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EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER STE 87(-3)-914 AIRFOIL (ste87391-il)
Reynolds number: 100,000
Max Cl/Cd: 45.46 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ste87391-il-100000-n5.txt
Download as CSV file: xf-ste87391-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER STE 87(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5170   0.08485   0.07977  -0.0776   0.9775   0.0272
 -10.750  -0.5404   0.07712   0.07195  -0.0834   0.9753   0.0269
 -10.500  -0.5648   0.07126   0.06596  -0.0869   0.9726   0.0267
 -10.250  -0.5921   0.06734   0.06194  -0.0866   0.9683   0.0265
 -10.000  -0.6177   0.06393   0.05839  -0.0860   0.9642   0.0264
  -9.750  -0.6296   0.05942   0.05351  -0.0885   0.9608   0.0266
  -9.500  -0.6429   0.05617   0.04994  -0.0867   0.9564   0.0269
  -9.000  -0.6323   0.04957   0.04266  -0.0874   0.9504   0.0279
  -8.750  -0.6146   0.04700   0.03983  -0.0885   0.9485   0.0285
  -8.500  -0.5952   0.04464   0.03717  -0.0893   0.9465   0.0290
  -8.250  -0.5826   0.04272   0.03502  -0.0881   0.9434   0.0294
  -8.000  -0.5632   0.04092   0.03297  -0.0881   0.9408   0.0299
  -7.750  -0.5398   0.03929   0.03109  -0.0885   0.9385   0.0306
  -7.500  -0.5138   0.03787   0.02945  -0.0892   0.9367   0.0316
  -7.250  -0.4858   0.03674   0.02810  -0.0902   0.9351   0.0332
  -7.000  -0.4552   0.03582   0.02694  -0.0914   0.9337   0.0348
  -6.750  -0.4375   0.03457   0.02568  -0.0905   0.9302   0.0360
  -6.500  -0.4136   0.03361   0.02465  -0.0907   0.9274   0.0371
  -6.250  -0.3855   0.03279   0.02373  -0.0916   0.9249   0.0387
  -6.000  -0.3544   0.03208   0.02287  -0.0930   0.9229   0.0408
  -5.750  -0.3211   0.03149   0.02210  -0.0948   0.9212   0.0435
  -5.500  -0.2860   0.03080   0.02133  -0.0971   0.9199   0.0494
  -5.250  -0.2660   0.03018   0.02066  -0.0963   0.9154   0.0565
  -5.000  -0.2355   0.02928   0.01993  -0.0977   0.9128   0.0815
  -4.750  -0.2031   0.02872   0.01979  -0.0996   0.9105   0.1664
  -4.500  -0.1697   0.02871   0.01975  -0.1012   0.9083   0.2043
  -4.250  -0.1342   0.02878   0.01989  -0.1033   0.9066   0.2468
  -4.000  -0.1142   0.02874   0.01982  -0.1024   0.9013   0.2708
  -3.750  -0.0855   0.02869   0.01980  -0.1031   0.8978   0.2913
  -3.500  -0.0529   0.02864   0.01972  -0.1044   0.8952   0.3076
  -3.250  -0.0181   0.02859   0.01964  -0.1060   0.8932   0.3220
  -3.000   0.0037   0.02853   0.01959  -0.1053   0.8880   0.3360
  -2.750   0.0315   0.02845   0.01954  -0.1057   0.8838   0.3535
  -2.500   0.0648   0.02836   0.01951  -0.1070   0.8810   0.3785
  -2.250   0.1005   0.02824   0.01950  -0.1088   0.8789   0.4141
  -2.000   0.1205   0.02813   0.01956  -0.1079   0.8724   0.4544
  -1.750   0.1504   0.02795   0.01967  -0.1085   0.8685   0.5202
  -1.500   0.1771   0.02787   0.02002  -0.1076   0.8656   0.6085
  -1.250   0.1859   0.02807   0.02044  -0.1031   0.8580   0.6728
  -1.000   0.2147   0.02825   0.02055  -0.1031   0.8535   0.7237
  -0.750   0.2494   0.02837   0.02057  -0.1042   0.8507   0.7543
  -0.500   0.2641   0.02855   0.02073  -0.1017   0.8418   0.7731
  -0.250   0.2940   0.02855   0.02066  -0.1017   0.8381   0.7914
   0.000   0.3110   0.02864   0.02073  -0.0996   0.8298   0.8056
   0.250   0.3384   0.02852   0.02058  -0.0991   0.8250   0.8197
   0.500   0.3570   0.02852   0.02055  -0.0972   0.8168   0.8319
   0.750   0.3844   0.02830   0.02031  -0.0967   0.8114   0.8443
   1.000   0.4031   0.02823   0.02023  -0.0949   0.8026   0.8560
   1.250   0.4293   0.02784   0.01982  -0.0939   0.7972   0.8676
   1.500   0.4455   0.02767   0.01967  -0.0915   0.7872   0.8797
   1.750   0.4696   0.02703   0.01903  -0.0897   0.7822   0.8990
   2.000   0.4761   0.02662   0.01867  -0.0849   0.7710   0.9207
   2.250   0.4890   0.02596   0.01805  -0.0812   0.7620   0.9453
   2.500   0.5159   0.02525   0.01736  -0.0805   0.7545   0.9624
   2.750   0.5423   0.02499   0.01712  -0.0804   0.7433   0.9717
   3.250   0.6035   0.02398   0.01612  -0.0813   0.7247   0.9981
   3.500   0.6319   0.02387   0.01603  -0.0817   0.7125   0.9981
   3.750   0.6628   0.02365   0.01582  -0.0824   0.7006   0.9981
   4.000   0.6963   0.02329   0.01547  -0.0833   0.6886   0.9981
   4.250   0.7311   0.02289   0.01509  -0.0845   0.6758   0.9981
   4.500   0.7653   0.02253   0.01472  -0.0855   0.6602   0.9981
   4.750   0.8001   0.02219   0.01435  -0.0866   0.6422   0.9981
   5.000   0.8371   0.02177   0.01391  -0.0880   0.6218   0.9981
   5.250   0.8736   0.02146   0.01352  -0.0893   0.5979   0.9981
   5.500   0.9094   0.02126   0.01320  -0.0906   0.5713   0.9981
   5.750   0.9414   0.02130   0.01314  -0.0914   0.5421   0.9981
   6.000   0.9698   0.02154   0.01327  -0.0917   0.5130   0.9981
   6.250   0.9955   0.02193   0.01354  -0.0917   0.4851   0.9981
   6.500   1.0193   0.02242   0.01392  -0.0915   0.4588   0.9981
   7.000   1.0629   0.02361   0.01495  -0.0905   0.4123   0.9981
   7.250   1.0842   0.02424   0.01552  -0.0900   0.3930   0.9981
   7.500   1.1052   0.02491   0.01614  -0.0894   0.3758   0.9981
   7.750   1.1259   0.02559   0.01681  -0.0888   0.3601   0.9981
   8.000   1.1464   0.02628   0.01749  -0.0883   0.3458   0.9981
   8.250   1.1672   0.02698   0.01820  -0.0877   0.3332   0.9981
   8.500   1.1884   0.02768   0.01892  -0.0872   0.3225   0.9981
   8.750   1.2089   0.02841   0.01967  -0.0867   0.3127   0.9981
   9.000   1.2294   0.02913   0.02048  -0.0861   0.3026   0.9981
   9.250   1.2498   0.02988   0.02126  -0.0855   0.2940   0.9981
   9.500   1.2697   0.03065   0.02211  -0.0849   0.2855   0.9981
   9.750   1.2891   0.03144   0.02297  -0.0842   0.2772   0.9981
  10.000   1.3067   0.03228   0.02389  -0.0833   0.2688   0.9981
  10.250   1.3230   0.03315   0.02489  -0.0822   0.2599   0.9981
  10.500   1.3381   0.03407   0.02583  -0.0810   0.2516   0.9981
  10.750   1.3507   0.03505   0.02699  -0.0795   0.2419   0.9981
  11.000   1.3615   0.03611   0.02814  -0.0778   0.2323   0.9981
  11.250   1.3686   0.03730   0.02937  -0.0758   0.2214   0.9981
  11.500   1.3730   0.03863   0.03081  -0.0735   0.2085   0.9981
  11.750   1.3748   0.04016   0.03242  -0.0712   0.1933   0.9981
  12.000   1.3770   0.04181   0.03416  -0.0692   0.1743   0.9981
  12.250   1.3786   0.04367   0.03603  -0.0672   0.1532   0.9981
  12.500   1.3810   0.04562   0.03798  -0.0655   0.1313   0.9981
  12.750   1.3805   0.04792   0.04023  -0.0637   0.1081   0.9981
  13.000   1.3757   0.05073   0.04294  -0.0618   0.0863   0.9981
  13.250   1.3685   0.05393   0.04606  -0.0599   0.0675   0.9981
  13.500   1.3591   0.05750   0.04960  -0.0582   0.0533   0.9981
  13.750   1.3493   0.06129   0.05342  -0.0569   0.0435   0.9981
  14.000   1.3384   0.06540   0.05762  -0.0559   0.0366   0.9981
  14.500   1.3150   0.07442   0.06690  -0.0552   0.0296   0.9981
  14.750   1.3021   0.07943   0.07206  -0.0556   0.0275   0.9981
  15.000   1.2871   0.08499   0.07778  -0.0564   0.0262   0.9981
  15.250   1.2715   0.09091   0.08383  -0.0578   0.0253   0.9981
  15.500   1.2575   0.09680   0.08996  -0.0594   0.0240   0.9981
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