Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 1233 AIRFOIL (e1233-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1233 AIRFOIL (e1233-il)
Reynolds number: 200,000
Max Cl/Cd: 58.07 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1233-il-200000-n5.txt
Download as CSV file: xf-e1233-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5508   0.07964   0.07528  -0.0696   1.0000   0.0159
 -13.500  -0.6061   0.06706   0.06232  -0.0773   1.0000   0.0156
 -13.250  -0.6322   0.06109   0.05616  -0.0797   1.0000   0.0156
 -13.000  -0.6489   0.05710   0.05206  -0.0804   1.0000   0.0157
 -12.750  -0.6685   0.05321   0.04800  -0.0803   1.0000   0.0157
 -12.500  -0.6840   0.05025   0.04491  -0.0794   1.0000   0.0157
 -12.250  -0.6871   0.04747   0.04202  -0.0801   0.9984   0.0159
 -12.000  -0.6764   0.04431   0.03864  -0.0835   0.9942   0.0159
 -11.750  -0.6636   0.04176   0.03595  -0.0861   0.9892   0.0163
 -11.500  -0.6481   0.03939   0.03339  -0.0887   0.9842   0.0166
 -11.250  -0.6345   0.03724   0.03108  -0.0899   0.9774   0.0168
 -11.000  -0.6160   0.03523   0.02888  -0.0917   0.9717   0.0172
 -10.500  -0.5936   0.03197   0.02531  -0.0907   0.9498   0.0178
 -10.250  -0.5827   0.03060   0.02380  -0.0896   0.9374   0.0183
 -10.000  -0.5697   0.02950   0.02268  -0.0887   0.9246   0.0189
  -9.750  -0.5507   0.02829   0.02141  -0.0884   0.9137   0.0193
  -9.500  -0.5249   0.02710   0.02011  -0.0893   0.9048   0.0202
  -9.250  -0.5015   0.02595   0.01884  -0.0894   0.8927   0.0208
  -9.000  -0.4723   0.02472   0.01750  -0.0906   0.8822   0.0218
  -8.750  -0.4368   0.02354   0.01625  -0.0930   0.8716   0.0226
  -8.500  -0.4001   0.02244   0.01504  -0.0956   0.8588   0.0239
  -8.250  -0.3557   0.02134   0.01381  -0.0997   0.8457   0.0253
  -8.000  -0.3069   0.02036   0.01272  -0.1047   0.8307   0.0275
  -7.750  -0.2649   0.01956   0.01181  -0.1082   0.8122   0.0303
  -7.500  -0.2309   0.01892   0.01102  -0.1100   0.7922   0.0334
  -7.250  -0.2031   0.01839   0.01038  -0.1105   0.7732   0.0370
  -7.000  -0.1789   0.01793   0.00983  -0.1102   0.7547   0.0417
  -6.750  -0.1564   0.01754   0.00936  -0.1096   0.7375   0.0475
  -6.250  -0.1140   0.01690   0.00858  -0.1076   0.7052   0.0627
  -6.000  -0.0930   0.01662   0.00825  -0.1065   0.6908   0.0715
  -5.750  -0.0716   0.01637   0.00793  -0.1055   0.6773   0.0809
  -5.500  -0.0501   0.01614   0.00764  -0.1045   0.6640   0.0912
  -5.250  -0.0289   0.01590   0.00737  -0.1034   0.6511   0.1027
  -5.000  -0.0073   0.01565   0.00710  -0.1025   0.6393   0.1165
  -4.750   0.0142   0.01539   0.00684  -0.1015   0.6280   0.1328
  -4.500   0.0361   0.01512   0.00659  -0.1006   0.6171   0.1519
  -4.000   0.0800   0.01454   0.00609  -0.0989   0.5959   0.2074
  -3.750   0.1017   0.01419   0.00584  -0.0982   0.5863   0.2529
  -3.500   0.1234   0.01373   0.00560  -0.0975   0.5767   0.3185
  -3.250   0.1446   0.01324   0.00540  -0.0967   0.5678   0.4072
  -3.000   0.1664   0.01289   0.00543  -0.0957   0.5586   0.5054
  -2.500   0.2148   0.01299   0.00565  -0.0938   0.5412   0.5978
  -2.250   0.2401   0.01313   0.00570  -0.0931   0.5332   0.6219
  -2.000   0.2656   0.01327   0.00578  -0.0924   0.5253   0.6400
  -1.750   0.2907   0.01343   0.00587  -0.0916   0.5173   0.6547
  -1.500   0.3159   0.01360   0.00596  -0.0909   0.5100   0.6672
  -1.250   0.3417   0.01375   0.00602  -0.0904   0.5024   0.6806
  -1.000   0.3661   0.01400   0.00620  -0.0895   0.4958   0.6944
  -0.750   0.3899   0.01426   0.00644  -0.0882   0.4894   0.7072
  -0.500   0.4151   0.01445   0.00654  -0.0876   0.4825   0.7186
  -0.250   0.4386   0.01464   0.00666  -0.0865   0.4764   0.7244
   0.000   0.4640   0.01474   0.00671  -0.0860   0.4700   0.7302
   0.250   0.4907   0.01483   0.00669  -0.0859   0.4638   0.7358
   0.500   0.5152   0.01495   0.00674  -0.0853   0.4585   0.7390
   0.750   0.5403   0.01505   0.00681  -0.0847   0.4533   0.7421
   1.000   0.5654   0.01515   0.00686  -0.0843   0.4475   0.7457
   1.250   0.5906   0.01527   0.00690  -0.0839   0.4421   0.7498
   1.500   0.6167   0.01539   0.00693  -0.0837   0.4371   0.7539
   1.750   0.6420   0.01548   0.00701  -0.0833   0.4319   0.7570
   2.000   0.6661   0.01561   0.00710  -0.0827   0.4272   0.7599
   2.250   0.6903   0.01576   0.00720  -0.0820   0.4230   0.7632
   2.500   0.7153   0.01590   0.00730  -0.0817   0.4186   0.7665
   2.750   0.7405   0.01602   0.00741  -0.0814   0.4138   0.7703
   3.000   0.7658   0.01617   0.00750  -0.0811   0.4091   0.7742
   3.250   0.7884   0.01633   0.00762  -0.0802   0.4051   0.7769
   3.500   0.8119   0.01649   0.00777  -0.0795   0.4013   0.7797
   3.750   0.8355   0.01662   0.00793  -0.0789   0.3973   0.7828
   4.000   0.8588   0.01678   0.00809  -0.0782   0.3933   0.7865
   4.250   0.8822   0.01697   0.00823  -0.0776   0.3894   0.7904
   4.500   0.9056   0.01719   0.00838  -0.0770   0.3859   0.7936
   4.750   0.9274   0.01733   0.00858  -0.0761   0.3820   0.7963
   5.000   0.9493   0.01751   0.00881  -0.0752   0.3783   0.7995
   5.250   0.9716   0.01772   0.00902  -0.0744   0.3748   0.8031
   5.500   0.9943   0.01796   0.00924  -0.0737   0.3716   0.8071
   6.000   1.0386   0.01845   0.00974  -0.0722   0.3650   0.8137
   6.250   1.0592   0.01867   0.01003  -0.0711   0.3613   0.8171
   6.500   1.0799   0.01892   0.01032  -0.0701   0.3580   0.8211
   6.750   1.1014   0.01920   0.01060  -0.0693   0.3550   0.8254
   7.000   1.1236   0.01951   0.01087  -0.0687   0.3523   0.8293
   7.250   1.1437   0.01979   0.01121  -0.0677   0.3495   0.8327
   7.500   1.1625   0.02007   0.01158  -0.0664   0.3461   0.8368
   7.750   1.1818   0.02037   0.01194  -0.0653   0.3429   0.8416
   8.000   1.2015   0.02070   0.01230  -0.0643   0.3398   0.8466
   8.250   1.2199   0.02101   0.01264  -0.0630   0.3371   0.8510
   8.500   1.2404   0.02136   0.01298  -0.0622   0.3347   0.8558
   8.750   1.2590   0.02174   0.01345  -0.0611   0.3321   0.8612
   9.000   1.2755   0.02211   0.01394  -0.0597   0.3290   0.8670
   9.250   1.2916   0.02250   0.01441  -0.0582   0.3259   0.8738
   9.500   1.3082   0.02290   0.01487  -0.0569   0.3229   0.8813
   9.750   1.3249   0.02329   0.01531  -0.0556   0.3205   0.8895
  10.000   1.3436   0.02370   0.01573  -0.0546   0.3182   0.8990
  10.500   1.3728   0.02463   0.01696  -0.0517   0.3127   0.9422
  11.000   1.4044   0.02579   0.01825  -0.0500   0.3068   1.0000
  11.250   1.4217   0.02642   0.01891  -0.0493   0.3044   1.0000
  11.500   1.4406   0.02702   0.01950  -0.0489   0.3020   1.0000
  11.750   1.4536   0.02784   0.02041  -0.0478   0.2993   1.0000
  12.000   1.4640   0.02876   0.02146  -0.0465   0.2963   1.0000
  12.250   1.4750   0.02969   0.02248  -0.0453   0.2933   1.0000
  12.500   1.4864   0.03061   0.02346  -0.0442   0.2905   1.0000
  12.750   1.4995   0.03147   0.02434  -0.0433   0.2878   1.0000
  13.000   1.5148   0.03227   0.02513  -0.0427   0.2851   1.0000
  13.250   1.5180   0.03371   0.02675  -0.0412   0.2821   1.0000
  13.500   1.5218   0.03518   0.02835  -0.0399   0.2785   1.0000
  13.750   1.5275   0.03659   0.02984  -0.0388   0.2752   1.0000
  14.000   1.5364   0.03781   0.03109  -0.0380   0.2720   1.0000
  14.250   1.5459   0.03907   0.03237  -0.0373   0.2689   1.0000
  14.500   1.5425   0.04134   0.03483  -0.0362   0.2653   1.0000
  14.750   1.5421   0.04349   0.03711  -0.0354   0.2616   1.0000
  15.000   1.5455   0.04538   0.03905  -0.0348   0.2581   1.0000
  15.250   1.5546   0.04678   0.04045  -0.0345   0.2549   1.0000
  15.500   1.5478   0.04978   0.04363  -0.0340   0.2512   1.0000
  15.750   1.5405   0.05298   0.04699  -0.0337   0.2471   1.0000
  16.000   1.5391   0.05565   0.04973  -0.0336   0.2431   1.0000
  16.250   1.5468   0.05734   0.05141  -0.0335   0.2397   1.0000
  16.500   1.5303   0.06193   0.05621  -0.0339   0.2353   1.0000
  16.750   1.5174   0.06627   0.06069  -0.0344   0.2305   1.0000
  17.000   1.5186   0.06891   0.06335  -0.0348   0.2263   1.0000
  17.250   1.5056   0.07349   0.06805  -0.0356   0.2217   1.0000
  17.500   1.4840   0.07939   0.07411  -0.0370   0.2163   1.0000
  17.750   1.4862   0.08210   0.07683  -0.0376   0.2116   1.0000
  18.000   1.4611   0.08877   0.08367  -0.0395   0.2061   1.0000
  18.250   1.4442   0.09442   0.08942  -0.0412   0.2004   1.0000
  18.500   1.4491   0.09686   0.09186  -0.0420   0.1957   1.0000
  18.750   1.4101   0.10607   0.10127  -0.0452   0.1887   1.0000
  19.000   1.4179   0.10812   0.10328  -0.0459   0.1835   1.0000
<< Back to EPPLER 1233 AIRFOIL (e1233-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 1233 AIRFOIL (e1233-il)