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FX 71-L-150/30 AIRFOIL (fx71l150-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/30 AIRFOIL (fx71l150-il)
Reynolds number: 200,000
Max Cl/Cd: 47.16 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx71l150-il-200000.txt
Download as CSV file: xf-fx71l150-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.8655   0.09791   0.09351  -0.0208   1.0000   0.0373
 -14.750  -0.8630   0.09400   0.08960  -0.0221   1.0000   0.0369
 -14.500  -0.8799   0.08760   0.08309  -0.0255   1.0000   0.0365
 -14.250  -0.9068   0.08038   0.07570  -0.0294   1.0000   0.0361
 -14.000  -0.9341   0.07376   0.06886  -0.0325   1.0000   0.0356
 -13.750  -0.9621   0.06759   0.06244  -0.0348   1.0000   0.0350
 -13.500  -0.9985   0.06109   0.05555  -0.0363   1.0000   0.0342
 -13.250  -1.0551   0.05472   0.04852  -0.0362   1.0000   0.0333
 -13.000  -1.0711   0.05216   0.04566  -0.0350   1.0000   0.0331
 -12.750  -1.0636   0.04939   0.04275  -0.0344   1.0000   0.0329
 -12.500  -1.0599   0.04677   0.03995  -0.0335   1.0000   0.0328
 -12.250  -1.0537   0.04433   0.03734  -0.0325   1.0000   0.0327
 -12.000  -1.0476   0.04206   0.03487  -0.0313   1.0000   0.0327
 -11.750  -1.0353   0.03997   0.03261  -0.0304   1.0000   0.0327
 -11.500  -1.0227   0.03803   0.03048  -0.0294   1.0000   0.0327
 -11.250  -1.0075   0.03627   0.02855  -0.0285   1.0000   0.0328
 -11.000  -0.9904   0.03466   0.02677  -0.0277   1.0000   0.0330
 -10.750  -0.9592   0.03288   0.02501  -0.0282   1.0000   0.0335
 -10.500  -0.9347   0.03155   0.02371  -0.0280   1.0000   0.0340
 -10.250  -0.9139   0.03037   0.02254  -0.0274   1.0000   0.0345
 -10.000  -0.8940   0.02923   0.02139  -0.0267   1.0000   0.0350
  -9.750  -0.8757   0.02812   0.02026  -0.0259   1.0000   0.0358
  -9.500  -0.8586   0.02705   0.01917  -0.0250   1.0000   0.0365
  -9.250  -0.8429   0.02600   0.01807  -0.0240   1.0000   0.0374
  -9.000  -0.8309   0.02480   0.01697  -0.0227   1.0000   0.0384
  -8.750  -0.8190   0.02383   0.01606  -0.0214   1.0000   0.0398
  -8.500  -0.8063   0.02298   0.01520  -0.0200   1.0000   0.0415
  -8.250  -0.7840   0.02183   0.01408  -0.0208   0.9553   0.0437
  -8.000  -0.7524   0.02065   0.01282  -0.0231   0.9208   0.0483
  -7.750  -0.7352   0.01957   0.01171  -0.0224   0.8988   0.0549
  -7.500  -0.7235   0.01849   0.01069  -0.0206   0.8836   0.0691
  -7.250  -0.7123   0.01741   0.00976  -0.0186   0.8718   0.0970
  -7.000  -0.6981   0.01655   0.00906  -0.0170   0.8625   0.1333
  -6.750  -0.6826   0.01571   0.00843  -0.0156   0.8538   0.1773
  -6.500  -0.6675   0.01491   0.00786  -0.0140   0.8465   0.2300
  -6.250  -0.6522   0.01407   0.00733  -0.0125   0.8384   0.2926
  -6.000  -0.6351   0.01347   0.00697  -0.0109   0.8317   0.3541
  -5.750  -0.6142   0.01306   0.00678  -0.0099   0.8245   0.4083
  -5.500  -0.5918   0.01288   0.00671  -0.0088   0.8184   0.4512
  -5.250  -0.5675   0.01283   0.00674  -0.0081   0.8124   0.4876
  -5.000  -0.5424   0.01291   0.00679  -0.0074   0.8064   0.5192
  -4.750  -0.5170   0.01307   0.00694  -0.0066   0.8015   0.5430
  -4.500  -0.4905   0.01326   0.00715  -0.0060   0.7960   0.5629
  -4.250  -0.4642   0.01352   0.00735  -0.0054   0.7911   0.5806
  -4.000  -0.4373   0.01389   0.00771  -0.0047   0.7869   0.5958
  -3.750  -0.4093   0.01426   0.00812  -0.0042   0.7815   0.6075
  -3.500  -0.3827   0.01449   0.00824  -0.0037   0.7766   0.6186
  -3.250  -0.3546   0.01479   0.00854  -0.0033   0.7719   0.6255
  -3.000  -0.3277   0.01497   0.00866  -0.0030   0.7660   0.6355
  -2.750  -0.3000   0.01530   0.00898  -0.0024   0.7611   0.6430
  -2.500  -0.2732   0.01542   0.00904  -0.0021   0.7558   0.6516
  -2.250  -0.2453   0.01559   0.00922  -0.0018   0.7507   0.6569
  -2.000  -0.2188   0.01565   0.00916  -0.0015   0.7468   0.6654
  -1.750  -0.1906   0.01583   0.00939  -0.0013   0.7420   0.6696
  -1.500  -0.1632   0.01595   0.00949  -0.0011   0.7374   0.6758
  -1.250  -0.1361   0.01600   0.00948  -0.0009   0.7337   0.6817
  -1.000  -0.1085   0.01612   0.00964  -0.0007   0.7287   0.6864
  -0.750  -0.0816   0.01616   0.00960  -0.0006   0.7234   0.6937
  -0.500  -0.0545   0.01624   0.00969  -0.0001   0.7189   0.6980
  -0.250  -0.0273   0.01625   0.00972  -0.0001   0.7126   0.7035
   0.000   0.0000   0.01623   0.00965   0.0000   0.7085   0.7085
   0.250   0.0273   0.01625   0.00972   0.0001   0.7035   0.7126
   0.500   0.0544   0.01624   0.00969   0.0001   0.6980   0.7189
   0.750   0.0816   0.01616   0.00961   0.0006   0.6937   0.7235
   1.000   0.1085   0.01613   0.00965   0.0007   0.6865   0.7288
   1.250   0.1360   0.01600   0.00948   0.0009   0.6817   0.7337
   1.500   0.1632   0.01595   0.00949   0.0011   0.6758   0.7374
   1.750   0.1906   0.01583   0.00939   0.0013   0.6696   0.7420
   2.000   0.2188   0.01565   0.00915   0.0015   0.6653   0.7468
   2.250   0.2453   0.01559   0.00922   0.0018   0.6569   0.7507
   2.500   0.2732   0.01541   0.00903   0.0021   0.6516   0.7558
   2.750   0.3000   0.01531   0.00898   0.0024   0.6430   0.7611
   3.000   0.3277   0.01497   0.00867   0.0030   0.6355   0.7660
   3.250   0.3546   0.01479   0.00854   0.0033   0.6255   0.7719
   3.500   0.3827   0.01449   0.00825   0.0037   0.6186   0.7766
   3.750   0.4093   0.01427   0.00813   0.0042   0.6075   0.7815
   4.000   0.4373   0.01389   0.00771   0.0047   0.5957   0.7868
   4.250   0.4642   0.01352   0.00735   0.0054   0.5806   0.7911
   4.500   0.4905   0.01325   0.00713   0.0061   0.5625   0.7960
   4.750   0.5170   0.01306   0.00693   0.0066   0.5426   0.8015
   5.000   0.5424   0.01291   0.00679   0.0074   0.5188   0.8063
   5.250   0.5674   0.01283   0.00673   0.0081   0.4871   0.8124
   5.500   0.5918   0.01288   0.00670   0.0088   0.4508   0.8184
   5.750   0.6143   0.01306   0.00678   0.0099   0.4087   0.8245
   6.000   0.6352   0.01347   0.00697   0.0109   0.3546   0.8317
   6.250   0.6522   0.01408   0.00733   0.0125   0.2923   0.8384
   6.500   0.6676   0.01491   0.00786   0.0140   0.2301   0.8465
   6.750   0.6826   0.01571   0.00843   0.0156   0.1773   0.8538
   7.000   0.6979   0.01656   0.00906   0.0170   0.1325   0.8625
   7.250   0.7122   0.01743   0.00976   0.0186   0.0964   0.8718
   7.500   0.7237   0.01849   0.01069   0.0206   0.0691   0.8836
   7.750   0.7354   0.01957   0.01170   0.0224   0.0549   0.8989
   8.000   0.7528   0.02063   0.01281   0.0231   0.0485   0.9207
   8.250   0.7841   0.02185   0.01410   0.0208   0.0438   0.9554
   8.500   0.8067   0.02297   0.01519   0.0199   0.0414   1.0000
   8.750   0.8191   0.02385   0.01607   0.0213   0.0397   1.0000
   9.000   0.8310   0.02481   0.01697   0.0227   0.0383   1.0000
   9.250   0.8434   0.02598   0.01806   0.0239   0.0375   1.0000
   9.500   0.8591   0.02704   0.01915   0.0250   0.0367   1.0000
   9.750   0.8764   0.02812   0.02025   0.0259   0.0359   1.0000
  10.000   0.8948   0.02922   0.02137   0.0267   0.0352   1.0000
  10.250   0.9142   0.03037   0.02253   0.0274   0.0345   1.0000
  10.500   0.9354   0.03156   0.02372   0.0279   0.0340   1.0000
  10.750   0.9584   0.03284   0.02500   0.0283   0.0336   1.0000
  11.000   0.9903   0.03458   0.02670   0.0277   0.0331   1.0000
  11.250   1.0104   0.03627   0.02851   0.0282   0.0329   1.0000
  11.500   1.0246   0.03801   0.03045   0.0292   0.0328   1.0000
  11.750   1.0365   0.03998   0.03261   0.0303   0.0327   1.0000
  12.000   1.0495   0.04203   0.03482   0.0311   0.0327   1.0000
  12.250   1.0548   0.04433   0.03734   0.0324   0.0327   1.0000
  12.500   1.0617   0.04674   0.03991   0.0333   0.0328   1.0000
  12.750   1.0644   0.04937   0.04272   0.0343   0.0329   1.0000
  13.000   1.0703   0.05225   0.04575   0.0350   0.0330   1.0000
  13.250   1.0585   0.05487   0.04864   0.0360   0.0332   1.0000
  13.500   0.9967   0.06132   0.05581   0.0361   0.0344   1.0000
  13.750   0.9625   0.06767   0.06253   0.0347   0.0351   1.0000
  14.000   0.9350   0.07378   0.06889   0.0324   0.0357   1.0000
  14.250   0.9098   0.08012   0.07542   0.0294   0.0361   1.0000
  14.500   0.8858   0.08689   0.08235   0.0259   0.0366   1.0000
  14.750   0.8659   0.09371   0.08930   0.0222   0.0369   1.0000
  15.000   0.8628   0.09850   0.09412   0.0202   0.0373   1.0000
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