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FX 71-L-150/20 AIRFOIL (fx711520-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 71-L-150/20 AIRFOIL (fx711520-il)
Reynolds number: 50,000
Max Cl/Cd: 25.55 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx711520-il-50000-n5.txt
Download as CSV file: xf-fx711520-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/20 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7538   0.10547   0.09763  -0.0087   1.0000   0.0501
 -13.250  -0.7890   0.09473   0.08668  -0.0155   1.0000   0.0494
 -13.000  -0.8197   0.08617   0.07790  -0.0205   1.0000   0.0490
 -12.750  -0.8424   0.07952   0.07101  -0.0239   1.0000   0.0488
 -12.500  -0.8587   0.07410   0.06534  -0.0261   1.0000   0.0489
 -12.250  -0.8698   0.06949   0.06049  -0.0275   1.0000   0.0491
 -12.000  -0.8757   0.06550   0.05625  -0.0283   1.0000   0.0494
 -11.750  -0.8770   0.06195   0.05245  -0.0287   1.0000   0.0499
 -11.500  -0.8734   0.05878   0.04902  -0.0288   1.0000   0.0506
 -11.250  -0.8653   0.05589   0.04583  -0.0286   1.0000   0.0514
 -11.000  -0.8486   0.05381   0.04369  -0.0283   1.0000   0.0528
 -10.750  -0.8305   0.05194   0.04172  -0.0278   1.0000   0.0544
 -10.500  -0.8091   0.05016   0.03972  -0.0271   1.0000   0.0568
 -10.250  -0.7902   0.04865   0.03824  -0.0265   1.0000   0.0594
 -10.000  -0.7721   0.04711   0.03656  -0.0259   1.0000   0.0634
  -9.750  -0.7582   0.04552   0.03501  -0.0254   1.0000   0.0676
  -9.500  -0.7442   0.04392   0.03343  -0.0249   1.0000   0.0728
  -9.250  -0.7318   0.04225   0.03177  -0.0243   1.0000   0.0798
  -9.000  -0.7221   0.04048   0.03005  -0.0238   1.0000   0.0893
  -8.750  -0.7137   0.03870   0.02838  -0.0234   1.0000   0.1011
  -8.500  -0.7062   0.03691   0.02675  -0.0230   1.0000   0.1155
  -8.250  -0.7005   0.03506   0.02507  -0.0224   1.0000   0.1327
  -8.000  -0.6966   0.03323   0.02345  -0.0215   1.0000   0.1528
  -7.750  -0.6950   0.03150   0.02196  -0.0202   1.0000   0.1766
  -7.500  -0.6936   0.02984   0.02063  -0.0187   1.0000   0.2069
  -7.250  -0.6938   0.02833   0.01950  -0.0168   1.0000   0.2474
  -7.000  -0.6922   0.02709   0.01874  -0.0149   0.9844   0.3012
  -6.750  -0.6670   0.02674   0.01892  -0.0150   0.9549   0.3827
  -6.500  -0.6331   0.02727   0.01954  -0.0153   0.9391   0.4402
  -6.250  -0.6003   0.02796   0.02009  -0.0154   0.9264   0.4810
  -6.000  -0.5686   0.02861   0.02052  -0.0155   0.9160   0.5114
  -5.750  -0.5369   0.02950   0.02121  -0.0149   0.9060   0.5334
  -5.250  -0.4776   0.03081   0.02211  -0.0137   0.8883   0.5695
  -5.000  -0.4528   0.03105   0.02215  -0.0130   0.8803   0.5863
  -4.750  -0.4211   0.03173   0.02268  -0.0121   0.8731   0.5973
  -4.500  -0.3978   0.03176   0.02255  -0.0114   0.8654   0.6096
  -4.250  -0.3738   0.03179   0.02240  -0.0106   0.8587   0.6217
  -4.000  -0.3489   0.03188   0.02239  -0.0099   0.8512   0.6309
  -3.750  -0.3263   0.03182   0.02218  -0.0091   0.8443   0.6416
  -3.500  -0.3034   0.03171   0.02195  -0.0084   0.8380   0.6504
  -3.250  -0.2787   0.03172   0.02187  -0.0078   0.8313   0.6583
  -3.000  -0.2611   0.03141   0.02144  -0.0070   0.8251   0.6691
  -2.750  -0.2336   0.03150   0.02145  -0.0065   0.8196   0.6754
  -2.500  -0.2168   0.03124   0.02110  -0.0057   0.8127   0.6855
  -2.250  -0.1932   0.03111   0.02091  -0.0051   0.8070   0.6917
  -2.000  -0.1691   0.03107   0.02081  -0.0047   0.8014   0.6979
  -1.750  -0.1545   0.03079   0.02046  -0.0038   0.7946   0.7077
  -1.500  -0.1283   0.03081   0.02044  -0.0033   0.7892   0.7130
  -1.250  -0.1052   0.03078   0.02038  -0.0028   0.7829   0.7197
  -1.000  -0.0894   0.03059   0.02013  -0.0021   0.7756   0.7286
  -0.750  -0.0631   0.03058   0.02011  -0.0016   0.7702   0.7332
  -0.500  -0.0411   0.03056   0.02008  -0.0011   0.7640   0.7391
  -0.250  -0.0235   0.03048   0.01997  -0.0005   0.7569   0.7461
   0.000   0.0000   0.03043   0.01992   0.0000   0.7514   0.7515
   0.250   0.0235   0.03048   0.01997   0.0005   0.7461   0.7570
   0.500   0.0411   0.03056   0.02008   0.0011   0.7390   0.7640
   0.750   0.0631   0.03058   0.02011   0.0016   0.7332   0.7702
   1.000   0.0895   0.03059   0.02013   0.0021   0.7286   0.7756
   1.250   0.1052   0.03078   0.02038   0.0028   0.7197   0.7829
   1.500   0.1283   0.03081   0.02044   0.0033   0.7130   0.7892
   1.750   0.1545   0.03079   0.02046   0.0039   0.7077   0.7946
   2.000   0.1691   0.03107   0.02081   0.0047   0.6979   0.8014
   2.250   0.1932   0.03111   0.02091   0.0051   0.6917   0.8070
   2.500   0.2169   0.03123   0.02110   0.0057   0.6855   0.8127
   2.750   0.2336   0.03150   0.02145   0.0065   0.6754   0.8197
   3.000   0.2611   0.03141   0.02144   0.0070   0.6691   0.8251
   3.250   0.2787   0.03172   0.02187   0.0078   0.6584   0.8313
   3.500   0.3035   0.03171   0.02195   0.0084   0.6504   0.8381
   3.750   0.3263   0.03182   0.02218   0.0091   0.6416   0.8443
   4.000   0.3490   0.03188   0.02238   0.0099   0.6309   0.8511
   4.250   0.3739   0.03179   0.02240   0.0106   0.6217   0.8587
   4.500   0.3978   0.03176   0.02255   0.0114   0.6096   0.8654
   4.750   0.4211   0.03172   0.02267   0.0121   0.5973   0.8732
   5.000   0.4528   0.03105   0.02215   0.0129   0.5863   0.8803
   5.250   0.4776   0.03080   0.02211   0.0137   0.5695   0.8883
   5.750   0.5369   0.02949   0.02121   0.0149   0.5334   0.9060
   6.000   0.5686   0.02861   0.02052   0.0155   0.5114   0.9160
   6.250   0.6004   0.02795   0.02009   0.0154   0.4809   0.9265
   6.500   0.6332   0.02726   0.01953   0.0153   0.4402   0.9391
   6.750   0.6671   0.02674   0.01892   0.0150   0.3827   0.9549
   7.000   0.6922   0.02709   0.01874   0.0149   0.3009   0.9846
   7.250   0.6939   0.02833   0.01949   0.0168   0.2471   1.0000
   7.500   0.6936   0.02985   0.02063   0.0187   0.2064   1.0000
   7.750   0.6950   0.03151   0.02197   0.0202   0.1759   1.0000
   8.000   0.6969   0.03322   0.02346   0.0215   0.1528   1.0000
   8.250   0.7008   0.03506   0.02507   0.0223   0.1327   1.0000
   8.500   0.7061   0.03694   0.02676   0.0230   0.1149   1.0000
   8.750   0.7138   0.03872   0.02840   0.0234   0.1004   1.0000
   9.000   0.7223   0.04049   0.03006   0.0237   0.0889   1.0000
   9.250   0.7321   0.04226   0.03177   0.0242   0.0796   1.0000
   9.500   0.7447   0.04392   0.03342   0.0248   0.0727   1.0000
   9.750   0.7588   0.04551   0.03500   0.0254   0.0675   1.0000
  10.000   0.7724   0.04713   0.03656   0.0258   0.0631   1.0000
  10.250   0.7908   0.04865   0.03823   0.0265   0.0593   1.0000
  10.500   0.8101   0.05017   0.03974   0.0271   0.0566   1.0000
  10.750   0.8313   0.05193   0.04171   0.0278   0.0544   1.0000
  11.000   0.8494   0.05380   0.04368   0.0282   0.0528   1.0000
  11.250   0.8660   0.05588   0.04582   0.0286   0.0514   1.0000
  11.500   0.8745   0.05876   0.04900   0.0287   0.0506   1.0000
  11.750   0.8775   0.06198   0.05249   0.0286   0.0499   1.0000
  12.000   0.8764   0.06552   0.05627   0.0282   0.0494   1.0000
  12.250   0.8701   0.06956   0.06056   0.0274   0.0490   1.0000
  12.500   0.8595   0.07412   0.06536   0.0260   0.0489   1.0000
  12.750   0.8432   0.07955   0.07103   0.0238   0.0488   1.0000
  13.000   0.8205   0.08618   0.07791   0.0204   0.0490   1.0000
  13.250   0.7903   0.09468   0.08663   0.0154   0.0494   1.0000
  13.500   0.7551   0.10543   0.09758   0.0086   0.0501   1.0000
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