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EPPLER 874 HYDROFOIL AIRFOIL (e874-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 874 HYDROFOIL AIRFOIL (e874-il)
Reynolds number: 100,000
Max Cl/Cd: 41.19 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e874-il-100000.txt
Download as CSV file: xf-e874-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 874 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5681   0.10849   0.10360   0.0007   1.0000   0.1039
  -9.250  -0.5688   0.10493   0.10007  -0.0011   1.0000   0.1085
  -9.000  -0.5988   0.10213   0.09745  -0.0097   1.0000   0.1116
  -8.750  -0.5773   0.09672   0.09201  -0.0056   1.0000   0.1142
  -8.500  -0.5693   0.09324   0.08854  -0.0051   1.0000   0.1174
  -7.750  -0.5914   0.08114   0.07667  -0.0124   1.0000   0.1280
  -7.500  -0.5874   0.07734   0.07289  -0.0128   1.0000   0.1307
  -6.750  -0.6171   0.05090   0.04536  -0.0266   1.0000   0.0742
  -6.500  -0.6062   0.04381   0.03798  -0.0252   1.0000   0.0558
  -6.250  -0.5978   0.03824   0.03146  -0.0227   1.0000   0.0471
  -6.000  -0.5851   0.03397   0.02683  -0.0208   1.0000   0.0447
  -5.750  -0.5692   0.03036   0.02268  -0.0187   1.0000   0.0423
  -5.500  -0.5501   0.02726   0.01898  -0.0166   1.0000   0.0406
  -5.250  -0.5281   0.02471   0.01602  -0.0148   1.0000   0.0400
  -5.000  -0.5053   0.02260   0.01366  -0.0132   1.0000   0.0405
  -4.750  -0.4830   0.02081   0.01174  -0.0116   1.0000   0.0425
  -4.500  -0.4615   0.01935   0.01015  -0.0099   1.0000   0.0462
  -4.250  -0.4421   0.01787   0.00866  -0.0081   1.0000   0.0567
  -4.000  -0.4260   0.01546   0.00705  -0.0055   1.0000   0.1561
  -3.750  -0.4074   0.01512   0.00695  -0.0040   1.0000   0.2901
  -3.500  -0.3875   0.01478   0.00667  -0.0025   1.0000   0.3414
  -3.250  -0.3656   0.01412   0.00612  -0.0012   1.0000   0.3827
  -3.000  -0.3444   0.01336   0.00561   0.0003   1.0000   0.4370
  -2.750  -0.3242   0.01251   0.00520   0.0020   1.0000   0.5240
  -2.500  -0.3021   0.01154   0.00494   0.0040   1.0000   0.6803
  -2.250  -0.1568   0.01151   0.00495  -0.0175   1.0000   0.9840
  -2.000  -0.1123   0.01139   0.00453  -0.0215   1.0000   1.0000
  -1.750  -0.0951   0.01127   0.00422  -0.0199   1.0000   1.0000
  -1.500  -0.0770   0.01120   0.00402  -0.0183   1.0000   1.0000
  -1.250  -0.0587   0.01116   0.00388  -0.0167   1.0000   1.0000
  -1.000  -0.0404   0.01115   0.00378  -0.0151   1.0000   1.0000
  -0.750  -0.0224   0.01118   0.00375  -0.0135   1.0000   1.0000
  -0.500  -0.0051   0.01123   0.00375  -0.0118   1.0000   1.0000
  -0.250   0.0107   0.01135   0.00384  -0.0099   1.0000   1.0000
   0.000   0.0233   0.01155   0.00404  -0.0077   1.0000   1.0000
   0.250   0.0297   0.01195   0.00444  -0.0049   1.0000   1.0000
   0.500   0.1011   0.01208   0.00462  -0.0146   0.9774   1.0000
   0.750   0.1663   0.01201   0.00463  -0.0226   0.9509   1.0000
   1.000   0.2326   0.01179   0.00450  -0.0304   0.9231   1.0000
   1.250   0.2952   0.01156   0.00434  -0.0371   0.8883   1.0000
   1.500   0.3424   0.01154   0.00434  -0.0405   0.8468   1.0000
   1.750   0.3757   0.01174   0.00447  -0.0410   0.8093   1.0000
   2.000   0.4027   0.01203   0.00471  -0.0405   0.7774   1.0000
   2.250   0.4279   0.01236   0.00501  -0.0396   0.7507   1.0000
   2.500   0.4524   0.01272   0.00542  -0.0386   0.7276   1.0000
   2.750   0.4763   0.01308   0.00584  -0.0377   0.7064   1.0000
   3.000   0.5002   0.01345   0.00627  -0.0366   0.6874   1.0000
   3.250   0.5239   0.01383   0.00675  -0.0355   0.6688   1.0000
   3.500   0.5467   0.01416   0.00721  -0.0341   0.6476   1.0000
   3.750   0.5631   0.01412   0.00714  -0.0304   0.5991   1.0000
   4.000   0.5729   0.01391   0.00662  -0.0252   0.5055   1.0000
   4.250   0.5663   0.01692   0.00727  -0.0187   0.0830   1.0000
   4.500   0.5821   0.01860   0.00885  -0.0162   0.0541   1.0000
   4.750   0.5987   0.02002   0.01038  -0.0137   0.0475   1.0000
   5.000   0.6170   0.02152   0.01189  -0.0115   0.0438   1.0000
   5.250   0.6383   0.02333   0.01368  -0.0097   0.0420   1.0000
   5.500   0.6627   0.02553   0.01593  -0.0084   0.0413   1.0000
   5.750   0.6886   0.02782   0.01846  -0.0070   0.0422   1.0000
   6.000   0.7128   0.03056   0.02169  -0.0050   0.0448   1.0000
   6.250   0.7334   0.03338   0.02501  -0.0030   0.0454   1.0000
   6.500   0.7513   0.03645   0.02853  -0.0009   0.0467   1.0000
   6.750   0.7671   0.04019   0.03263   0.0010   0.0493   1.0000
   7.000   0.7840   0.04514   0.03813   0.0036   0.0626   1.0000
   9.250   0.5845   0.09059   0.08615  -0.0060   0.1608   1.0000
   9.500   0.5919   0.09490   0.09044  -0.0050   0.1543   1.0000
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