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EPPLER 335 AIRFOIL (e335-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 335 AIRFOIL (e335-il)
Reynolds number: 1,000,000
Max Cl/Cd: 90.13 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e335-il-1000000.txt
Download as CSV file: xf-e335-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 335 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5189   0.08138   0.07990  -0.0138   1.0000   0.0078
  -9.250  -0.5376   0.07518   0.07367  -0.0181   1.0000   0.0077
  -9.000  -0.5562   0.07058   0.06902  -0.0187   1.0000   0.0078
  -8.750  -0.5741   0.06692   0.06531  -0.0170   1.0000   0.0078
  -8.500  -0.5917   0.06371   0.06203  -0.0136   1.0000   0.0077
  -8.250  -0.5829   0.05859   0.05659  -0.0161   0.8825   0.0079
  -8.000  -0.5914   0.05586   0.05347  -0.0122   0.8038   0.0080
  -7.750  -0.5952   0.05263   0.04998  -0.0090   0.7687   0.0081
  -7.500  -0.5951   0.04937   0.04649  -0.0059   0.7423   0.0083
  -7.250  -0.5925   0.04610   0.04298  -0.0029   0.7211   0.0084
  -5.250  -0.5046   0.01782   0.01168   0.0231   0.6066   0.0073
  -4.750  -0.4499   0.01428   0.00771   0.0241   0.5813   0.0059
  -4.500  -0.4244   0.01334   0.00663   0.0248   0.5688   0.0059
  -4.250  -0.4000   0.01268   0.00585   0.0257   0.5569   0.0059
  -3.750  -0.3521   0.01172   0.00471   0.0275   0.5349   0.0063
  -3.500  -0.3278   0.01137   0.00429   0.0284   0.5248   0.0068
  -3.250  -0.3047   0.01092   0.00376   0.0294   0.5144   0.0077
  -3.000  -0.2799   0.01067   0.00348   0.0301   0.5044   0.0083
  -2.750  -0.2548   0.01048   0.00323   0.0308   0.4948   0.0092
  -2.500  -0.2305   0.01019   0.00289   0.0316   0.4857   0.0103
  -2.250  -0.2053   0.01002   0.00268   0.0323   0.4772   0.0120
  -2.000  -0.1812   0.00977   0.00243   0.0331   0.4683   0.0215
  -1.750  -0.1588   0.00937   0.00224   0.0342   0.4606   0.0735
  -1.500  -0.1370   0.00900   0.00210   0.0354   0.4527   0.1480
  -1.250  -0.1251   0.00803   0.00188   0.0383   0.4466   0.3614
  -1.000  -0.1283   0.00673   0.00158   0.0444   0.4413   0.6334
  -0.750  -0.1293   0.00600   0.00174   0.0511   0.4356   0.8655
  -0.500  -0.1054   0.00633   0.00206   0.0526   0.4290   0.8952
  -0.250  -0.0751   0.00688   0.00258   0.0528   0.4218   0.9098
   0.000  -0.0407   0.00736   0.00301   0.0520   0.4153   0.9171
   0.250   0.0019   0.00790   0.00348   0.0494   0.4078   0.9210
   0.500   0.0376   0.00833   0.00384   0.0481   0.4011   0.9261
   0.750   0.0775   0.00873   0.00418   0.0460   0.3952   0.9302
   1.000   0.1157   0.00891   0.00428   0.0438   0.3888   0.9308
   1.250   0.1485   0.00894   0.00427   0.0428   0.3835   0.9313
   1.500   0.1812   0.00898   0.00427   0.0417   0.3781   0.9318
   1.750   0.2131   0.00905   0.00427   0.0407   0.3727   0.9323
   2.000   0.2453   0.00908   0.00428   0.0397   0.3686   0.9329
   2.250   0.2766   0.00912   0.00428   0.0390   0.3636   0.9335
   2.500   0.3067   0.00918   0.00429   0.0384   0.3586   0.9342
   2.750   0.3361   0.00922   0.00432   0.0380   0.3545   0.9351
   3.000   0.3643   0.00923   0.00432   0.0378   0.3505   0.9361
   3.250   0.3904   0.00927   0.00433   0.0381   0.3461   0.9374
   3.500   0.3740   0.00912   0.00418   0.0475   0.3436   0.9445
   3.750   0.4028   0.00913   0.00418   0.0472   0.3396   0.9450
   4.000   0.4330   0.00914   0.00419   0.0465   0.3355   0.9455
   4.250   0.4628   0.00918   0.00421   0.0460   0.3312   0.9459
   4.500   0.4912   0.00926   0.00426   0.0457   0.3261   0.9464
   4.750   0.5200   0.00926   0.00429   0.0453   0.3228   0.9469
   5.000   0.5484   0.00929   0.00432   0.0450   0.3185   0.9474
   5.250   0.5772   0.00937   0.00437   0.0446   0.3136   0.9479
   5.500   0.6055   0.00944   0.00445   0.0443   0.3095   0.9486
   5.750   0.6330   0.00946   0.00449   0.0442   0.3052   0.9492
   6.000   0.6587   0.00952   0.00454   0.0445   0.3004   0.9500
   6.250   0.6824   0.00960   0.00462   0.0451   0.2954   0.9509
   6.500   0.7052   0.00961   0.00466   0.0460   0.2914   0.9521
   6.750   0.7253   0.00965   0.00471   0.0474   0.2862   0.9539
   7.000   0.7339   0.00966   0.00471   0.0513   0.2816   0.9568
   7.250   0.7487   0.00963   0.00473   0.0539   0.2777   0.9585
   7.500   0.7751   0.00967   0.00477   0.0539   0.2717   0.9591
   7.750   0.8013   0.00977   0.00487   0.0539   0.2653   0.9597
   8.000   0.8284   0.00985   0.00498   0.0538   0.2591   0.9602
   8.250   0.8550   0.01001   0.00513   0.0536   0.2519   0.9609
   8.500   0.8824   0.01012   0.00527   0.0534   0.2447   0.9615
   8.750   0.9078   0.01030   0.00545   0.0535   0.2365   0.9622
   9.000   0.9332   0.01046   0.00561   0.0536   0.2278   0.9629
   9.250   0.9576   0.01064   0.00580   0.0539   0.2192   0.9638
   9.500   0.9804   0.01089   0.00603   0.0544   0.2086   0.9649
   9.750   1.0022   0.01112   0.00625   0.0551   0.1975   0.9661
  10.000   1.0217   0.01139   0.00650   0.0563   0.1851   0.9676
  10.250   1.0373   0.01168   0.00676   0.0582   0.1718   0.9697
  10.500   1.0488   0.01199   0.00704   0.0609   0.1583   0.9719
  10.750   1.0711   0.01250   0.00748   0.0611   0.1417   0.9730
  11.000   1.0942   0.01302   0.00796   0.0611   0.1269   0.9740
  11.250   1.1163   0.01357   0.00849   0.0612   0.1136   0.9750
  11.500   1.1367   0.01421   0.00908   0.0615   0.0993   0.9762
  11.750   1.1557   0.01485   0.00969   0.0620   0.0876   0.9777
  12.000   1.1719   0.01556   0.01036   0.0629   0.0759   0.9797
  12.250   1.1761   0.01615   0.01094   0.0663   0.0686   0.9838
  12.500   1.1953   0.01711   0.01188   0.0659   0.0576   0.9848
  12.750   1.2140   0.01813   0.01289   0.0653   0.0494   0.9860
  13.000   1.2302   0.01935   0.01411   0.0646   0.0417   0.9874
  13.250   1.2434   0.02086   0.01563   0.0636   0.0350   0.9894
  13.500   1.2534   0.02276   0.01756   0.0623   0.0292   0.9918
  13.750   1.2628   0.02486   0.01971   0.0607   0.0258   0.9943
  14.000   1.2742   0.02733   0.02224   0.0581   0.0229   0.9958
  14.250   1.2835   0.03004   0.02503   0.0555   0.0204   0.9975
  14.500   1.2884   0.03330   0.02835   0.0527   0.0183   0.9990
  14.750   1.2928   0.03651   0.03165   0.0502   0.0167   1.0000
  15.000   1.2681   0.03914   0.03435   0.0537   0.0161   1.0000
  15.250   1.2514   0.04206   0.03733   0.0554   0.0157   1.0000
  15.500   1.2397   0.04536   0.04070   0.0557   0.0154   1.0000
  15.750   1.2276   0.04904   0.04445   0.0553   0.0148   1.0000
  16.000   1.2158   0.05282   0.04831   0.0547   0.0138   1.0000
  16.250   1.2068   0.05647   0.05203   0.0540   0.0129   1.0000
  16.500   1.1982   0.06025   0.05589   0.0531   0.0128   1.0000
  16.750   1.1873   0.06442   0.06012   0.0519   0.0120   1.0000
  17.000   1.1754   0.06883   0.06460   0.0506   0.0114   1.0000
  17.250   1.1679   0.07276   0.06860   0.0494   0.0108   1.0000
  17.500   1.1591   0.07696   0.07289   0.0480   0.0108   1.0000
  17.750   1.1514   0.08106   0.07705   0.0466   0.0100   1.0000
  18.000   1.1428   0.08530   0.08136   0.0451   0.0095   1.0000
  18.250   1.1340   0.08968   0.08581   0.0435   0.0092   1.0000
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