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EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 435 AIRFOIL (e435-il)
Reynolds number: 100,000
Max Cl/Cd: 48.02 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e435-il-100000.txt
Download as CSV file: xf-e435-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 435 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2705   0.11398   0.10966  -0.0659   0.9632   0.1062
  -9.000  -0.2764   0.10994   0.10565  -0.0726   0.9588   0.1121
  -8.750  -0.3250   0.10671   0.10254  -0.0788   0.9491   0.1134
  -8.500  -0.2695   0.10315   0.09892  -0.0736   0.9488   0.1176
  -8.250  -0.2578   0.09981   0.09556  -0.0764   0.9455   0.1236
  -8.000  -0.2886   0.09715   0.09300  -0.0780   0.9368   0.1271
  -7.750  -0.3525   0.09319   0.08909  -0.0841   0.9276   0.1283
  -7.500  -0.2686   0.09014   0.08600  -0.0811   0.9300   0.1384
  -7.250  -0.3007   0.08864   0.08458  -0.0777   0.9209   0.1395
  -7.000  -0.3453   0.08329   0.07921  -0.0849   0.9132   0.1427
  -6.000  -0.3859   0.05648   0.05021  -0.0912   0.8910   0.0622
  -5.750  -0.3643   0.05262   0.04631  -0.0923   0.8876   0.0600
  -5.500  -0.3275   0.04782   0.04022  -0.0953   0.8846   0.0533
  -5.250  -0.2944   0.04507   0.03705  -0.0973   0.8816   0.0533
  -5.000  -0.2846   0.04363   0.03535  -0.0951   0.8767   0.0533
  -4.750  -0.2581   0.04168   0.03308  -0.0954   0.8729   0.0534
  -4.500  -0.2244   0.03948   0.03075  -0.0966   0.8697   0.0548
  -4.250  -0.1838   0.03818   0.02937  -0.0988   0.8670   0.0593
  -4.000  -0.1756   0.03774   0.02880  -0.0961   0.8617   0.0638
  -3.750  -0.1540   0.03701   0.02814  -0.0954   0.8571   0.0700
  -3.500  -0.1207   0.03608   0.02723  -0.0964   0.8535   0.0851
  -3.250  -0.0797   0.03470   0.02622  -0.0991   0.8509   0.1228
  -3.000  -0.0544   0.03199   0.02566  -0.1017   0.8468   0.4345
  -2.750  -0.0498   0.03350   0.02756  -0.0959   0.8407   0.6267
  -2.500  -0.0324   0.03487   0.02886  -0.0916   0.8364   0.6710
  -2.250  -0.0217   0.03600   0.02994  -0.0871   0.8318   0.6980
  -2.000  -0.0220   0.03685   0.03076  -0.0819   0.8252   0.7162
  -1.750  -0.0048   0.03757   0.03137  -0.0785   0.8206   0.7404
  -1.500   0.0185   0.03815   0.03184  -0.0755   0.8175   0.7626
  -1.250   0.0110   0.03882   0.03248  -0.0708   0.8095   0.7757
  -1.000   0.0236   0.03915   0.03274  -0.0668   0.8046   0.7940
  -0.750   0.0403   0.03939   0.03291  -0.0624   0.8013   0.8174
  -0.500   0.0271   0.03987   0.03341  -0.0565   0.7928   0.8313
  -0.250   0.0428   0.03995   0.03341  -0.0536   0.7880   0.8491
   0.000   0.0858   0.04006   0.03332  -0.0561   0.7848   0.8578
   0.250   0.0790   0.04059   0.03384  -0.0523   0.7756   0.8642
   0.500   0.1178   0.04075   0.03384  -0.0548   0.7709   0.8699
   0.750   0.1365   0.04116   0.03417  -0.0545   0.7642   0.8749
   1.000   0.1573   0.04152   0.03445  -0.0545   0.7574   0.8798
   1.250   0.2008   0.04159   0.03440  -0.0574   0.7534   0.8843
   1.500   0.2080   0.04235   0.03512  -0.0561   0.7445   0.8893
   1.750   0.2409   0.04249   0.03518  -0.0574   0.7391   0.8937
   2.000   0.2879   0.04246   0.03505  -0.0604   0.7360   0.8983
   2.250   0.2882   0.04347   0.03606  -0.0585   0.7248   0.9040
   2.500   0.3299   0.04338   0.03590  -0.0607   0.7209   0.9087
   2.750   0.3379   0.04438   0.03690  -0.0597   0.7107   0.9146
   3.000   0.3756   0.04433   0.03680  -0.0613   0.7058   0.9204
   3.250   0.4227   0.04402   0.03644  -0.0639   0.7031   0.9268
   3.500   0.4223   0.04522   0.03768  -0.0620   0.6907   0.9348
   3.750   0.4687   0.04488   0.03731  -0.0645   0.6876   0.9421
   4.000   0.4740   0.04612   0.03860  -0.0635   0.6755   0.9527
   4.250   0.5243   0.04572   0.03821  -0.0668   0.6722   0.9646
   4.500   0.5380   0.04696   0.03951  -0.0674   0.6600   1.0000
   4.750   0.5893   0.04654   0.03907  -0.0709   0.6565   1.0000
   5.000   0.6029   0.04807   0.04063  -0.0715   0.6447   1.0000
   5.250   0.6533   0.04754   0.04012  -0.0747   0.6411   1.0000
   5.500   0.6692   0.04898   0.04159  -0.0754   0.6294   1.0000
   5.750   0.7186   0.04833   0.04096  -0.0784   0.6257   1.0000
   6.000   0.7742   0.04717   0.03985  -0.0817   0.6236   1.0000
   6.250   0.7853   0.04878   0.04151  -0.0817   0.6102   1.0000
   6.500   0.8405   0.04736   0.04014  -0.0847   0.6082   1.0000
   7.000   0.8709   0.05001   0.04291  -0.0850   0.5837   1.0000
   7.250   0.9189   0.04865   0.04162  -0.0869   0.5796   1.0000
   7.500   0.9752   0.04642   0.03949  -0.0892   0.5779   1.0000
   7.750   1.0344   0.04363   0.03681  -0.0914   0.5769   1.0000
   8.000   1.0992   0.04031   0.03360  -0.0940   0.5764   1.0000
   8.500   1.1256   0.04193   0.03538  -0.0919   0.5508   1.0000
   8.750   1.1982   0.03785   0.03145  -0.0949   0.5491   1.0000
   9.000   1.2956   0.03273   0.02645  -0.1010   0.5461   1.0000
   9.250   1.3201   0.03241   0.02622  -0.1003   0.5323   1.0000
   9.500   1.3533   0.03160   0.02547  -0.1005   0.5179   1.0000
   9.750   1.3859   0.03089   0.02479  -0.1006   0.5018   1.0000
  10.000   1.4154   0.03043   0.02434  -0.1004   0.4841   1.0000
  10.250   1.4450   0.03009   0.02395  -0.1002   0.4649   1.0000
  10.500   1.4484   0.03104   0.02492  -0.0971   0.4458   1.0000
  10.750   1.4553   0.03193   0.02582  -0.0946   0.4259   1.0000
  11.000   1.4649   0.03275   0.02659  -0.0925   0.4055   1.0000
  11.250   1.4768   0.03356   0.02728  -0.0906   0.3848   1.0000
  11.500   1.4760   0.03510   0.02883  -0.0877   0.3652   1.0000
  11.750   1.4770   0.03665   0.03035  -0.0851   0.3456   1.0000
  12.000   1.4789   0.03824   0.03188  -0.0828   0.3263   1.0000
  12.250   1.4818   0.03985   0.03340  -0.0806   0.3074   1.0000
  12.500   1.4820   0.04173   0.03522  -0.0785   0.2892   1.0000
  12.750   1.4794   0.04388   0.03736  -0.0763   0.2718   1.0000
  13.000   1.4772   0.04610   0.03958  -0.0743   0.2549   1.0000
  13.250   1.4750   0.04844   0.04190  -0.0725   0.2385   1.0000
  13.500   1.4730   0.05087   0.04431  -0.0709   0.2228   1.0000
  13.750   1.4711   0.05341   0.04682  -0.0695   0.2078   1.0000
  14.000   1.4691   0.05606   0.04946  -0.0682   0.1935   1.0000
  14.250   1.4677   0.05876   0.05213  -0.0670   0.1800   1.0000
  14.500   1.4667   0.06150   0.05482  -0.0660   0.1670   1.0000
  14.750   1.4663   0.06427   0.05753  -0.0652   0.1547   1.0000
  15.000   1.4612   0.06765   0.06105  -0.0645   0.1439   1.0000
  15.250   1.4597   0.07078   0.06423  -0.0639   0.1334   1.0000
  15.500   1.4605   0.07371   0.06712  -0.0634   0.1235   1.0000
  15.750   1.4618   0.07658   0.06996  -0.0630   0.1144   1.0000
  16.000   1.4579   0.08028   0.07386  -0.0628   0.1066   1.0000
  16.250   1.4624   0.08297   0.07649  -0.0626   0.0987   1.0000
  16.500   1.4586   0.08668   0.08036  -0.0627   0.0924   1.0000
  16.750   1.4624   0.08960   0.08330  -0.0626   0.0860   1.0000
  17.000   1.4590   0.09337   0.08723  -0.0630   0.0808   1.0000
  17.250   1.4646   0.09612   0.08996  -0.0630   0.0752   1.0000
  17.500   1.4571   0.10059   0.09470  -0.0638   0.0715   1.0000
  17.750   1.4704   0.10231   0.09625  -0.0636   0.0660   1.0000
  18.000   1.4573   0.10764   0.10196  -0.0650   0.0638   1.0000
  18.250   1.4485   0.11246   0.10702  -0.0664   0.0611   1.0000
  18.500   1.4637   0.11387   0.10825  -0.0663   0.0566   1.0000
  18.750   1.4458   0.12012   0.11487  -0.0686   0.0555   1.0000
  19.000   1.4291   0.12646   0.12153  -0.0714   0.0543   1.0000
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