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EPPLER 428 AIRFOIL (e428-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 428 AIRFOIL (e428-il)
Reynolds number: 100,000
Max Cl/Cd: 32.09 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e428-il-100000.txt
Download as CSV file: xf-e428-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 428 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8444   0.08438   0.07897  -0.0164   1.0000   0.0566
 -12.500  -0.8836   0.07317   0.06765  -0.0249   1.0000   0.0557
 -12.250  -0.9164   0.06441   0.05870  -0.0318   1.0000   0.0549
 -12.000  -0.9463   0.05751   0.05156  -0.0369   1.0000   0.0545
 -11.750  -0.9694   0.05261   0.04642  -0.0390   1.0000   0.0544
 -11.500  -0.9868   0.04893   0.04248  -0.0385   1.0000   0.0546
 -11.250  -0.9962   0.04541   0.03862  -0.0376   1.0000   0.0554
 -11.000  -0.9994   0.04207   0.03483  -0.0365   1.0000   0.0565
 -10.750  -0.9879   0.03947   0.03225  -0.0357   1.0000   0.0587
 -10.500  -0.9762   0.03740   0.03010  -0.0347   1.0000   0.0619
 -10.250  -0.9674   0.03472   0.02707  -0.0336   1.0000   0.0662
 -10.000  -0.9528   0.03318   0.02559  -0.0326   1.0000   0.0732
  -9.750  -0.9398   0.03151   0.02383  -0.0315   1.0000   0.0844
  -9.500  -0.9242   0.03058   0.02301  -0.0304   1.0000   0.0996
  -9.250  -0.9057   0.03000   0.02236  -0.0295   1.0000   0.1124
  -9.000  -0.8868   0.02930   0.02140  -0.0286   1.0000   0.1231
  -8.750  -0.8643   0.02943   0.02157  -0.0279   1.0000   0.1333
  -8.500  -0.8406   0.02975   0.02204  -0.0272   1.0000   0.1432
  -8.250  -0.8186   0.02947   0.02168  -0.0265   1.0000   0.1530
  -8.000  -0.7974   0.02904   0.02098  -0.0257   1.0000   0.1631
  -7.750  -0.7721   0.02889   0.02107  -0.0250   1.0000   0.1709
  -7.500  -0.7513   0.02760   0.01947  -0.0243   1.0000   0.1798
  -7.250  -0.7268   0.02699   0.01893  -0.0236   1.0000   0.1872
  -7.000  -0.7047   0.02572   0.01741  -0.0228   1.0000   0.1961
  -6.750  -0.6806   0.02504   0.01671  -0.0221   1.0000   0.2049
  -6.500  -0.6573   0.02417   0.01575  -0.0214   1.0000   0.2144
  -6.250  -0.6340   0.02348   0.01482  -0.0206   1.0000   0.2254
  -6.000  -0.6097   0.02277   0.01423  -0.0199   1.0000   0.2339
  -5.750  -0.5861   0.02199   0.01326  -0.0191   1.0000   0.2444
  -5.500  -0.5620   0.02144   0.01274  -0.0184   1.0000   0.2543
  -5.250  -0.5382   0.02074   0.01200  -0.0176   1.0000   0.2643
  -5.000  -0.5147   0.02026   0.01134  -0.0168   1.0000   0.2764
  -4.750  -0.4910   0.01970   0.01094  -0.0160   1.0000   0.2873
  -4.500  -0.4675   0.01911   0.01036  -0.0151   1.0000   0.2987
  -4.250  -0.4439   0.01859   0.00971  -0.0143   1.0000   0.3104
  -4.000  -0.4204   0.01800   0.00926  -0.0134   1.0000   0.3205
  -3.750  -0.3970   0.01744   0.00871  -0.0126   1.0000   0.3313
  -3.500  -0.3739   0.01699   0.00821  -0.0118   1.0000   0.3427
  -3.250  -0.3515   0.01650   0.00787  -0.0108   1.0000   0.3537
  -3.000  -0.3297   0.01609   0.00752  -0.0098   1.0000   0.3660
  -2.750  -0.3086   0.01576   0.00721  -0.0087   1.0000   0.3791
  -2.500  -0.2886   0.01546   0.00701  -0.0076   1.0000   0.3925
  -2.250  -0.2699   0.01521   0.00689  -0.0063   1.0000   0.4066
  -2.000  -0.2521   0.01504   0.00685  -0.0051   1.0000   0.4227
  -1.750  -0.2348   0.01495   0.00688  -0.0039   1.0000   0.4412
  -1.500  -0.2038   0.01487   0.00700  -0.0054   0.9943   0.4671
  -1.250  -0.1431   0.01457   0.00701  -0.0118   0.9739   0.5145
  -1.000  -0.0824   0.01408   0.00697  -0.0174   0.9535   0.5796
  -0.750  -0.0338   0.01363   0.00692  -0.0203   0.9325   0.6542
  -0.500   0.0077   0.01330   0.00689  -0.0214   0.9116   0.7231
  -0.250   0.0448   0.01304   0.00683  -0.0212   0.8898   0.7815
   0.000   0.0739   0.01288   0.00679  -0.0195   0.8631   0.8321
   0.250   0.1062   0.01276   0.00670  -0.0183   0.8375   0.8796
   0.500   0.1454   0.01271   0.00661  -0.0187   0.8069   0.9230
   0.750   0.1975   0.01269   0.00647  -0.0219   0.7726   0.9574
   1.000   0.2557   0.01266   0.00626  -0.0268   0.7328   0.9857
   1.250   0.2903   0.01263   0.00605  -0.0281   0.6932   1.0000
   1.500   0.3054   0.01269   0.00592  -0.0258   0.6576   1.0000
   1.750   0.3227   0.01282   0.00583  -0.0236   0.6175   1.0000
   2.000   0.3415   0.01303   0.00577  -0.0216   0.5704   1.0000
   2.250   0.3611   0.01334   0.00576  -0.0197   0.5166   1.0000
   2.500   0.3817   0.01379   0.00583  -0.0181   0.4636   1.0000
   2.750   0.4037   0.01432   0.00602  -0.0168   0.4207   1.0000
   3.000   0.4270   0.01486   0.00627  -0.0158   0.3901   1.0000
   3.250   0.4513   0.01538   0.00662  -0.0151   0.3661   1.0000
   3.500   0.4760   0.01592   0.00697  -0.0144   0.3473   1.0000
   3.750   0.5012   0.01647   0.00739  -0.0138   0.3316   1.0000
   4.000   0.5269   0.01706   0.00790  -0.0132   0.3187   1.0000
   4.250   0.5527   0.01771   0.00842  -0.0127   0.3077   1.0000
   4.500   0.5785   0.01832   0.00896  -0.0123   0.2968   1.0000
   4.750   0.6045   0.01900   0.00968  -0.0118   0.2873   1.0000
   5.000   0.6307   0.01975   0.01030  -0.0114   0.2790   1.0000
   5.250   0.6564   0.02048   0.01114  -0.0110   0.2702   1.0000
   5.500   0.6825   0.02127   0.01183  -0.0106   0.2624   1.0000
   5.750   0.7075   0.02207   0.01280  -0.0101   0.2541   1.0000
   6.000   0.7332   0.02285   0.01346  -0.0097   0.2455   1.0000
   6.250   0.7573   0.02363   0.01445  -0.0090   0.2364   1.0000
   6.500   0.7829   0.02448   0.01515  -0.0087   0.2283   1.0000
   6.750   0.8062   0.02532   0.01628  -0.0080   0.2198   1.0000
   7.000   0.8314   0.02618   0.01706  -0.0075   0.2124   1.0000
   7.250   0.8538   0.02731   0.01848  -0.0068   0.2046   1.0000
   7.500   0.8782   0.02819   0.01938  -0.0063   0.1974   1.0000
   7.750   0.8997   0.02957   0.02100  -0.0055   0.1902   1.0000
   8.000   0.9229   0.03051   0.02202  -0.0048   0.1827   1.0000
   8.250   0.9443   0.03197   0.02360  -0.0042   0.1763   1.0000
   8.500   0.9637   0.03351   0.02545  -0.0032   0.1696   1.0000
   8.750   0.9877   0.03465   0.02654  -0.0028   0.1647   1.0000
   9.000   1.0011   0.03718   0.02953  -0.0016   0.1595   1.0000
   9.250   1.0181   0.03887   0.03147  -0.0007   0.1539   1.0000
   9.500   1.0460   0.03935   0.03168  -0.0005   0.1487   1.0000
   9.750   1.0485   0.04251   0.03552   0.0012   0.1438   1.0000
  10.000   1.0739   0.04227   0.03519   0.0018   0.1371   1.0000
  10.250   1.0869   0.04373   0.03682   0.0028   0.1313   1.0000
  10.500   1.1042   0.04423   0.03744   0.0039   0.1248   1.0000
  10.750   1.1266   0.04456   0.03768   0.0045   0.1195   1.0000
  11.000   1.1195   0.04808   0.04174   0.0063   0.1154   1.0000
  11.250   1.1643   0.04563   0.03874   0.0063   0.1081   1.0000
  11.500   1.1426   0.05003   0.04385   0.0087   0.1047   1.0000
  11.750   0.9181   0.08186   0.07659  -0.0040   0.1226   1.0000
  12.000   0.8924   0.09152   0.08625  -0.0096   0.1214   1.0000
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