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AIRFOIL 3024 9.84% (s3024-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: AIRFOIL 3024 9.84% (s3024-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.05 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3024-il-1000000.txt
Download as CSV file: xf-s3024-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AIRFOIL 3024    9.84%                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2462   0.09666   0.09513  -0.0415   0.9669   0.0106
 -10.250  -0.2424   0.09261   0.09106  -0.0431   0.9588   0.0109
  -9.250  -0.3324   0.09077   0.08921  -0.0408   0.9889   0.0108
  -9.000  -0.3184   0.08530   0.08374  -0.0470   0.9798   0.0111
  -8.750  -0.3011   0.07843   0.07685  -0.0558   0.9691   0.0118
  -8.500  -0.2875   0.07354   0.07192  -0.0616   0.9546   0.0119
  -8.250  -0.2880   0.06900   0.06733  -0.0646   0.9350   0.0119
  -8.000  -0.2959   0.06526   0.06354  -0.0659   0.9182   0.0119
  -7.750  -0.3030   0.06072   0.05896  -0.0692   0.9044   0.0119
  -7.500  -0.3041   0.05419   0.05236  -0.0745   0.8935   0.0120
  -7.250  -0.3089   0.02835   0.02637  -0.0730   0.8672   0.0122
  -7.000  -0.3131   0.02212   0.01988  -0.0750   0.8608   0.0124
  -6.750  -0.3009   0.01948   0.01710  -0.0754   0.8555   0.0126
  -6.500  -0.2871   0.01653   0.01397  -0.0759   0.8501   0.0128
  -6.250  -0.2708   0.01414   0.01138  -0.0760   0.8451   0.0132
  -6.000  -0.2535   0.01159   0.00857  -0.0760   0.8404   0.0137
  -5.750  -0.2417   0.01779   0.01351  -0.0794   0.8466   0.0114
  -5.500  -0.2192   0.01552   0.01086  -0.0786   0.8420   0.0112
  -5.250  -0.1940   0.01415   0.00927  -0.0782   0.8372   0.0113
  -5.000  -0.1683   0.01303   0.00796  -0.0778   0.8324   0.0113
  -4.750  -0.1424   0.01212   0.00688  -0.0773   0.8279   0.0113
  -4.500  -0.1158   0.01131   0.00597  -0.0771   0.8231   0.0114
  -4.250  -0.0887   0.01084   0.00541  -0.0769   0.8181   0.0117
  -4.000  -0.0616   0.01047   0.00495  -0.0766   0.8135   0.0119
  -3.750  -0.0347   0.00985   0.00428  -0.0764   0.8084   0.0120
  -3.500  -0.0085   0.00914   0.00348  -0.0760   0.8031   0.0122
  -3.250   0.0180   0.00859   0.00282  -0.0757   0.7981   0.0129
  -3.000   0.0457   0.00826   0.00248  -0.0756   0.7926   0.0139
  -2.750   0.0734   0.00803   0.00219  -0.0755   0.7870   0.0149
  -2.500   0.1013   0.00785   0.00196  -0.0754   0.7816   0.0158
  -2.250   0.1292   0.00761   0.00170  -0.0753   0.7755   0.0187
  -2.000   0.1562   0.00726   0.00148  -0.0751   0.7697   0.0589
  -1.750   0.1836   0.00692   0.00136  -0.0751   0.7633   0.1190
  -1.500   0.2108   0.00668   0.00126  -0.0751   0.7566   0.1782
  -1.250   0.2382   0.00643   0.00120  -0.0751   0.7498   0.2446
  -1.000   0.2649   0.00613   0.00114  -0.0750   0.7422   0.3373
  -0.750   0.2915   0.00578   0.00111  -0.0749   0.7345   0.4508
  -0.500   0.3173   0.00543   0.00110  -0.0746   0.7265   0.5770
  -0.250   0.3420   0.00503   0.00110  -0.0740   0.7181   0.7186
   0.000   0.3625   0.00461   0.00115  -0.0721   0.7098   0.8814
   0.250   0.3947   0.00454   0.00119  -0.0726   0.7005   0.9627
   0.500   0.4328   0.00459   0.00117  -0.0748   0.6908   0.9840
   0.750   0.4765   0.00464   0.00115  -0.0782   0.6799   0.9936
   1.000   0.5198   0.00469   0.00112  -0.0817   0.6676   1.0000
   1.250   0.5453   0.00475   0.00113  -0.0812   0.6552   1.0000
   1.500   0.5706   0.00484   0.00115  -0.0806   0.6413   1.0000
   1.750   0.5960   0.00493   0.00117  -0.0801   0.6266   1.0000
   2.000   0.6212   0.00505   0.00121  -0.0796   0.6111   1.0000
   2.500   0.6716   0.00531   0.00133  -0.0785   0.5772   1.0000
   2.750   0.6967   0.00545   0.00140  -0.0780   0.5591   1.0000
   3.000   0.7217   0.00562   0.00149  -0.0775   0.5401   1.0000
   3.500   0.7717   0.00598   0.00169  -0.0764   0.5016   1.0000
   3.750   0.7966   0.00618   0.00181  -0.0759   0.4806   1.0000
   4.000   0.8215   0.00639   0.00195  -0.0754   0.4597   1.0000
   4.250   0.8463   0.00662   0.00209  -0.0749   0.4364   1.0000
   4.500   0.8711   0.00686   0.00224  -0.0744   0.4136   1.0000
   4.750   0.8956   0.00713   0.00241  -0.0739   0.3907   1.0000
   5.000   0.9202   0.00740   0.00260  -0.0734   0.3671   1.0000
   5.250   0.9444   0.00770   0.00280  -0.0729   0.3435   1.0000
   5.500   0.9678   0.00806   0.00303  -0.0722   0.3130   1.0000
   5.750   0.9908   0.00846   0.00328  -0.0715   0.2816   1.0000
   6.000   1.0138   0.00886   0.00355  -0.0709   0.2529   1.0000
   6.250   1.0368   0.00925   0.00382  -0.0702   0.2280   1.0000
   6.500   1.0596   0.00965   0.00411  -0.0695   0.2038   1.0000
   6.750   1.0826   0.01003   0.00441  -0.0688   0.1826   1.0000
   7.000   1.1047   0.01047   0.00473  -0.0680   0.1606   1.0000
   7.250   1.1267   0.01091   0.00508  -0.0672   0.1394   1.0000
   7.500   1.1469   0.01148   0.00550  -0.0662   0.1124   1.0000
   7.750   1.1670   0.01204   0.00594  -0.0651   0.0900   1.0000
   8.000   1.1858   0.01269   0.00644  -0.0639   0.0663   1.0000
   8.250   1.1997   0.01369   0.00719  -0.0619   0.0322   1.0000
   8.500   1.2143   0.01460   0.00796  -0.0600   0.0130   1.0000
   8.750   1.2333   0.01515   0.00852  -0.0587   0.0110   1.0000
   9.000   1.2512   0.01574   0.00916  -0.0572   0.0097   1.0000
   9.250   1.2695   0.01624   0.00972  -0.0558   0.0094   1.0000
   9.500   1.2854   0.01675   0.01029  -0.0540   0.0091   1.0000
   9.750   1.2993   0.01734   0.01093  -0.0518   0.0086   1.0000
  10.000   1.3125   0.01797   0.01163  -0.0497   0.0084   1.0000
  10.250   1.3249   0.01868   0.01240  -0.0476   0.0080   1.0000
  10.500   1.3350   0.01956   0.01334  -0.0452   0.0076   1.0000
  10.750   1.3404   0.02077   0.01466  -0.0424   0.0073   1.0000
  11.000   1.3445   0.02210   0.01610  -0.0396   0.0071   1.0000
  11.250   1.3529   0.02319   0.01727  -0.0375   0.0070   1.0000
  11.500   1.3603   0.02439   0.01855  -0.0355   0.0070   1.0000
  11.750   1.3697   0.02548   0.01972  -0.0338   0.0069   1.0000
  12.000   1.3787   0.02664   0.02095  -0.0321   0.0068   1.0000
  12.250   1.3827   0.02823   0.02265  -0.0302   0.0068   1.0000
  12.500   1.3874   0.02984   0.02435  -0.0285   0.0067   1.0000
  12.750   1.3903   0.03165   0.02626  -0.0269   0.0066   1.0000
  13.000   1.3958   0.03331   0.02800  -0.0257   0.0064   1.0000
  13.250   1.3971   0.03542   0.03021  -0.0243   0.0064   1.0000
  13.500   1.3977   0.03770   0.03259  -0.0232   0.0063   1.0000
  13.750   1.4005   0.03984   0.03481  -0.0224   0.0061   1.0000
  14.000   1.3996   0.04245   0.03753  -0.0216   0.0061   1.0000
  14.250   1.3983   0.04522   0.04041  -0.0210   0.0060   1.0000
  14.500   1.3975   0.04806   0.04335  -0.0208   0.0060   1.0000
  14.750   1.3941   0.05134   0.04674  -0.0206   0.0060   1.0000
  15.000   1.3913   0.05472   0.05024  -0.0208   0.0058   1.0000
  15.250   1.3906   0.05794   0.05355  -0.0214   0.0057   1.0000
  15.500   1.3853   0.06193   0.05765  -0.0220   0.0057   1.0000
  15.750   1.3838   0.06554   0.06133  -0.0231   0.0055   1.0000
  16.000   1.3754   0.07025   0.06620  -0.0242   0.0056   1.0000
  16.250   1.3715   0.07448   0.07050  -0.0257   0.0054   1.0000
  16.500   1.3632   0.07947   0.07559  -0.0274   0.0053   1.0000
  16.750   1.3559   0.08449   0.08072  -0.0293   0.0053   1.0000
  17.000   1.3481   0.08971   0.08606  -0.0314   0.0053   1.0000
  17.250   1.3384   0.09535   0.09182  -0.0338   0.0052   1.0000
  17.500   1.3293   0.10108   0.09766  -0.0364   0.0052   1.0000
  17.750   1.3204   0.10699   0.10370  -0.0393   0.0052   1.0000
  18.000   1.3102   0.11315   0.10998  -0.0423   0.0052   1.0000
  18.250   1.2961   0.12012   0.11708  -0.0458   0.0051   1.0000
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