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FX 71-L-150/30 AIRFOIL (fx711530-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 71-L-150/30 AIRFOIL (fx711530-il)
Reynolds number: 100,000
Max Cl/Cd: 39.46 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx711530-il-100000.txt
Download as CSV file: xf-fx711530-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7146   0.11124   0.10582  -0.0114   1.0000   0.0666
 -13.250  -0.7308   0.10269   0.09726  -0.0157   1.0000   0.0651
 -13.000  -0.8949   0.07778   0.07165  -0.0336   1.0000   0.0598
 -12.750  -0.8996   0.07350   0.06729  -0.0344   1.0000   0.0593
 -12.500  -0.9151   0.06902   0.06266  -0.0353   1.0000   0.0588
 -12.250  -0.9321   0.06482   0.05828  -0.0356   1.0000   0.0583
 -12.000  -0.9501   0.06096   0.05420  -0.0352   1.0000   0.0579
 -11.750  -0.9651   0.05750   0.05051  -0.0341   1.0000   0.0573
 -11.500  -0.9771   0.05437   0.04712  -0.0322   1.0000   0.0569
 -11.250  -0.9848   0.05147   0.04396  -0.0299   1.0000   0.0566
 -11.000  -0.9856   0.04859   0.04078  -0.0280   1.0000   0.0565
 -10.750  -0.9806   0.04604   0.03795  -0.0265   1.0000   0.0570
 -10.500  -0.9721   0.04365   0.03529  -0.0251   1.0000   0.0577
 -10.250  -0.9611   0.04141   0.03275  -0.0238   1.0000   0.0587
 -10.000  -0.9464   0.03925   0.03027  -0.0226   1.0000   0.0595
  -9.750  -0.9230   0.03698   0.02788  -0.0225   1.0000   0.0608
  -9.500  -0.8954   0.03507   0.02599  -0.0227   1.0000   0.0623
  -9.250  -0.8682   0.03332   0.02421  -0.0227   1.0000   0.0643
  -9.000  -0.8418   0.03170   0.02242  -0.0224   1.0000   0.0669
  -8.750  -0.8135   0.03008   0.02102  -0.0227   1.0000   0.0706
  -8.500  -0.7902   0.02866   0.01962  -0.0221   1.0000   0.0759
  -8.250  -0.7724   0.02729   0.01835  -0.0210   1.0000   0.0841
  -8.000  -0.7619   0.02569   0.01704  -0.0194   1.0000   0.0957
  -7.750  -0.7549   0.02431   0.01589  -0.0174   1.0000   0.1125
  -7.500  -0.7540   0.02311   0.01493  -0.0145   1.0000   0.1333
  -7.250  -0.7694   0.02262   0.01456  -0.0089   1.0000   0.1467
  -7.000  -0.7646   0.02129   0.01360  -0.0073   0.9925   0.1862
  -6.750  -0.7421   0.01929   0.01229  -0.0092   0.9798   0.2838
  -6.500  -0.7172   0.01818   0.01186  -0.0102   0.9690   0.3912
  -6.250  -0.6831   0.01818   0.01212  -0.0115   0.9604   0.4658
  -6.000  -0.6440   0.01878   0.01272  -0.0131   0.9527   0.5167
  -5.750  -0.6065   0.01981   0.01376  -0.0136   0.9446   0.5480
  -5.500  -0.5661   0.02103   0.01492  -0.0143   0.9373   0.5717
  -5.250  -0.5268   0.02215   0.01598  -0.0148   0.9304   0.5889
  -5.000  -0.4934   0.02302   0.01677  -0.0145   0.9222   0.6039
  -4.750  -0.4570   0.02365   0.01725  -0.0151   0.9159   0.6189
  -4.500  -0.4251   0.02460   0.01817  -0.0142   0.9078   0.6293
  -4.250  -0.3913   0.02527   0.01877  -0.0139   0.9010   0.6406
  -4.000  -0.3646   0.02557   0.01896  -0.0132   0.8941   0.6532
  -3.750  -0.3425   0.02567   0.01897  -0.0123   0.8864   0.6660
  -3.500  -0.3071   0.02616   0.01942  -0.0121   0.8813   0.6729
  -3.250  -0.2860   0.02617   0.01937  -0.0111   0.8743   0.6834
  -3.000  -0.2656   0.02603   0.01913  -0.0101   0.8672   0.6946
  -2.750  -0.2362   0.02623   0.01929  -0.0095   0.8610   0.7018
  -2.500  -0.2164   0.02608   0.01909  -0.0083   0.8528   0.7110
  -2.250  -0.1961   0.02582   0.01873  -0.0072   0.8464   0.7212
  -2.000  -0.1728   0.02585   0.01875  -0.0063   0.8387   0.7288
  -1.750  -0.1489   0.02573   0.01858  -0.0055   0.8332   0.7369
  -1.500  -0.1325   0.02555   0.01836  -0.0046   0.8266   0.7466
  -1.250  -0.1055   0.02562   0.01842  -0.0040   0.8209   0.7523
  -1.000  -0.0861   0.02541   0.01816  -0.0032   0.8157   0.7610
  -0.750  -0.0638   0.02549   0.01826  -0.0025   0.8085   0.7671
  -0.500  -0.0428   0.02525   0.01797  -0.0017   0.8029   0.7751
  -0.250  -0.0215   0.02537   0.01811  -0.0008   0.7949   0.7811
   0.000   0.0000   0.02519   0.01789   0.0000   0.7891   0.7890
   0.250   0.0215   0.02537   0.01812   0.0009   0.7812   0.7950
   0.500   0.0428   0.02525   0.01797   0.0017   0.7751   0.8030
   0.750   0.0638   0.02548   0.01826   0.0025   0.7670   0.8085
   1.000   0.0861   0.02540   0.01815   0.0032   0.7610   0.8157
   1.250   0.1055   0.02561   0.01842   0.0040   0.7523   0.8209
   1.500   0.1324   0.02555   0.01836   0.0046   0.7466   0.8266
   1.750   0.1488   0.02573   0.01858   0.0055   0.7369   0.8332
   2.000   0.1727   0.02585   0.01875   0.0063   0.7288   0.8387
   2.250   0.1962   0.02582   0.01873   0.0072   0.7212   0.8463
   2.500   0.2164   0.02608   0.01908   0.0083   0.7110   0.8528
   2.750   0.2362   0.02622   0.01928   0.0095   0.7017   0.8611
   3.000   0.2657   0.02603   0.01913   0.0101   0.6946   0.8672
   3.250   0.2859   0.02618   0.01937   0.0110   0.6834   0.8743
   3.500   0.3072   0.02615   0.01941   0.0121   0.6729   0.8813
   3.750   0.3425   0.02567   0.01897   0.0123   0.6660   0.8865
   4.000   0.3646   0.02558   0.01897   0.0132   0.6532   0.8941
   4.250   0.3912   0.02527   0.01877   0.0139   0.6406   0.9009
   4.500   0.4252   0.02461   0.01818   0.0142   0.6294   0.9078
   4.750   0.4571   0.02364   0.01725   0.0151   0.6189   0.9160
   5.000   0.4935   0.02302   0.01676   0.0145   0.6039   0.9222
   5.250   0.5268   0.02216   0.01599   0.0148   0.5890   0.9304
   5.500   0.5662   0.02102   0.01491   0.0143   0.5716   0.9373
   5.750   0.6065   0.01983   0.01378   0.0136   0.5482   0.9446
   6.000   0.6443   0.01878   0.01271   0.0130   0.5176   0.9527
   6.250   0.6831   0.01818   0.01212   0.0114   0.4661   0.9605
   6.500   0.7173   0.01818   0.01186   0.0101   0.3914   0.9690
   6.750   0.7421   0.01928   0.01229   0.0092   0.2837   0.9799
   7.000   0.7647   0.02130   0.01360   0.0073   0.1851   0.9926
   7.250   0.7690   0.02261   0.01456   0.0089   0.1465   1.0000
   7.500   0.7540   0.02311   0.01492   0.0145   0.1333   1.0000
   7.750   0.7551   0.02431   0.01589   0.0173   0.1125   1.0000
   8.000   0.7623   0.02568   0.01703   0.0193   0.0959   1.0000
   8.250   0.7726   0.02729   0.01834   0.0210   0.0840   1.0000
   8.500   0.7905   0.02867   0.01962   0.0220   0.0759   1.0000
   8.750   0.8136   0.03009   0.02103   0.0226   0.0704   1.0000
   9.000   0.8420   0.03170   0.02243   0.0224   0.0668   1.0000
   9.250   0.8683   0.03331   0.02419   0.0227   0.0644   1.0000
   9.500   0.8957   0.03506   0.02599   0.0226   0.0623   1.0000
   9.750   0.9231   0.03698   0.02789   0.0224   0.0609   1.0000
  10.000   0.9479   0.03929   0.03028   0.0224   0.0597   1.0000
  10.250   0.9611   0.04141   0.03275   0.0237   0.0587   1.0000
  10.500   0.9725   0.04368   0.03533   0.0250   0.0578   1.0000
  10.750   0.9813   0.04607   0.03799   0.0264   0.0572   1.0000
  11.000   0.9860   0.04863   0.04082   0.0280   0.0566   1.0000
  11.250   0.9855   0.05149   0.04398   0.0298   0.0568   1.0000
  11.500   0.9779   0.05438   0.04714   0.0321   0.0570   1.0000
  11.750   0.9657   0.05754   0.05054   0.0340   0.0573   1.0000
  12.000   0.9517   0.06093   0.05417   0.0351   0.0579   1.0000
  12.250   0.9329   0.06484   0.05830   0.0355   0.0583   1.0000
  12.500   0.9173   0.06896   0.06260   0.0352   0.0588   1.0000
  12.750   0.9005   0.07349   0.06729   0.0343   0.0593   1.0000
  13.000   0.8926   0.07797   0.07186   0.0334   0.0598   1.0000
  13.250   0.6911   0.11318   0.10781   0.0085   0.0688   1.0000
  13.500   0.7096   0.11305   0.10766   0.0100   0.0678   1.0000
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