1118   0.9242   0.0445
  -7.750  -0.2381   0.06671   0.06323  -0.1120   0.9240   0.0461
  -7.500  -0.2266   0.06403   0.06053  -0.1130   0.9203   0.0479
  -7.250  -0.2149   0.05995   0.05628  -0.1167   0.9173   0.0511
  -7.000  -0.2310   0.05828   0.05454  -0.1123   0.9070   0.0510
  -6.750  -0.2291   0.05304   0.04870  -0.1151   0.9027   0.0558
  -6.500  -0.2103   0.05120   0.04708  -0.1150   0.8997   0.0593
  -6.250  -0.2156   0.04981   0.04559  -0.1110   0.8908   0.0610
  -6.000  -0.1975   0.04590   0.04120  -0.1129   0.8881   0.0688
  -5.750  -0.1866   0.04415   0.03948  -0.1113   0.8832   0.0715
  -5.250  -0.1515   0.03288   0.02652  -0.1076   0.8740   0.0373
  -5.000  -0.1142   0.02961   0.02244  -0.1080   0.8729   0.0290
  -4.750  -0.0777   0.02674   0.01934  -0.1098   0.8721   0.0281
  -4.500  -0.0819   0.02649   0.01899  -0.1041   0.8624   0.0279
  -4.250  -0.0491   0.02494   0.01724  -0.1047   0.8604   0.0280
  -4.000  -0.0131   0.02376   0.01590  -0.1060   0.8590   0.0290
  -3.750   0.0231   0.02223   0.01445  -0.1077   0.8580   0.0321
  -3.500   0.0623   0.02119   0.01343  -0.1100   0.8571   0.0394
  -3.250   0.0561   0.02159   0.01380  -0.1041   0.8467   0.0438
  -3.000   0.0918   0.02013   0.01260  -0.1060   0.8450   0.0914
  -2.750   0.1250   0.01734   0.01211  -0.1090   0.8439   0.5872
  -2.500   0.1551   0.01764   0.01264  -0.1077   0.8425   0.7381
  -2.250   0.1511   0.01850   0.01349  -0.1014   0.8328   0.7589
  -2.000   0.1774   0.01877   0.01368  -0.0999   0.8300   0.7855
  -1.750   0.2046   0.01895   0.01378  -0.0982   0.8281   0.8057
  -1.500   0.2338   0.01901   0.01376  -0.0971   0.8267   0.8232
  -1.250   0.2249   0.01969   0.01444  -0.0903   0.8158   0.8339
  -1.000   0.2528   0.01960   0.01426  -0.0893   0.8137   0.8479
  -0.750   0.2762   0.01949   0.01409  -0.0868   0.8121   0.8651
  -0.500   0.2597   0.02009   0.01472  -0.0781   0.8010   0.8806
  -0.250   0.2755   0.01980   0.01439  -0.0741   0.7984   0.9003
   0.000   0.3109   0.01940   0.01389  -0.0749   0.7971   0.9083
   0.250   0.3532   0.01903   0.01343  -0.0776   0.7960   0.9113
   0.500   0.3972   0.01864   0.01294  -0.0806   0.7950   0.9137
   1.000   0.4342   0.01863   0.01286  -0.0779   0.7821   0.9223
   1.250   0.4786   0.01819   0.01236  -0.0809   0.7809   0.9239
   1.500   0.4779   0.01855   0.01273  -0.0762   0.7704   0.9304
   1.750   0.5222   0.01814   0.01227  -0.0794   0.7685   0.9320
   2.000   0.5667   0.01768   0.01176  -0.0825   0.7668   0.9336
   2.250   0.6118   0.01719   0.01123  -0.0856   0.7653   0.9352
   2.500   0.6150   0.01742   0.01150  -0.0814   0.7550   0.9412
   2.750   0.6594   0.01693   0.01098  -0.0845   0.7525   0.9428
   3.000   0.7064   0.01644   0.01046  -0.0881   0.7504   0.9442
   3.250   0.7147   0.01656   0.01063  -0.0847   0.7406   0.9504
   3.500   0.7586   0.01608   0.01014  -0.0877   0.7373   0.9524
   3.750   0.7856   0.01594   0.01003  -0.0877   0.7306   0.9566
   4.000   0.8173   0.01567   0.00978  -0.0886   0.7241   0.9603
   4.250   0.8654   0.01517   0.00925  -0.0923   0.7202   0.9615
   4.500   0.8845   0.01516   0.00933  -0.0910   0.7100   0.9680
   4.750   0.9298   0.01473   0.00889  -0.0943   0.7046   0.9703
   5.000   0.9552   0.01469   0.00893  -0.0942   0.6939   0.9761
   5.250   0.9889   0.01454   0.00883  -0.0956   0.6842   0.9808
   5.500   1.0298   0.01426   0.00854  -0.0982   0.6753   0.9840
   5.750   1.0603   0.01423   0.00858  -0.0991   0.6626   0.9915
   6.000   1.0821   0.01418   0.00858  -0.0984   0.6495   1.0000
   6.250   1.1027   0.01417   0.00860  -0.0974   0.6358   1.0000
   6.500   1.1254   0.01419   0.00864  -0.0967   0.6206   1.0000
   6.750   1.1482   0.01425   0.00871  -0.0961   0.6041   1.0000
   7.000   1.1716   0.01437   0.00880  -0.0956   0.5859   1.0000
   7.250   1.1904   0.01462   0.00905  -0.0944   0.5657   1.0000
   7.500   1.2091   0.01494   0.00934  -0.0932   0.5439   1.0000
   7.750   1.2269   0.01534   0.00969  -0.0919   0.5210   1.0000
   8.000   1.2423   0.01585   0.01012  -0.0902   0.4966   1.0000
   8.250   1.2559   0.01644   0.01065  -0.0883   0.4720   1.0000
   8.500   1.2678   0.01714   0.01125  -0.0862   0.4471   1.0000
   8.750   1.2778   0.01792   0.01197  -0.0838   0.4221   1.0000
   9.000   1.2867   0.01878   0.01275  -0.0814   0.3978   1.0000
   9.250   1.2945   0.01973   0.01361  -0.0789   0.3742   1.0000
   9.500   1.3017   0.02074   0.01457  -0.0764   0.3507   1.0000
   9.750   1.3079   0.02186   0.01560  -0.0739   0.3284   1.0000
  10.000   1.3141   0.02302   0.01672  -0.0716   0.3060   1.0000
  10.250   1.3194   0.02429   0.01792  -0.0692   0.2844   1.0000
  10.500   1.3246   0.02562   0.01920  -0.0670   0.2637   1.0000
  10.750   1.3297   0.02702   0.02056  -0.0648   0.2427   1.0000
  11.000   1.3335   0.02857   0.02203  -0.0627   0.2233   1.0000
  11.250   1.3382   0.03012   0.02355  -0.0608   0.2039   1.0000
  11.500   1.3426   0.03176   0.02517  -0.0590   0.1853   1.0000
  11.750   1.3459   0.03354   0.02690  -0.0572   0.1680   1.0000
  12.000   1.3485   0.03544   0.02876  -0.0555   0.1520   1.0000
  12.250   1.3508   0.03745   0.03073  -0.0539   0.1371   1.0000
  12.750   1.3548   0.04176   0.03499  -0.0510   0.1103   1.0000
  13.000   1.3569   0.04403   0.03728  -0.0497   0.0986   1.0000
  13.250   1.3590   0.04638   0.03966  -0.0486   0.0881   1.0000
  13.500   1.3598   0.04893   0.04226  -0.0476   0.0790   1.0000
  13.750   1.3573   0.05187   0.04516  -0.0465   0.0718   1.0000
  14.000   1.3598   0.05442   0.04781  -0.0458   0.0648   1.0000
  14.250   1.3587   0.05742   0.05085  -0.0451   0.0591   1.0000
  14.500   1.3595   0.06028   0.05379  -0.0446   0.0540   1.0000
  14.750   1.3579   0.06348   0.05702  -0.0441   0.0499   1.0000
  15.000   1.3596   0.06642   0.06008  -0.0440   0.0458   1.0000
  15.250   1.3570   0.06985   0.06348  -0.0437   0.0425   1.0000
  15.500   1.3589   0.07291   0.06674  -0.0437   0.0395   1.0000
  15.750   1.3590   0.07623   0.07016  -0.0439   0.0367   1.0000
  16.000   1.3584   0.07954   0.07342  -0.0438   0.0341   1.0000
  16.250   1.3581   0.08314   0.07727  -0.0443   0.0320   1.0000
  16.500   1.3568   0.08686   0.08110  -0.0451   0.0297   1.0000
  16.750   1.3564   0.09027   0.08447  -0.0455   0.0276   1.0000
  17.000   1.3539   0.09434   0.08877  -0.0464   0.0259   1.0000
  17.250   1.3507   0.09857   0.09317  -0.0477   0.0242   1.0000
  17.500   1.3484   0.10259   0.09721  -0.0491   0.0227   1.0000
  17.750   1.3451   0.10677   0.10150  -0.0502   0.0211   1.0000
  18.000   1.3392   0.11172   0.10668  -0.0523   0.0198   1.0000
  18.250   1.3348   0.11637   0.11144  -0.0544   0.0186   1.0000
  18.500   1.3342   0.12004   0.11506  -0.0559   0.0173   1.0000
  18.750   1.3251   0.12580   0.12107  -0.0587   0.0164   1.0000
  19.000   1.3175   0.13136   0.12686  -0.0616   0.0156   1.0000
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