Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S3014-095-85 (s3014-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.87 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3014-il-1000000-n5.txt
Download as CSV file: xf-s3014-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3014-095-85                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7505   0.03525   0.03315  -0.0544   0.9600   0.0061
 -10.000  -0.7545   0.03091   0.02838  -0.0536   0.9305   0.0062
  -9.750  -0.7439   0.02882   0.02603  -0.0525   0.9161   0.0063
  -9.500  -0.7304   0.02690   0.02385  -0.0516   0.9047   0.0063
  -9.250  -0.7249   0.02312   0.01957  -0.0502   0.8939   0.0066
  -9.000  -0.7060   0.02180   0.01806  -0.0494   0.8860   0.0068
  -8.750  -0.6838   0.02096   0.01709  -0.0490   0.8788   0.0069
  -8.250  -0.6371   0.01964   0.01553  -0.0481   0.8656   0.0072
  -8.000  -0.6136   0.01888   0.01464  -0.0477   0.8594   0.0074
  -7.750  -0.5899   0.01806   0.01368  -0.0473   0.8536   0.0076
  -7.500  -0.5653   0.01743   0.01292  -0.0469   0.8475   0.0079
  -7.250  -0.5406   0.01677   0.01212  -0.0465   0.8420   0.0082
  -7.000  -0.5157   0.01603   0.01124  -0.0461   0.8362   0.0085
  -6.750  -0.4907   0.01532   0.01040  -0.0457   0.8304   0.0088
  -6.500  -0.4654   0.01457   0.00951  -0.0454   0.8249   0.0091
  -6.250  -0.4398   0.01392   0.00873  -0.0450   0.8191   0.0093
  -6.000  -0.4140   0.01332   0.00802  -0.0446   0.8138   0.0094
  -5.750  -0.3878   0.01276   0.00736  -0.0444   0.8080   0.0096
  -5.500  -0.3616   0.01224   0.00674  -0.0440   0.8022   0.0097
  -5.250  -0.3350   0.01179   0.00622  -0.0438   0.7968   0.0098
  -5.000  -0.3081   0.01146   0.00582  -0.0436   0.7907   0.0099
  -4.750  -0.2833   0.01054   0.00477  -0.0430   0.7850   0.0104
  -4.500  -0.2571   0.00998   0.00415  -0.0427   0.7786   0.0108
  -4.250  -0.2304   0.00962   0.00370  -0.0424   0.7722   0.0112
  -4.000  -0.2032   0.00931   0.00336  -0.0423   0.7654   0.0116
  -3.750  -0.1759   0.00906   0.00305  -0.0421   0.7585   0.0121
  -3.500  -0.1484   0.00882   0.00277  -0.0419   0.7512   0.0126
  -3.250  -0.1210   0.00861   0.00249  -0.0417   0.7438   0.0130
  -3.000  -0.0933   0.00842   0.00225  -0.0416   0.7358   0.0134
  -2.750  -0.0657   0.00825   0.00203  -0.0415   0.7277   0.0137
  -2.500  -0.0379   0.00810   0.00184  -0.0414   0.7184   0.0140
  -2.250  -0.0102   0.00798   0.00167  -0.0412   0.7080   0.0144
  -2.000   0.0176   0.00789   0.00152  -0.0411   0.6958   0.0148
  -1.750   0.0453   0.00781   0.00137  -0.0410   0.6825   0.0154
  -1.500   0.0730   0.00773   0.00122  -0.0409   0.6683   0.0170
  -1.250   0.1007   0.00766   0.00111  -0.0408   0.6530   0.0207
  -1.000   0.1276   0.00745   0.00100  -0.0406   0.6367   0.0668
  -0.750   0.1546   0.00729   0.00093  -0.0404   0.6207   0.1126
  -0.500   0.1816   0.00713   0.00089  -0.0403   0.6052   0.1667
  -0.250   0.2083   0.00694   0.00085  -0.0402   0.5900   0.2344
   0.250   0.2588   0.00618   0.00085  -0.0396   0.5584   0.5146
   0.500   0.2846   0.00600   0.00087  -0.0392   0.5417   0.6009
   0.750   0.3104   0.00588   0.00089  -0.0388   0.5242   0.6732
   1.000   0.3351   0.00573   0.00093  -0.0381   0.5064   0.7550
   1.250   0.3591   0.00561   0.00099  -0.0372   0.4884   0.8314
   1.500   0.3842   0.00552   0.00106  -0.0364   0.4688   0.9121
   1.750   0.4328   0.00564   0.00115  -0.0409   0.4437   0.9676
   2.000   0.4699   0.00584   0.00122  -0.0430   0.4176   0.9838
   2.250   0.5044   0.00603   0.00130  -0.0446   0.3925   0.9929
   2.500   0.5406   0.00623   0.00138  -0.0465   0.3669   0.9981
   2.750   0.5720   0.00643   0.00148  -0.0475   0.3431   1.0000
   3.000   0.5972   0.00664   0.00158  -0.0470   0.3216   1.0000
   3.250   0.6223   0.00684   0.00169  -0.0465   0.3020   1.0000
   3.500   0.6476   0.00703   0.00181  -0.0460   0.2848   1.0000
   3.750   0.6726   0.00725   0.00195  -0.0455   0.2659   1.0000
   4.000   0.6978   0.00745   0.00208  -0.0450   0.2506   1.0000
   4.250   0.7229   0.00767   0.00222  -0.0445   0.2347   1.0000
   4.750   0.7731   0.00809   0.00254  -0.0436   0.2078   1.0000
   5.000   0.7982   0.00830   0.00271  -0.0431   0.1952   1.0000
   5.250   0.8234   0.00850   0.00288  -0.0427   0.1847   1.0000
   5.500   0.8480   0.00876   0.00307  -0.0422   0.1699   1.0000
   5.750   0.8720   0.00910   0.00330  -0.0416   0.1495   1.0000
   6.000   0.8964   0.00938   0.00354  -0.0410   0.1353   1.0000
   6.250   0.9201   0.00975   0.00381  -0.0404   0.1161   1.0000
   6.500   0.9436   0.01013   0.00409  -0.0398   0.0994   1.0000
   6.750   0.9674   0.01049   0.00438  -0.0392   0.0851   1.0000
   7.000   0.9908   0.01087   0.00470  -0.0386   0.0708   1.0000
   7.250   1.0134   0.01134   0.00508  -0.0379   0.0546   1.0000
   7.500   1.0356   0.01185   0.00550  -0.0371   0.0394   1.0000
   7.750   1.0576   0.01236   0.00594  -0.0363   0.0267   1.0000
   8.000   1.0764   0.01321   0.00665  -0.0351   0.0075   1.0000
   8.250   1.0987   0.01367   0.00712  -0.0343   0.0052   1.0000
   8.500   1.1214   0.01407   0.00757  -0.0336   0.0044   1.0000
   8.750   1.1439   0.01448   0.00802  -0.0329   0.0041   1.0000
   9.000   1.1658   0.01492   0.00851  -0.0321   0.0038   1.0000
   9.250   1.1869   0.01542   0.00905  -0.0312   0.0035   1.0000
   9.500   1.2074   0.01597   0.00965  -0.0302   0.0032   1.0000
   9.750   1.2267   0.01659   0.01035  -0.0291   0.0030   1.0000
  10.000   1.2455   0.01721   0.01103  -0.0279   0.0028   1.0000
  10.250   1.2645   0.01778   0.01167  -0.0267   0.0028   1.0000
  10.500   1.2824   0.01838   0.01234  -0.0255   0.0027   1.0000
  10.750   1.2995   0.01900   0.01302  -0.0241   0.0026   1.0000
  11.000   1.3149   0.01969   0.01378  -0.0225   0.0025   1.0000
  11.250   1.3264   0.02041   0.01457  -0.0202   0.0025   1.0000
  11.500   1.3357   0.02119   0.01544  -0.0177   0.0024   1.0000
  11.750   1.3452   0.02202   0.01634  -0.0155   0.0023   1.0000
  12.000   1.3536   0.02297   0.01737  -0.0133   0.0023   1.0000
  12.250   1.3608   0.02406   0.01856  -0.0112   0.0022   1.0000
  12.500   1.3676   0.02524   0.01984  -0.0093   0.0021   1.0000
  12.750   1.3725   0.02664   0.02133  -0.0075   0.0021   1.0000
  13.000   1.3788   0.02800   0.02278  -0.0060   0.0020   1.0000
  13.250   1.3835   0.02955   0.02442  -0.0046   0.0020   1.0000
  13.500   1.3888   0.03112   0.02607  -0.0035   0.0019   1.0000
  13.750   1.3910   0.03306   0.02811  -0.0024   0.0019   1.0000
  14.000   1.3891   0.03551   0.03067  -0.0015   0.0018   1.0000
  14.250   1.3907   0.03774   0.03300  -0.0010   0.0018   1.0000
  14.500   1.3905   0.04028   0.03565  -0.0007   0.0018   1.0000
  14.750   1.3867   0.04337   0.03885  -0.0008   0.0018   1.0000
  15.000   1.3815   0.04684   0.04244  -0.0012   0.0017   1.0000
  15.250   1.3719   0.05106   0.04679  -0.0022   0.0017   1.0000
  15.500   1.3685   0.05469   0.05052  -0.0032   0.0017   1.0000
  15.750   1.3533   0.06026   0.05624  -0.0052   0.0017   1.0000
  16.000   1.3446   0.06515   0.06125  -0.0072   0.0017   1.0000
  16.250   1.3233   0.07236   0.06862  -0.0105   0.0017   1.0000
  16.500   1.3076   0.07894   0.07533  -0.0136   0.0016   1.0000
  16.750   1.2931   0.08556   0.08208  -0.0169   0.0017   1.0000
  17.000   1.2774   0.09255   0.08919  -0.0203   0.0017   1.0000
  17.250   1.2559   0.10089   0.09767  -0.0246   0.0017   1.0000
  17.500   1.2388   0.10854   0.10543  -0.0285   0.0017   1.0000
<< Back to S3014-095-85 (s3014-il)

Polar data table (+)

Polar graphs


<< Back to S3014-095-85 (s3014-il)