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FX 71-L-150/30 AIRFOIL (fx711530-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 71-L-150/30 AIRFOIL (fx711530-il)
Reynolds number: 50,000
Max Cl/Cd: 26.93 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx711530-il-50000-n5.txt
Download as CSV file: xf-fx711530-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/30 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7298   0.10912   0.10119  -0.0115   1.0000   0.0510
 -13.500  -0.7733   0.09618   0.08802  -0.0196   1.0000   0.0501
 -13.250  -0.8083   0.08672   0.07829  -0.0252   1.0000   0.0498
 -13.000  -0.8321   0.07984   0.07116  -0.0287   1.0000   0.0496
 -12.750  -0.8478   0.07447   0.06556  -0.0308   1.0000   0.0496
 -12.500  -0.8578   0.06996   0.06082  -0.0321   1.0000   0.0499
 -12.250  -0.8632   0.06605   0.05669  -0.0329   1.0000   0.0504
 -12.000  -0.8646   0.06254   0.05295  -0.0333   1.0000   0.0511
 -11.750  -0.8619   0.05938   0.04953  -0.0333   1.0000   0.0519
 -11.500  -0.8565   0.05641   0.04624  -0.0331   1.0000   0.0532
 -11.250  -0.8433   0.05439   0.04420  -0.0328   1.0000   0.0549
 -11.000  -0.8311   0.05240   0.04213  -0.0324   1.0000   0.0572
 -10.750  -0.8165   0.05036   0.03987  -0.0318   1.0000   0.0603
 -10.500  -0.8014   0.04875   0.03830  -0.0313   1.0000   0.0635
 -10.250  -0.7834   0.04714   0.03655  -0.0305   1.0000   0.0677
 -10.000  -0.7688   0.04557   0.03499  -0.0297   1.0000   0.0720
  -9.750  -0.7549   0.04394   0.03334  -0.0289   1.0000   0.0777
  -9.500  -0.7440   0.04226   0.03163  -0.0282   1.0000   0.0855
  -9.250  -0.7370   0.04044   0.02991  -0.0276   1.0000   0.0957
  -9.000  -0.7301   0.03869   0.02826  -0.0270   1.0000   0.1072
  -8.750  -0.7237   0.03693   0.02661  -0.0261   1.0000   0.1212
  -8.500  -0.7179   0.03520   0.02503  -0.0250   1.0000   0.1363
  -8.250  -0.7137   0.03350   0.02350  -0.0236   1.0000   0.1538
  -8.000  -0.7110   0.03190   0.02207  -0.0217   1.0000   0.1746
  -7.750  -0.7101   0.03035   0.02080  -0.0195   1.0000   0.1993
  -7.500  -0.7086   0.02887   0.01961  -0.0174   1.0000   0.2339
  -7.250  -0.7077   0.02756   0.01870  -0.0149   1.0000   0.2760
  -7.000  -0.7063   0.02664   0.01818  -0.0119   1.0000   0.3224
  -6.750  -0.7066   0.02624   0.01810  -0.0080   1.0000   0.3642
  -6.500  -0.6874   0.02621   0.01828  -0.0069   0.9821   0.4156
  -6.000  -0.6188   0.02710   0.01900  -0.0087   0.9517   0.5003
  -5.750  -0.5827   0.02793   0.01967  -0.0090   0.9398   0.5263
  -5.500  -0.5465   0.02867   0.02023  -0.0095   0.9298   0.5484
  -5.250  -0.5124   0.02927   0.02066  -0.0097   0.9202   0.5669
  -5.000  -0.4809   0.02963   0.02081  -0.0099   0.9111   0.5837
  -4.750  -0.4531   0.02974   0.02073  -0.0099   0.9016   0.5999
  -4.500  -0.4168   0.03025   0.02110  -0.0102   0.8940   0.6100
  -4.250  -0.3904   0.03025   0.02094  -0.0099   0.8847   0.6221
  -4.000  -0.3683   0.03007   0.02058  -0.0093   0.8756   0.6352
  -3.750  -0.3395   0.03019   0.02058  -0.0090   0.8675   0.6444
  -3.500  -0.3160   0.03003   0.02029  -0.0085   0.8597   0.6546
  -3.250  -0.2972   0.02973   0.01986  -0.0076   0.8513   0.6659
  -3.000  -0.2673   0.02980   0.01983  -0.0074   0.8449   0.6732
  -2.750  -0.2469   0.02961   0.01955  -0.0065   0.8371   0.6829
  -2.500  -0.2237   0.02942   0.01924  -0.0060   0.8309   0.6920
  -2.250  -0.2014   0.02933   0.01909  -0.0053   0.8236   0.6992
  -2.000  -0.1817   0.02903   0.01869  -0.0046   0.8178   0.7082
  -1.750  -0.1592   0.02896   0.01858  -0.0040   0.8108   0.7152
  -1.500  -0.1370   0.02879   0.01835  -0.0033   0.8045   0.7232
  -1.250  -0.1175   0.02865   0.01815  -0.0024   0.7973   0.7318
  -1.000  -0.0910   0.02860   0.01807  -0.0020   0.7907   0.7378
  -0.750  -0.0713   0.02844   0.01787  -0.0012   0.7836   0.7460
  -0.500  -0.0444   0.02843   0.01786  -0.0010   0.7769   0.7512
  -0.250  -0.0238   0.02836   0.01775  -0.0003   0.7703   0.7585
   0.000   0.0000   0.02837   0.01777   0.0000   0.7638   0.7638
   0.250   0.0238   0.02836   0.01774   0.0003   0.7585   0.7703
   0.500   0.0444   0.02843   0.01785   0.0010   0.7512   0.7769
   0.750   0.0713   0.02844   0.01787   0.0012   0.7460   0.7836
   1.000   0.0910   0.02859   0.01807   0.0020   0.7378   0.7907
   1.250   0.1175   0.02865   0.01815   0.0024   0.7318   0.7973
   1.500   0.1370   0.02879   0.01835   0.0033   0.7232   0.8045
   1.750   0.1592   0.02896   0.01858   0.0040   0.7152   0.8108
   2.000   0.1817   0.02903   0.01869   0.0046   0.7082   0.8178
   2.250   0.2014   0.02932   0.01909   0.0053   0.6992   0.8236
   2.500   0.2237   0.02942   0.01923   0.0060   0.6920   0.8309
   2.750   0.2469   0.02962   0.01955   0.0065   0.6829   0.8371
   3.000   0.2673   0.02980   0.01982   0.0074   0.6732   0.8449
   3.250   0.2973   0.02972   0.01985   0.0076   0.6659   0.8513
   3.500   0.3161   0.03003   0.02029   0.0085   0.6546   0.8596
   3.750   0.3396   0.03018   0.02057   0.0090   0.6444   0.8675
   4.000   0.3684   0.03006   0.02057   0.0093   0.6352   0.8756
   4.250   0.3905   0.03024   0.02093   0.0099   0.6221   0.8847
   4.500   0.4169   0.03024   0.02109   0.0102   0.6100   0.8940
   4.750   0.4532   0.02973   0.02072   0.0099   0.5999   0.9016
   5.000   0.4810   0.02962   0.02080   0.0099   0.5837   0.9112
   5.250   0.5126   0.02926   0.02065   0.0097   0.5669   0.9203
   5.500   0.5466   0.02866   0.02022   0.0095   0.5484   0.9299
   5.750   0.5828   0.02792   0.01966   0.0090   0.5262   0.9399
   6.000   0.6189   0.02710   0.01900   0.0086   0.5004   0.9518
   6.500   0.6876   0.02621   0.01827   0.0069   0.4155   0.9822
   6.750   0.7065   0.02623   0.01810   0.0080   0.3643   1.0000
   7.000   0.7063   0.02664   0.01817   0.0119   0.3223   1.0000
   7.250   0.7078   0.02756   0.01869   0.0149   0.2758   1.0000
   7.500   0.7087   0.02887   0.01960   0.0174   0.2338   1.0000
   7.750   0.7103   0.03035   0.02080   0.0195   0.1992   1.0000
   8.000   0.7113   0.03190   0.02206   0.0216   0.1746   1.0000
   8.250   0.7140   0.03350   0.02350   0.0235   0.1536   1.0000
   8.500   0.7183   0.03520   0.02503   0.0249   0.1362   1.0000
   8.750   0.7237   0.03695   0.02662   0.0261   0.1207   1.0000
   9.000   0.7303   0.03870   0.02826   0.0269   0.1070   1.0000
   9.250   0.7374   0.04044   0.02990   0.0275   0.0956   1.0000
   9.500   0.7447   0.04224   0.03161   0.0281   0.0855   1.0000
   9.750   0.7555   0.04393   0.03333   0.0288   0.0777   1.0000
  10.000   0.7696   0.04554   0.03495   0.0297   0.0721   1.0000
  10.250   0.7841   0.04713   0.03654   0.0304   0.0677   1.0000
  10.500   0.8019   0.04876   0.03831   0.0312   0.0633   1.0000
  10.750   0.8181   0.05033   0.03985   0.0318   0.0605   1.0000
  11.000   0.8321   0.05237   0.04210   0.0323   0.0573   1.0000
  11.250   0.8447   0.05438   0.04420   0.0327   0.0550   1.0000
  11.500   0.8579   0.05635   0.04618   0.0330   0.0533   1.0000
  11.750   0.8629   0.05938   0.04954   0.0332   0.0519   1.0000
  12.000   0.8659   0.06250   0.05291   0.0332   0.0511   1.0000
  12.250   0.8641   0.06606   0.05670   0.0328   0.0504   1.0000
  12.500   0.8587   0.06997   0.06084   0.0320   0.0500   1.0000
  12.750   0.8488   0.07448   0.06558   0.0307   0.0497   1.0000
  13.000   0.8331   0.07985   0.07118   0.0286   0.0495   1.0000
  13.250   0.8093   0.08673   0.07830   0.0251   0.0497   1.0000
  13.500   0.7748   0.09611   0.08794   0.0195   0.0502   1.0000
  13.750   0.7306   0.10923   0.10129   0.0113   0.0510   1.0000
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