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EPPLER 818 HYDROFOIL AIRFOIL (e818-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 818 HYDROFOIL AIRFOIL (e818-il)
Reynolds number: 100,000
Max Cl/Cd: 66.08 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e818-il-100000.txt
Download as CSV file: xf-e818-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 818 HYDROFOIL 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  -0.4663   0.10672   0.10201  -0.0362   1.0000   0.1026
  -9.000  -0.4757   0.10421   0.09959  -0.0360   1.0000   0.1076
  -8.750  -0.5198   0.10273   0.09830  -0.0392   1.0000   0.1101
  -5.750  -0.5477   0.04118   0.03476  -0.0582   1.0000   0.0433
  -5.500  -0.5174   0.03689   0.02948  -0.0594   1.0000   0.0344
  -5.250  -0.4918   0.03354   0.02587  -0.0598   1.0000   0.0315
  -5.000  -0.4637   0.03034   0.02224  -0.0604   1.0000   0.0292
  -4.750  -0.4357   0.02786   0.01938  -0.0603   1.0000   0.0274
  -4.500  -0.4086   0.02587   0.01713  -0.0598   1.0000   0.0262
  -4.250  -0.3821   0.02422   0.01523  -0.0593   1.0000   0.0258
  -4.000  -0.3549   0.02283   0.01376  -0.0593   1.0000   0.0262
  -3.750  -0.3255   0.02163   0.01237  -0.0600   1.0000   0.0279
  -3.500  -0.2951   0.02068   0.01111  -0.0607   1.0000   0.0316
  -3.250  -0.2515   0.01759   0.00986  -0.0658   1.0000   0.3906
  -3.000  -0.2374   0.01888   0.01163  -0.0620   1.0000   0.5341
  -2.750  -0.2139   0.01882   0.01140  -0.0612   1.0000   0.5528
  -2.500  -0.1896   0.01878   0.01121  -0.0607   1.0000   0.5733
  -2.250  -0.1669   0.01878   0.01114  -0.0599   1.0000   0.5919
  -2.000  -0.1432   0.01878   0.01094  -0.0594   1.0000   0.6130
  -1.750  -0.1213   0.01882   0.01097  -0.0584   1.0000   0.6321
  -1.500  -0.0987   0.01888   0.01099  -0.0577   1.0000   0.6531
  -1.250  -0.0773   0.01895   0.01107  -0.0567   1.0000   0.6730
  -1.000  -0.0558   0.01904   0.01117  -0.0558   1.0000   0.6943
  -0.750  -0.0345   0.01915   0.01130  -0.0549   1.0000   0.7164
  -0.500  -0.0149   0.01926   0.01146  -0.0536   1.0000   0.7380
  -0.250   0.0047   0.01938   0.01158  -0.0523   1.0000   0.7614
   0.000   0.0237   0.01951   0.01175  -0.0509   1.0000   0.7866
   0.250   0.0415   0.01963   0.01193  -0.0492   1.0000   0.8136
   0.500   0.0573   0.01972   0.01210  -0.0471   1.0000   0.8449
   0.750   0.0700   0.01971   0.01221  -0.0444   1.0000   0.8850
   1.000   0.0809   0.01917   0.01185  -0.0422   1.0000   1.0000
   1.250   0.1167   0.01967   0.01226  -0.0457   1.0000   1.0000
   1.500   0.1472   0.02020   0.01270  -0.0479   1.0000   1.0000
   1.750   0.1745   0.02075   0.01320  -0.0493   1.0000   1.0000
   2.000   0.2076   0.02148   0.01392  -0.0518   0.9965   1.0000
   2.250   0.2529   0.02244   0.01491  -0.0564   0.9863   1.0000
   2.500   0.2966   0.02334   0.01587  -0.0606   0.9760   1.0000
   2.750   0.3396   0.02413   0.01690  -0.0644   0.9654   1.0000
   3.000   0.3842   0.02490   0.01782  -0.0684   0.9550   1.0000
   3.250   0.4270   0.02549   0.01859  -0.0719   0.9433   1.0000
   3.500   0.4710   0.02595   0.01928  -0.0754   0.9303   1.0000
   3.750   0.5121   0.02621   0.01981  -0.0780   0.9150   1.0000
   4.000   0.5579   0.02621   0.02027  -0.0810   0.8973   1.0000
   4.250   0.6978   0.01056   0.00143  -0.0795   0.0419   1.0000
   4.500   0.7197   0.01337   0.00412  -0.0784   0.0387   1.0000
   4.750   0.7558   0.01593   0.00672  -0.0791   0.0377   1.0000
   5.000   0.7954   0.01900   0.00993  -0.0802   0.0378   1.0000
   5.250   0.8308   0.02208   0.01325  -0.0805   0.0393   1.0000
   5.500   0.8608   0.02447   0.01641  -0.0782   0.0462   1.0000
   5.750   0.8892   0.02851   0.02111  -0.0759   0.0602   1.0000
   9.750   0.9320   0.10802   0.10420  -0.0535   0.0760   1.0000
  10.000   0.9113   0.11331   0.10956  -0.0565   0.0759   1.0000
  10.250   0.8930   0.11984   0.11612  -0.0620   0.0757   1.0000
  10.500   0.8768   0.12735   0.12358  -0.0700   0.0751   1.0000
  10.750   0.8658   0.13374   0.12991  -0.0761   0.0728   1.0000
  11.000   0.8635   0.13906   0.13521  -0.0794   0.0698   1.0000
  11.250   0.8696   0.14336   0.13950  -0.0800   0.0665   1.0000
  11.500   0.7508   0.14779   0.14425  -0.0728   0.0760   1.0000
  11.750   0.7392   0.15153   0.14799  -0.0763   0.0755   1.0000
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