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FX 84-W-097 (fx84w097-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 84-W-097 (fx84w097-il)
Reynolds number: 500,000
Max Cl/Cd: 96.19 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx84w097-il-500000-n5.txt
Download as CSV file: xf-fx84w097-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 84-W-097                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4962   0.10654   0.10426  -0.0110   1.0000   0.0085
 -10.750  -0.4979   0.10150   0.09923  -0.0134   1.0000   0.0086
  -9.750  -0.7241   0.03120   0.02800  -0.0570   0.9513   0.0083
  -9.500  -0.7160   0.02760   0.02388  -0.0565   0.9276   0.0085
  -9.250  -0.7057   0.02473   0.02058  -0.0555   0.9106   0.0087
  -9.000  -0.6884   0.02322   0.01883  -0.0546   0.8975   0.0090
  -8.500  -0.6456   0.02137   0.01665  -0.0535   0.8756   0.0096
  -8.250  -0.6232   0.02042   0.01551  -0.0530   0.8662   0.0099
  -7.750  -0.5777   0.01815   0.01276  -0.0520   0.8481   0.0107
  -7.500  -0.5539   0.01716   0.01153  -0.0516   0.8401   0.0111
  -7.250  -0.5293   0.01630   0.01046  -0.0512   0.8318   0.0115
  -7.000  -0.5041   0.01560   0.00958  -0.0509   0.8242   0.0118
  -6.750  -0.4795   0.01466   0.00851  -0.0505   0.8164   0.0125
  -6.500  -0.4535   0.01414   0.00789  -0.0503   0.8090   0.0131
  -6.250  -0.4271   0.01369   0.00733  -0.0501   0.8016   0.0138
  -6.000  -0.4005   0.01326   0.00680  -0.0500   0.7944   0.0147
  -5.750  -0.3738   0.01288   0.00631  -0.0498   0.7870   0.0157
  -5.500  -0.3473   0.01238   0.00572  -0.0496   0.7800   0.0167
  -5.250  -0.3206   0.01196   0.00524  -0.0495   0.7725   0.0180
  -5.000  -0.2936   0.01163   0.00483  -0.0493   0.7654   0.0193
  -4.750  -0.2664   0.01133   0.00445  -0.0492   0.7578   0.0207
  -4.500  -0.2391   0.01102   0.00407  -0.0491   0.7508   0.0224
  -4.250  -0.2119   0.01070   0.00372  -0.0490   0.7435   0.0249
  -4.000  -0.1844   0.01047   0.00341  -0.0489   0.7367   0.0273
  -3.750  -0.1568   0.01024   0.00312  -0.0489   0.7295   0.0296
  -3.500  -0.1292   0.00999   0.00286  -0.0488   0.7229   0.0344
  -3.250  -0.1014   0.00982   0.00264  -0.0488   0.7157   0.0386
  -3.000  -0.0738   0.00961   0.00242  -0.0488   0.7091   0.0458
  -2.750  -0.0459   0.00943   0.00224  -0.0488   0.7019   0.0547
  -2.500  -0.0182   0.00928   0.00207  -0.0487   0.6952   0.0664
  -2.250   0.0097   0.00910   0.00192  -0.0488   0.6877   0.0816
  -2.000   0.0375   0.00895   0.00180  -0.0488   0.6807   0.1027
  -1.750   0.0653   0.00877   0.00169  -0.0488   0.6731   0.1289
  -1.500   0.0930   0.00859   0.00158  -0.0489   0.6661   0.1650
  -1.250   0.1207   0.00837   0.00150  -0.0489   0.6585   0.2115
  -1.000   0.1481   0.00813   0.00143  -0.0490   0.6515   0.2750
  -0.750   0.1752   0.00780   0.00137  -0.0491   0.6441   0.3681
  -0.500   0.2017   0.00740   0.00131  -0.0490   0.6374   0.4885
  -0.250   0.2274   0.00694   0.00131  -0.0487   0.6302   0.6320
   0.000   0.2523   0.00664   0.00134  -0.0480   0.6235   0.7421
   0.250   0.2773   0.00649   0.00139  -0.0472   0.6162   0.8141
   0.500   0.3025   0.00644   0.00142  -0.0463   0.6094   0.8586
   0.750   0.3279   0.00642   0.00145  -0.0455   0.6018   0.8925
   1.000   0.3537   0.00643   0.00148  -0.0448   0.5943   0.9239
   1.250   0.3831   0.00645   0.00149  -0.0449   0.5858   0.9501
   1.500   0.4221   0.00648   0.00149  -0.0472   0.5772   0.9793
   1.750   0.4662   0.00652   0.00150  -0.0507   0.5680   0.9971
   2.000   0.4958   0.00659   0.00153  -0.0511   0.5597   1.0000
   2.250   0.5213   0.00668   0.00158  -0.0507   0.5518   1.0000
   2.500   0.5474   0.00676   0.00163  -0.0504   0.5428   1.0000
   2.750   0.5736   0.00687   0.00171  -0.0501   0.5326   1.0000
   3.000   0.6000   0.00698   0.00178  -0.0498   0.5213   1.0000
   3.250   0.6267   0.00710   0.00187  -0.0497   0.5110   1.0000
   3.500   0.6536   0.00721   0.00198  -0.0495   0.5007   1.0000
   3.750   0.6805   0.00734   0.00209  -0.0494   0.4892   1.0000
   4.000   0.7073   0.00749   0.00221  -0.0492   0.4772   1.0000
   4.250   0.7341   0.00764   0.00234  -0.0491   0.4636   1.0000
   4.500   0.7599   0.00790   0.00251  -0.0489   0.4356   1.0000
   4.750   0.7849   0.00827   0.00270  -0.0485   0.3952   1.0000
   5.000   0.8100   0.00863   0.00293  -0.0483   0.3601   1.0000
   5.250   0.8349   0.00903   0.00319  -0.0480   0.3254   1.0000
   5.500   0.8586   0.00957   0.00354  -0.0476   0.2792   1.0000
   5.750   0.8813   0.01025   0.00396  -0.0471   0.2251   1.0000
   6.250   0.9239   0.01187   0.00501  -0.0459   0.1146   1.0000
   6.500   0.9454   0.01262   0.00556  -0.0452   0.0765   1.0000
   6.750   0.9679   0.01322   0.00606  -0.0447   0.0542   1.0000
   7.000   0.9907   0.01376   0.00653  -0.0442   0.0411   1.0000
   7.250   1.0137   0.01426   0.00701  -0.0436   0.0326   1.0000
   7.500   1.0367   0.01474   0.00749  -0.0431   0.0267   1.0000
   7.750   1.0590   0.01527   0.00803  -0.0425   0.0223   1.0000
   8.000   1.0814   0.01575   0.00855  -0.0419   0.0197   1.0000
   8.250   1.1021   0.01636   0.00917  -0.0410   0.0171   1.0000
   8.500   1.1235   0.01690   0.00977  -0.0403   0.0156   1.0000
   8.750   1.1440   0.01747   0.01039  -0.0395   0.0143   1.0000
   9.000   1.1631   0.01813   0.01109  -0.0385   0.0130   1.0000
   9.250   1.1803   0.01890   0.01191  -0.0372   0.0119   1.0000
   9.500   1.1979   0.01957   0.01266  -0.0360   0.0113   1.0000
   9.750   1.2139   0.02030   0.01346  -0.0346   0.0107   1.0000
  10.000   1.2270   0.02105   0.01428  -0.0328   0.0103   1.0000
  10.250   1.2376   0.02186   0.01516  -0.0307   0.0098   1.0000
  10.500   1.2471   0.02279   0.01616  -0.0286   0.0095   1.0000
  10.750   1.2552   0.02388   0.01732  -0.0267   0.0091   1.0000
  11.000   1.2596   0.02532   0.01884  -0.0246   0.0087   1.0000
  11.250   1.2680   0.02655   0.02017  -0.0231   0.0084   1.0000
  11.500   1.2751   0.02797   0.02169  -0.0216   0.0082   1.0000
  11.750   1.2852   0.02919   0.02300  -0.0206   0.0079   1.0000
  12.000   1.2932   0.03065   0.02456  -0.0195   0.0076   1.0000
  12.250   1.2989   0.03236   0.02637  -0.0184   0.0074   1.0000
  12.500   1.3055   0.03406   0.02817  -0.0176   0.0072   1.0000
  12.750   1.3103   0.03598   0.03018  -0.0168   0.0070   1.0000
  13.000   1.3149   0.03799   0.03231  -0.0162   0.0068   1.0000
  13.250   1.3197   0.04004   0.03445  -0.0157   0.0066   1.0000
  13.500   1.3226   0.04236   0.03687  -0.0154   0.0065   1.0000
  13.750   1.3242   0.04490   0.03951  -0.0152   0.0063   1.0000
  14.000   1.3240   0.04772   0.04245  -0.0152   0.0062   1.0000
  14.250   1.3212   0.05096   0.04580  -0.0154   0.0061   1.0000
  14.500   1.3157   0.05463   0.04960  -0.0157   0.0060   1.0000
  14.750   1.3104   0.05844   0.05354  -0.0163   0.0059   1.0000
  15.000   1.3103   0.06175   0.05700  -0.0171   0.0059   1.0000
  15.250   1.3069   0.06564   0.06104  -0.0182   0.0058   1.0000
  15.500   1.3023   0.06989   0.06544  -0.0196   0.0057   1.0000
  15.750   1.2969   0.07439   0.07010  -0.0212   0.0056   1.0000
  16.000   1.2907   0.07920   0.07507  -0.0231   0.0056   1.0000
  16.250   1.2819   0.08464   0.08067  -0.0254   0.0055   1.0000
  16.500   1.2732   0.09026   0.08645  -0.0281   0.0055   1.0000
  16.750   1.2624   0.09648   0.09283  -0.0311   0.0054   1.0000
  17.000   1.2506   0.10312   0.09964  -0.0345   0.0054   1.0000
  17.250   1.2373   0.11034   0.10703  -0.0385   0.0053   1.0000
  17.500   1.2236   0.11779   0.11463  -0.0426   0.0053   1.0000
  17.750   1.2086   0.12592   0.12292  -0.0473   0.0053   1.0000
  18.000   1.1918   0.13471   0.13187  -0.0525   0.0053   1.0000
  18.250   1.1738   0.14420   0.14153  -0.0582   0.0053   1.0000
  18.500   1.1542   0.15451   0.15198  -0.0645   0.0054   1.0000
  18.750   1.1280   0.16733   0.16497  -0.0724   0.0054   1.0000
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