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EPPLER 1230 AIRFOIL (e1230-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1230 AIRFOIL (e1230-il)
Reynolds number: 100,000
Max Cl/Cd: 43.3 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1230-il-100000-n5.txt
Download as CSV file: xf-e1230-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1230 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4137   0.09636   0.09109  -0.0506   1.0000   0.0295
 -11.750  -0.4811   0.07737   0.07200  -0.0617   1.0000   0.0286
 -11.500  -0.5371   0.06608   0.06049  -0.0686   1.0000   0.0280
 -11.250  -0.5756   0.05983   0.05405  -0.0705   1.0000   0.0277
 -11.000  -0.6071   0.05550   0.04953  -0.0700   1.0000   0.0276
 -10.750  -0.6353   0.05243   0.04631  -0.0674   1.0000   0.0276
 -10.500  -0.6620   0.05026   0.04401  -0.0628   1.0000   0.0276
 -10.250  -0.6812   0.04805   0.04164  -0.0584   1.0000   0.0277
 -10.000  -0.6945   0.04587   0.03928  -0.0545   1.0000   0.0278
  -9.750  -0.7039   0.04383   0.03704  -0.0506   1.0000   0.0281
  -9.500  -0.6977   0.04127   0.03417  -0.0496   0.9967   0.0286
  -9.250  -0.6719   0.03816   0.03058  -0.0518   0.9891   0.0294
  -9.000  -0.6427   0.03581   0.02795  -0.0538   0.9810   0.0303
  -8.750  -0.6121   0.03430   0.02636  -0.0557   0.9715   0.0315
  -8.500  -0.5832   0.03272   0.02459  -0.0569   0.9604   0.0333
  -8.250  -0.5550   0.03118   0.02288  -0.0579   0.9481   0.0353
  -7.750  -0.4969   0.02849   0.01995  -0.0594   0.9223   0.0395
  -7.500  -0.4672   0.02730   0.01877  -0.0603   0.9093   0.0417
  -7.250  -0.4340   0.02615   0.01749  -0.0616   0.8969   0.0459
  -7.000  -0.3977   0.02506   0.01636  -0.0636   0.8850   0.0508
  -6.750  -0.3652   0.02403   0.01530  -0.0647   0.8697   0.0563
  -6.500  -0.3316   0.02311   0.01432  -0.0660   0.8537   0.0643
  -6.250  -0.2979   0.02226   0.01341  -0.0673   0.8369   0.0745
  -6.000  -0.2651   0.02154   0.01261  -0.0684   0.8191   0.0870
  -5.750  -0.2343   0.02091   0.01193  -0.0690   0.8006   0.1008
  -5.500  -0.2059   0.02035   0.01134  -0.0693   0.7821   0.1158
  -5.250  -0.1791   0.01985   0.01079  -0.0691   0.7641   0.1320
  -5.000  -0.1536   0.01937   0.01029  -0.0687   0.7466   0.1499
  -4.750  -0.1289   0.01891   0.00981  -0.0682   0.7300   0.1711
  -4.500  -0.1049   0.01846   0.00936  -0.0675   0.7142   0.1981
  -4.250  -0.0834   0.01797   0.00897  -0.0665   0.6985   0.2357
  -4.000  -0.0632   0.01740   0.00860  -0.0652   0.6838   0.2924
  -3.750  -0.0446   0.01678   0.00830  -0.0636   0.6706   0.3779
  -3.500  -0.0259   0.01645   0.00840  -0.0615   0.6575   0.4822
  -3.250  -0.0037   0.01654   0.00861  -0.0598   0.6441   0.5527
  -3.000   0.0206   0.01674   0.00870  -0.0585   0.6321   0.5928
  -2.750   0.0449   0.01694   0.00875  -0.0574   0.6198   0.6210
  -2.500   0.0691   0.01713   0.00877  -0.0563   0.6079   0.6434
  -2.000   0.1176   0.01737   0.00871  -0.0542   0.5856   0.6793
  -1.750   0.1423   0.01746   0.00867  -0.0531   0.5758   0.6950
  -1.500   0.1659   0.01753   0.00869  -0.0518   0.5650   0.7118
  -1.250   0.1896   0.01760   0.00866  -0.0505   0.5558   0.7296
  -1.000   0.2133   0.01763   0.00863  -0.0493   0.5458   0.7449
  -0.750   0.2384   0.01765   0.00854  -0.0485   0.5372   0.7561
  -0.500   0.2635   0.01767   0.00849  -0.0478   0.5276   0.7651
  -0.250   0.2898   0.01771   0.00838  -0.0473   0.5198   0.7724
   0.000   0.3154   0.01775   0.00837  -0.0469   0.5108   0.7795
   0.250   0.3416   0.01781   0.00829  -0.0466   0.5033   0.7863
   0.500   0.3681   0.01787   0.00830  -0.0463   0.4949   0.7920
   0.750   0.3944   0.01794   0.00828  -0.0460   0.4871   0.7985
   1.000   0.4214   0.01804   0.00828  -0.0459   0.4801   0.8043
   1.250   0.4478   0.01814   0.00835  -0.0457   0.4725   0.8103
   1.500   0.4743   0.01826   0.00837  -0.0455   0.4663   0.8172
   1.750   0.5009   0.01839   0.00847  -0.0453   0.4594   0.8234
   2.000   0.5271   0.01852   0.00858  -0.0451   0.4524   0.8307
   2.250   0.5542   0.01867   0.00863  -0.0450   0.4467   0.8384
   2.500   0.5807   0.01884   0.00883  -0.0448   0.4401   0.8469
   2.750   0.6082   0.01902   0.00901  -0.0448   0.4340   0.8555
   3.000   0.6372   0.01922   0.00915  -0.0452   0.4289   0.8656
   3.500   0.6952   0.01968   0.00965  -0.0460   0.4168   0.8969
   3.750   0.7286   0.01993   0.00984  -0.0473   0.4115   0.9128
   4.250   0.8008   0.02056   0.01051  -0.0514   0.4005   0.9542
   4.500   0.8387   0.02087   0.01077  -0.0539   0.3952   0.9788
   5.000   0.8918   0.02154   0.01137  -0.0546   0.3860   1.0000
   5.250   0.9115   0.02188   0.01170  -0.0534   0.3814   1.0000
   5.500   0.9332   0.02222   0.01200  -0.0526   0.3775   1.0000
   5.750   0.9566   0.02257   0.01226  -0.0521   0.3742   1.0000
   6.000   0.9777   0.02300   0.01270  -0.0512   0.3702   1.0000
   6.250   0.9976   0.02344   0.01319  -0.0502   0.3657   1.0000
   6.500   1.0190   0.02384   0.01361  -0.0493   0.3616   1.0000
   6.750   1.0420   0.02422   0.01395  -0.0488   0.3581   1.0000
   7.000   1.0670   0.02464   0.01427  -0.0486   0.3552   1.0000
   7.250   1.0847   0.02521   0.01500  -0.0472   0.3514   1.0000
   7.500   1.1037   0.02575   0.01561  -0.0461   0.3475   1.0000
   7.750   1.1244   0.02622   0.01611  -0.0453   0.3438   1.0000
   8.000   1.1470   0.02665   0.01653  -0.0447   0.3405   1.0000
   8.250   1.1720   0.02709   0.01691  -0.0445   0.3378   1.0000
   8.500   1.1862   0.02782   0.01781  -0.0428   0.3342   1.0000
   8.750   1.2024   0.02851   0.01862  -0.0414   0.3307   1.0000
   9.000   1.2204   0.02912   0.01930  -0.0403   0.3274   1.0000
   9.250   1.2409   0.02963   0.01983  -0.0395   0.3243   1.0000
   9.500   1.2646   0.03009   0.02026  -0.0392   0.3215   1.0000
   9.750   1.2788   0.03087   0.02116  -0.0376   0.3185   1.0000
  10.000   1.2873   0.03182   0.02229  -0.0353   0.3152   1.0000
  10.250   1.2978   0.03267   0.02326  -0.0333   0.3120   1.0000
  10.500   1.3120   0.03339   0.02406  -0.0318   0.3090   1.0000
  10.750   1.3311   0.03395   0.02463  -0.0309   0.3062   1.0000
  11.000   1.3567   0.03439   0.02504  -0.0309   0.3037   1.0000
  11.250   1.3521   0.03585   0.02674  -0.0274   0.3006   1.0000
  11.500   1.3484   0.03741   0.02851  -0.0243   0.2973   1.0000
  11.750   1.3508   0.03878   0.03001  -0.0221   0.2941   1.0000
  12.000   1.3620   0.03975   0.03105  -0.0209   0.2912   1.0000
  12.250   1.3836   0.04022   0.03152  -0.0205   0.2886   1.0000
  12.500   1.3949   0.04130   0.03268  -0.0193   0.2859   1.0000
  12.750   1.3588   0.04528   0.03698  -0.0157   0.2820   1.0000
  13.000   1.3324   0.04931   0.04122  -0.0138   0.2779   1.0000
  13.250   1.3359   0.05116   0.04315  -0.0131   0.2746   1.0000
  13.500   1.3655   0.05078   0.04276  -0.0128   0.2721   1.0000
  13.750   1.0907   0.08699   0.07945  -0.0197   0.2525   1.0000
  14.000   1.1383   0.08299   0.07548  -0.0178   0.2533   1.0000
  14.250   1.1921   0.07833   0.07085  -0.0158   0.2539   1.0000
  14.500   1.2618   0.07194   0.06447  -0.0135   0.2545   1.0000
  16.000   0.9878   0.13479   0.12779  -0.0345   0.1963   1.0000
  16.250   0.9654   0.14267   0.13573  -0.0380   0.1873   1.0000
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