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EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1233 AIRFOIL (e1233-il)
Reynolds number: 50,000
Max Cl/Cd: 21.16 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1233-il-50000-n5.txt
Download as CSV file: xf-e1233-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1233 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3340   0.10281   0.09620  -0.0545   1.0000   0.0540
 -10.500  -0.3520   0.09674   0.09023  -0.0562   1.0000   0.0537
 -10.250  -0.3788   0.08989   0.08345  -0.0585   1.0000   0.0532
 -10.000  -0.4141   0.08371   0.07732  -0.0600   1.0000   0.0526
  -9.750  -0.4543   0.07890   0.07255  -0.0599   1.0000   0.0519
  -9.500  -0.4976   0.07534   0.06901  -0.0580   0.9998   0.0513
  -9.250  -0.5193   0.06898   0.06234  -0.0638   0.9854   0.0510
  -9.000  -0.5280   0.06382   0.05681  -0.0671   0.9711   0.0513
  -8.750  -0.5286   0.05947   0.05209  -0.0688   0.9556   0.0521
  -8.500  -0.5256   0.05516   0.04728  -0.0699   0.9406   0.0536
  -8.250  -0.5146   0.05151   0.04315  -0.0707   0.9271   0.0553
  -8.000  -0.4897   0.04955   0.04110  -0.0721   0.9160   0.0579
  -7.750  -0.4670   0.04652   0.03761  -0.0733   0.9052   0.0606
  -7.500  -0.4454   0.04419   0.03498  -0.0734   0.8926   0.0631
  -7.250  -0.4180   0.04246   0.03310  -0.0743   0.8817   0.0673
  -7.000  -0.3857   0.04051   0.03094  -0.0756   0.8724   0.0726
  -6.750  -0.3588   0.03889   0.02903  -0.0756   0.8605   0.0787
  -6.500  -0.3201   0.03729   0.02740  -0.0776   0.8533   0.0872
  -6.250  -0.2943   0.03615   0.02624  -0.0774   0.8407   0.0962
  -6.000  -0.2522   0.03465   0.02462  -0.0796   0.8340   0.1113
  -5.750  -0.2269   0.03372   0.02366  -0.0792   0.8208   0.1254
  -5.500  -0.1936   0.03260   0.02254  -0.0802   0.8108   0.1441
  -5.250  -0.1614   0.03149   0.02149  -0.0810   0.8002   0.1651
  -5.000  -0.1360   0.03058   0.02062  -0.0808   0.7881   0.1881
  -4.750  -0.1034   0.02935   0.01951  -0.0819   0.7790   0.2200
  -4.500  -0.0862   0.02850   0.01884  -0.0805   0.7654   0.2545
  -4.250  -0.0639   0.02733   0.01803  -0.0801   0.7548   0.3147
  -4.000  -0.0460   0.02649   0.01788  -0.0781   0.7434   0.4161
  -3.750  -0.0252   0.02698   0.01886  -0.0742   0.7318   0.5282
  -3.500   0.0062   0.02751   0.01924  -0.0728   0.7219   0.5993
  -3.250   0.0232   0.02806   0.01960  -0.0699   0.7093   0.6385
  -3.000   0.0544   0.02863   0.01990  -0.0687   0.7002   0.6715
  -2.750   0.0696   0.02906   0.02015  -0.0657   0.6880   0.6980
  -2.500   0.0959   0.02963   0.02051  -0.0636   0.6781   0.7205
  -2.250   0.1191   0.03014   0.02085  -0.0611   0.6678   0.7421
  -2.000   0.1435   0.03057   0.02110  -0.0589   0.6582   0.7634
  -1.750   0.1688   0.03087   0.02122  -0.0571   0.6484   0.7829
  -1.500   0.1931   0.03104   0.02121  -0.0556   0.6391   0.7994
  -1.250   0.2142   0.03106   0.02107  -0.0541   0.6299   0.8136
  -1.000   0.2418   0.03105   0.02086  -0.0538   0.6215   0.8247
  -0.750   0.2626   0.03106   0.02075  -0.0526   0.6122   0.8343
  -0.500   0.2913   0.03091   0.02037  -0.0528   0.6049   0.8439
  -0.250   0.3063   0.03102   0.02043  -0.0508   0.5954   0.8520
   0.000   0.3375   0.03087   0.02006  -0.0516   0.5886   0.8597
   0.250   0.3486   0.03101   0.02016  -0.0491   0.5800   0.8677
   0.500   0.3740   0.03098   0.01999  -0.0490   0.5726   0.8745
   0.750   0.3953   0.03095   0.01982  -0.0482   0.5662   0.8818
   1.000   0.4107   0.03119   0.02003  -0.0467   0.5578   0.8885
   1.250   0.4362   0.03112   0.01981  -0.0466   0.5519   0.8954
   1.500   0.4548   0.03137   0.02001  -0.0456   0.5447   0.9016
   1.750   0.4715   0.03158   0.02019  -0.0443   0.5376   0.9087
   2.000   0.5041   0.03154   0.01998  -0.0454   0.5324   0.9144
   2.250   0.5179   0.03202   0.02049  -0.0440   0.5253   0.9214
   2.500   0.5340   0.03233   0.02076  -0.0427   0.5188   0.9288
   2.750   0.5753   0.03235   0.02063  -0.0454   0.5138   0.9331
   3.000   0.5836   0.03300   0.02133  -0.0433   0.5071   0.9418
   3.250   0.6082   0.03353   0.02185  -0.0438   0.5006   0.9480
   3.500   0.6460   0.03365   0.02186  -0.0460   0.4959   0.9534
   3.750   0.6667   0.03438   0.02262  -0.0462   0.4899   0.9605
   4.000   0.6823   0.03528   0.02359  -0.0458   0.4833   0.9696
   4.250   0.7225   0.03553   0.02375  -0.0486   0.4785   0.9750
   4.500   0.7589   0.03587   0.02402  -0.0508   0.4742   0.9817
   4.750   0.7505   0.03770   0.02606  -0.0479   0.4669   1.0000
   5.000   0.7312   0.03838   0.02675  -0.0416   0.4624   1.0000
   5.250   0.7556   0.03846   0.02675  -0.0414   0.4590   1.0000
   5.500   0.7178   0.04097   0.02939  -0.0348   0.4521   1.0000
   5.750   0.7038   0.04345   0.03192  -0.0320   0.4452   1.0000
   6.000   0.7338   0.04374   0.03216  -0.0328   0.4419   1.0000
   6.250   0.7750   0.04351   0.03183  -0.0345   0.4396   1.0000
   6.750   0.7196   0.05194   0.04046  -0.0297   0.4230   1.0000
   7.000   0.7590   0.05150   0.03996  -0.0307   0.4213   1.0000
   7.500   0.6934   0.06396   0.05261  -0.0300   0.4021   1.0000
   8.500   0.6542   0.08210   0.07091  -0.0328   0.3736   1.0000
   8.750   0.6753   0.08328   0.07208  -0.0331   0.3707   1.0000
   9.000   0.7016   0.08391   0.07269  -0.0333   0.3687   1.0000
   9.500   0.6752   0.09398   0.08289  -0.0353   0.3553   1.0000
   9.750   0.6978   0.09506   0.08396  -0.0356   0.3527   1.0000
  10.250   0.6821   0.10410   0.09312  -0.0379   0.3416   1.0000
  10.500   0.6971   0.10602   0.09505  -0.0384   0.3380   1.0000
  10.750   0.7196   0.10711   0.09617  -0.0386   0.3355   1.0000
  11.000   0.7061   0.11233   0.10145  -0.0401   0.3297   1.0000
  11.250   0.7062   0.11598   0.10516  -0.0412   0.3249   1.0000
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