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EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 100,000
Max Cl/Cd: 49.8 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e433-il-100000-n5.txt
Download as CSV file: xf-e433-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 433 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2359   0.09811   0.09318  -0.0866   0.9594   0.0292
  -9.500  -0.2255   0.09615   0.09120  -0.0858   0.9546   0.0276
  -9.000  -0.2252   0.08242   0.07749  -0.0975   0.9459   0.0231
  -8.750  -0.2274   0.07888   0.07398  -0.0990   0.9386   0.0227
  -8.500  -0.2265   0.07343   0.06852  -0.1044   0.9336   0.0223
  -8.250  -0.2364   0.06921   0.06426  -0.1068   0.9257   0.0220
  -8.000  -0.2463   0.06498   0.05994  -0.1091   0.9186   0.0216
  -7.750  -0.2590   0.06146   0.05631  -0.1085   0.9097   0.0213
  -7.500  -0.2621   0.05690   0.05152  -0.1096   0.9039   0.0207
  -7.250  -0.2690   0.05337   0.04776  -0.1080   0.8965   0.0203
  -7.000  -0.2701   0.04921   0.04324  -0.1070   0.8902   0.0198
  -6.750  -0.2588   0.04405   0.03747  -0.1076   0.8870   0.0192
  -6.500  -0.2636   0.04135   0.03432  -0.1035   0.8783   0.0189
  -6.250  -0.2454   0.03842   0.03091  -0.1033   0.8748   0.0188
  -6.000  -0.2201   0.03571   0.02778  -0.1040   0.8726   0.0190
  -5.750  -0.2061   0.03408   0.02588  -0.1022   0.8673   0.0193
  -5.500  -0.1891   0.03258   0.02409  -0.1008   0.8623   0.0196
  -5.250  -0.1617   0.03084   0.02206  -0.1011   0.8597   0.0202
  -5.000  -0.1307   0.02939   0.02031  -0.1019   0.8578   0.0219
  -4.750  -0.0980   0.02801   0.01873  -0.1029   0.8564   0.0244
  -4.500  -0.0931   0.02771   0.01837  -0.0991   0.8483   0.0255
  -4.250  -0.0661   0.02664   0.01716  -0.0990   0.8453   0.0276
  -4.000  -0.0361   0.02555   0.01600  -0.0995   0.8432   0.0303
  -3.750  -0.0036   0.02467   0.01505  -0.1006   0.8416   0.0368
  -3.250   0.0299   0.02379   0.01420  -0.0973   0.8305   0.0582
  -3.000   0.0602   0.02289   0.01354  -0.0981   0.8283   0.1045
  -2.500   0.0941   0.02071   0.01346  -0.0957   0.8194   0.5403
  -2.250   0.1063   0.02108   0.01417  -0.0911   0.8148   0.6992
  -2.000   0.1330   0.02136   0.01429  -0.0899   0.8123   0.7526
  -1.750   0.1600   0.02156   0.01434  -0.0886   0.8105   0.7836
  -1.500   0.1580   0.02218   0.01493  -0.0829   0.8007   0.8003
  -1.250   0.1743   0.02236   0.01502  -0.0790   0.7976   0.8266
  -1.000   0.1902   0.02237   0.01498  -0.0748   0.7953   0.8541
  -0.750   0.1829   0.02291   0.01551  -0.0681   0.7850   0.8732
  -0.500   0.2090   0.02272   0.01517  -0.0672   0.7824   0.8831
  -0.250   0.2443   0.02248   0.01477  -0.0687   0.7806   0.8874
   0.000   0.2501   0.02294   0.01518  -0.0655   0.7710   0.8935
   0.250   0.2815   0.02275   0.01486  -0.0662   0.7681   0.8972
   0.500   0.3171   0.02249   0.01448  -0.0677   0.7661   0.9005
   1.000   0.3581   0.02276   0.01462  -0.0660   0.7536   0.9096
   1.250   0.3939   0.02247   0.01424  -0.0675   0.7513   0.9126
   1.750   0.4378   0.02270   0.01439  -0.0662   0.7387   0.9219
   2.000   0.4741   0.02236   0.01401  -0.0677   0.7363   0.9251
   2.500   0.5203   0.02254   0.01417  -0.0669   0.7234   0.9350
   2.750   0.5585   0.02214   0.01375  -0.0686   0.7210   0.9384
   3.000   0.5714   0.02260   0.01423  -0.0668   0.7110   0.9465
   3.250   0.6089   0.02223   0.01386  -0.0684   0.7076   0.9502
   3.500   0.6460   0.02190   0.01355  -0.0701   0.7038   0.9542
   3.750   0.6666   0.02220   0.01391  -0.0696   0.6942   0.9627
   4.000   0.7095   0.02169   0.01341  -0.0721   0.6910   0.9673
   4.250   0.7315   0.02203   0.01383  -0.0721   0.6805   0.9828
   4.500   0.7725   0.02146   0.01329  -0.0742   0.6763   1.0000
   4.750   0.7892   0.02184   0.01372  -0.0731   0.6655   1.0000
   5.000   0.8305   0.02130   0.01323  -0.0753   0.6607   1.0000
   5.250   0.8481   0.02166   0.01365  -0.0743   0.6491   1.0000
   5.500   0.8752   0.02167   0.01371  -0.0745   0.6394   1.0000
   5.750   0.9111   0.02133   0.01342  -0.0758   0.6311   1.0000
   6.000   0.9324   0.02158   0.01374  -0.0752   0.6185   1.0000
   6.250   0.9575   0.02169   0.01390  -0.0751   0.6060   1.0000
   6.500   0.9847   0.02171   0.01397  -0.0753   0.5930   1.0000
   6.750   1.0119   0.02174   0.01407  -0.0754   0.5789   1.0000
   7.000   1.0379   0.02183   0.01419  -0.0753   0.5635   1.0000
   7.250   1.0628   0.02197   0.01437  -0.0751   0.5466   1.0000
   7.500   1.0875   0.02213   0.01455  -0.0748   0.5282   1.0000
   7.750   1.1120   0.02233   0.01473  -0.0744   0.5088   1.0000
   8.000   1.1306   0.02279   0.01520  -0.0734   0.4877   1.0000
   8.250   1.1504   0.02324   0.01563  -0.0724   0.4660   1.0000
   8.500   1.1672   0.02384   0.01620  -0.0712   0.4440   1.0000
   8.750   1.1822   0.02454   0.01686  -0.0697   0.4216   1.0000
   9.000   1.1960   0.02533   0.01762  -0.0682   0.3997   1.0000
   9.250   1.2079   0.02624   0.01851  -0.0665   0.3776   1.0000
   9.500   1.2189   0.02721   0.01944  -0.0647   0.3564   1.0000
   9.750   1.2285   0.02830   0.02052  -0.0629   0.3348   1.0000
  10.000   1.2373   0.02947   0.02165  -0.0611   0.3141   1.0000
  10.250   1.2454   0.03072   0.02288  -0.0593   0.2941   1.0000
  10.500   1.2527   0.03206   0.02423  -0.0575   0.2739   1.0000
  10.750   1.2592   0.03350   0.02565  -0.0558   0.2551   1.0000
  11.250   1.2708   0.03663   0.02877  -0.0526   0.2192   1.0000
  11.500   1.2761   0.03831   0.03047  -0.0511   0.2022   1.0000
  11.750   1.2807   0.04011   0.03228  -0.0496   0.1860   1.0000
  12.000   1.2846   0.04202   0.03423  -0.0483   0.1706   1.0000
  12.250   1.2881   0.04403   0.03626  -0.0470   0.1563   1.0000
  12.500   1.2912   0.04616   0.03841  -0.0459   0.1427   1.0000
  12.750   1.2938   0.04840   0.04069  -0.0448   0.1302   1.0000
  13.000   1.2955   0.05080   0.04313  -0.0439   0.1187   1.0000
  13.250   1.2960   0.05339   0.04574  -0.0430   0.1086   1.0000
  13.500   1.2969   0.05605   0.04846  -0.0423   0.0987   1.0000
  13.750   1.2983   0.05875   0.05126  -0.0418   0.0897   1.0000
  14.000   1.2971   0.06179   0.05436  -0.0414   0.0825   1.0000
  14.250   1.2967   0.06484   0.05752  -0.0411   0.0754   1.0000
  14.500   1.2954   0.06810   0.06087  -0.0409   0.0697   1.0000
  14.750   1.2937   0.07150   0.06438  -0.0410   0.0642   1.0000
  15.000   1.2906   0.07515   0.06810  -0.0412   0.0598   1.0000
  15.250   1.2893   0.07869   0.07180  -0.0415   0.0553   1.0000
  15.500   1.2843   0.08278   0.07595  -0.0421   0.0521   1.0000
  15.750   1.2825   0.08655   0.07988  -0.0427   0.0484   1.0000
  16.000   1.2795   0.09057   0.08404  -0.0436   0.0453   1.0000
  16.250   1.2743   0.09495   0.08849  -0.0447   0.0429   1.0000
  16.500   1.2717   0.09906   0.09276  -0.0458   0.0403   1.0000
  16.750   1.2686   0.10335   0.09722  -0.0471   0.0378   1.0000
  17.000   1.2640   0.10792   0.10192  -0.0488   0.0358   1.0000
  17.250   1.2597   0.11235   0.10637  -0.0505   0.0341   1.0000
  17.500   1.2564   0.11695   0.11124  -0.0523   0.0322   1.0000
  17.750   1.2521   0.12171   0.11618  -0.0544   0.0305   1.0000
  18.000   1.2475   0.12658   0.12116  -0.0568   0.0290   1.0000
  18.250   1.2436   0.13126   0.12589  -0.0592   0.0278   1.0000
  18.500   1.2391   0.13624   0.13104  -0.0618   0.0266   1.0000
  18.750   1.2322   0.14194   0.13698  -0.0650   0.0254   1.0000
  19.000   1.2252   0.14772   0.14293  -0.0684   0.0244   1.0000
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