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FX 71-L-150/25 AIRFOIL (fx711525-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 71-L-150/25 AIRFOIL (fx711525-il)
Reynolds number: 50,000
Max Cl/Cd: 26.82 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx711525-il-50000-n5.txt
Download as CSV file: xf-fx711525-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 71-L-150/25 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
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.8253   0.08567   0.07716  -0.0267   1.0000   0.0491
 -13.000  -0.8442   0.07974   0.07101  -0.0294   1.0000   0.0490
 -12.750  -0.8613   0.07445   0.06547  -0.0315   1.0000   0.0491
 -12.500  -0.8718   0.07003   0.06085  -0.0326   1.0000   0.0494
 -12.250  -0.8734   0.06659   0.05725  -0.0332   1.0000   0.0497
 -12.000  -0.8725   0.06341   0.05390  -0.0334   1.0000   0.0503
 -11.750  -0.8691   0.06043   0.05075  -0.0335   1.0000   0.0509
 -11.500  -0.8628   0.05761   0.04775  -0.0333   1.0000   0.0518
 -11.250  -0.8532   0.05497   0.04488  -0.0330   1.0000   0.0530
 -11.000  -0.8391   0.05253   0.04215  -0.0325   1.0000   0.0544
 -10.750  -0.8200   0.05078   0.04037  -0.0320   1.0000   0.0562
 -10.500  -0.8006   0.04913   0.03863  -0.0313   1.0000   0.0586
 -10.250  -0.7814   0.04754   0.03694  -0.0306   1.0000   0.0620
 -10.000  -0.7656   0.04600   0.03535  -0.0299   1.0000   0.0658
  -9.750  -0.7522   0.04438   0.03373  -0.0293   1.0000   0.0708
  -9.500  -0.7388   0.04278   0.03211  -0.0285   1.0000   0.0769
  -9.250  -0.7276   0.04112   0.03046  -0.0278   1.0000   0.0846
  -9.000  -0.7200   0.03936   0.02879  -0.0272   1.0000   0.0951
  -8.750  -0.7127   0.03763   0.02718  -0.0265   1.0000   0.1075
  -8.500  -0.7055   0.03594   0.02557  -0.0257   1.0000   0.1235
  -8.250  -0.7010   0.03415   0.02400  -0.0245   1.0000   0.1404
  -8.000  -0.6984   0.03245   0.02249  -0.0230   1.0000   0.1602
  -7.750  -0.6967   0.03090   0.02116  -0.0210   1.0000   0.1841
  -7.500  -0.6959   0.02937   0.01992  -0.0189   1.0000   0.2150
  -7.250  -0.6969   0.02797   0.01891  -0.0164   1.0000   0.2540
  -7.000  -0.7000   0.02691   0.01827  -0.0130   1.0000   0.2987
  -6.750  -0.7061   0.02633   0.01803  -0.0086   1.0000   0.3421
  -6.500  -0.6880   0.02613   0.01814  -0.0074   0.9834   0.4044
  -6.250  -0.6554   0.02646   0.01853  -0.0080   0.9694   0.4592
  -6.000  -0.6218   0.02700   0.01895  -0.0085   0.9572   0.4989
  -5.750  -0.5894   0.02750   0.01927  -0.0090   0.9460   0.5297
  -5.500  -0.5524   0.02819   0.01978  -0.0097   0.9374   0.5539
  -5.250  -0.5191   0.02892   0.02033  -0.0095   0.9276   0.5733
  -5.000  -0.4823   0.02945   0.02068  -0.0102   0.9199   0.5904
  -4.750  -0.4555   0.02972   0.02077  -0.0098   0.9097   0.6065
  -4.500  -0.4143   0.03044   0.02133  -0.0104   0.9032   0.6160
  -4.250  -0.3902   0.03039   0.02113  -0.0099   0.8939   0.6292
  -4.000  -0.3603   0.03052   0.02111  -0.0099   0.8860   0.6400
  -3.750  -0.3334   0.03051   0.02096  -0.0097   0.8785   0.6502
  -3.500  -0.3104   0.03043   0.02075  -0.0091   0.8700   0.6606
  -3.250  -0.2831   0.03032   0.02051  -0.0090   0.8633   0.6694
  -3.000  -0.2608   0.03029   0.02039  -0.0082   0.8551   0.6786
  -2.750  -0.2390   0.03010   0.02010  -0.0075   0.8476   0.6879
  -2.500  -0.2119   0.03008   0.01998  -0.0073   0.8414   0.6954
  -2.250  -0.1977   0.02980   0.01962  -0.0060   0.8329   0.7053
  -2.000  -0.1686   0.02979   0.01954  -0.0059   0.8268   0.7113
  -1.750  -0.1531   0.02961   0.01929  -0.0046   0.8190   0.7210
  -1.500  -0.1286   0.02958   0.01921  -0.0041   0.8121   0.7274
  -1.250  -0.1036   0.02950   0.01907  -0.0036   0.8063   0.7348
  -1.000  -0.0876   0.02940   0.01894  -0.0025   0.7978   0.7430
  -0.750  -0.0607   0.02937   0.01888  -0.0023   0.7919   0.7491
  -0.500  -0.0460   0.02927   0.01874  -0.0011   0.7842   0.7580
  -0.250  -0.0200   0.02928   0.01875  -0.0008   0.7776   0.7633
   0.000   0.0000   0.02925   0.01870   0.0000   0.7709   0.7709
   0.250   0.0200   0.02928   0.01875   0.0008   0.7633   0.7776
   0.500   0.0460   0.02926   0.01873   0.0011   0.7580   0.7842
   0.750   0.0608   0.02937   0.01888   0.0023   0.7490   0.7919
   1.000   0.0876   0.02940   0.01894   0.0025   0.7430   0.7978
   1.250   0.1036   0.02950   0.01907   0.0036   0.7348   0.8063
   1.500   0.1286   0.02958   0.01921   0.0041   0.7274   0.8121
   1.750   0.1531   0.02961   0.01928   0.0046   0.7210   0.8190
   2.000   0.1686   0.02979   0.01954   0.0058   0.7113   0.8268
   2.250   0.1977   0.02980   0.01962   0.0060   0.7054   0.8329
   2.500   0.2120   0.03008   0.01998   0.0073   0.6954   0.8414
   2.750   0.2391   0.03010   0.02009   0.0075   0.6879   0.8477
   3.000   0.2608   0.03029   0.02038   0.0082   0.6786   0.8551
   3.250   0.2830   0.03032   0.02051   0.0090   0.6694   0.8633
   3.500   0.3105   0.03042   0.02074   0.0091   0.6607   0.8700
   3.750   0.3334   0.03051   0.02095   0.0097   0.6503   0.8785
   4.000   0.3604   0.03051   0.02110   0.0099   0.6401   0.8861
   4.250   0.3903   0.03039   0.02113   0.0099   0.6292   0.8939
   4.500   0.4144   0.03044   0.02133   0.0103   0.6161   0.9032
   4.750   0.4556   0.02971   0.02076   0.0097   0.6065   0.9097
   5.000   0.4824   0.02945   0.02067   0.0102   0.5904   0.9199
   5.250   0.5192   0.02891   0.02032   0.0095   0.5733   0.9277
   5.500   0.5524   0.02819   0.01978   0.0096   0.5540   0.9375
   5.750   0.5895   0.02750   0.01926   0.0089   0.5297   0.9461
   6.000   0.6220   0.02699   0.01894   0.0085   0.4988   0.9573
   6.250   0.6556   0.02645   0.01852   0.0080   0.4591   0.9695
   6.500   0.6881   0.02613   0.01814   0.0074   0.4045   0.9835
   6.750   0.7061   0.02633   0.01802   0.0086   0.3421   1.0000
   7.000   0.6999   0.02691   0.01827   0.0130   0.2985   1.0000
   7.250   0.6969   0.02797   0.01891   0.0164   0.2537   1.0000
   7.500   0.6961   0.02936   0.01992   0.0189   0.2150   1.0000
   7.750   0.6969   0.03090   0.02115   0.0210   0.1841   1.0000
   8.000   0.6985   0.03245   0.02250   0.0230   0.1598   1.0000
   8.250   0.7012   0.03416   0.02400   0.0245   0.1404   1.0000
   8.500   0.7059   0.03593   0.02556   0.0256   0.1237   1.0000
   8.750   0.7129   0.03764   0.02719   0.0265   0.1073   1.0000
   9.000   0.7201   0.03937   0.02880   0.0272   0.0947   1.0000
   9.250   0.7280   0.04112   0.03045   0.0277   0.0845   1.0000
   9.500   0.7390   0.04279   0.03211   0.0285   0.0766   1.0000
   9.750   0.7525   0.04439   0.03373   0.0292   0.0706   1.0000
  10.000   0.7665   0.04598   0.03532   0.0299   0.0659   1.0000
  10.250   0.7817   0.04755   0.03694   0.0305   0.0618   1.0000
  10.500   0.8015   0.04910   0.03860   0.0312   0.0587   1.0000
  10.750   0.8207   0.05078   0.04036   0.0319   0.0561   1.0000
  11.000   0.8400   0.05249   0.04209   0.0324   0.0545   1.0000
  11.250   0.8539   0.05499   0.04491   0.0329   0.0529   1.0000
  11.500   0.8637   0.05761   0.04775   0.0332   0.0519   1.0000
  11.750   0.8699   0.06043   0.05075   0.0334   0.0509   1.0000
  12.000   0.8733   0.06342   0.05392   0.0333   0.0503   1.0000
  12.250   0.8748   0.06657   0.05722   0.0331   0.0497   1.0000
  12.500   0.8738   0.06995   0.06075   0.0326   0.0493   1.0000
  12.750   0.8625   0.07442   0.06544   0.0314   0.0491   1.0000
  13.000   0.8456   0.07972   0.07099   0.0293   0.0491   1.0000
  13.250   0.8244   0.08594   0.07745   0.0264   0.0491   1.0000
  13.500   0.7633   0.09946   0.09142   0.0176   0.0504   1.0000
  13.750   0.7003   0.11803   0.11022   0.0056   0.0521   1.0000
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