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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 50,000
Max Cl/Cd: 36.37 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3014-il-50000-n5.txt
Download as CSV file: xf-s3014-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4267   0.09823   0.09142  -0.0236   1.0000   0.0605
  -8.750  -0.4262   0.09398   0.08724  -0.0258   1.0000   0.0580
  -8.250  -0.4447   0.08290   0.07637  -0.0363   1.0000   0.0519
  -8.000  -0.4430   0.07909   0.07262  -0.0375   1.0000   0.0512
  -7.750  -0.4425   0.07495   0.06851  -0.0394   1.0000   0.0505
  -7.500  -0.4433   0.07069   0.06426  -0.0412   1.0000   0.0498
  -7.250  -0.4448   0.06648   0.06003  -0.0426   1.0000   0.0491
  -7.000  -0.4468   0.06247   0.05597  -0.0433   1.0000   0.0485
  -6.750  -0.4497   0.05865   0.05204  -0.0431   1.0000   0.0479
  -6.500  -0.4517   0.05504   0.04828  -0.0423   1.0000   0.0474
  -6.250  -0.4522   0.05154   0.04456  -0.0411   1.0000   0.0470
  -6.000  -0.4500   0.04819   0.04093  -0.0396   1.0000   0.0468
  -5.750  -0.4448   0.04501   0.03741  -0.0381   1.0000   0.0468
  -5.500  -0.4366   0.04213   0.03415  -0.0367   1.0000   0.0477
  -5.250  -0.4257   0.03942   0.03098  -0.0352   1.0000   0.0493
  -5.000  -0.4122   0.03690   0.02794  -0.0337   1.0000   0.0509
  -4.750  -0.3964   0.03464   0.02518  -0.0323   1.0000   0.0517
  -4.500  -0.3787   0.03258   0.02267  -0.0309   1.0000   0.0522
  -4.250  -0.3602   0.03062   0.02045  -0.0296   1.0000   0.0532
  -4.000  -0.3302   0.02883   0.01839  -0.0305   0.9953   0.0549
  -3.750  -0.2963   0.02731   0.01664  -0.0318   0.9889   0.0576
  -3.500  -0.2606   0.02604   0.01510  -0.0332   0.9828   0.0614
  -3.250  -0.2274   0.02500   0.01391  -0.0344   0.9756   0.0688
  -3.000  -0.1896   0.02407   0.01286  -0.0365   0.9695   0.0825
  -2.750  -0.1567   0.02301   0.01177  -0.0376   0.9617   0.1077
  -2.500  -0.1213   0.02150   0.01113  -0.0400   0.9557   0.2509
  -2.250  -0.0987   0.02004   0.01110  -0.0394   0.9474   0.5184
  -2.000  -0.0413   0.01901   0.01107  -0.0422   0.9459   0.8928
  -1.750   0.0281   0.01905   0.01052  -0.0506   0.9429   1.0000
  -1.500   0.0615   0.01920   0.01030  -0.0521   0.9325   1.0000
  -1.250   0.0975   0.01936   0.01011  -0.0541   0.9230   1.0000
  -1.000   0.1374   0.01951   0.00996  -0.0567   0.9147   1.0000
  -0.750   0.1674   0.01968   0.00991  -0.0573   0.9034   1.0000
  -0.500   0.1980   0.01987   0.00988  -0.0581   0.8925   1.0000
  -0.250   0.2302   0.02003   0.00987  -0.0589   0.8822   1.0000
   0.000   0.2640   0.02017   0.00985  -0.0600   0.8723   1.0000
   0.250   0.2905   0.02036   0.00992  -0.0597   0.8600   1.0000
   0.500   0.3172   0.02054   0.00999  -0.0594   0.8477   1.0000
   0.750   0.3443   0.02071   0.01007  -0.0591   0.8355   1.0000
   1.000   0.3717   0.02085   0.01014  -0.0588   0.8230   1.0000
   1.250   0.3990   0.02096   0.01019  -0.0583   0.8104   1.0000
   1.500   0.4257   0.02106   0.01023  -0.0577   0.7973   1.0000
   1.750   0.4518   0.02113   0.01027  -0.0569   0.7836   1.0000
   2.000   0.4771   0.02120   0.01034  -0.0559   0.7692   1.0000
   2.250   0.5018   0.02127   0.01039  -0.0548   0.7542   1.0000
   2.500   0.5262   0.02132   0.01044  -0.0536   0.7387   1.0000
   2.750   0.5508   0.02136   0.01048  -0.0524   0.7227   1.0000
   3.000   0.5755   0.02137   0.01053  -0.0512   0.7064   1.0000
   3.250   0.6007   0.02135   0.01052  -0.0500   0.6899   1.0000
   3.500   0.6257   0.02133   0.01052  -0.0487   0.6728   1.0000
   3.750   0.6487   0.02144   0.01067  -0.0474   0.6529   1.0000
   4.000   0.6734   0.02145   0.01073  -0.0461   0.6336   1.0000
   4.250   0.6972   0.02154   0.01085  -0.0447   0.6125   1.0000
   4.500   0.7214   0.02162   0.01094  -0.0434   0.5906   1.0000
   4.750   0.7445   0.02181   0.01114  -0.0420   0.5665   1.0000
   5.000   0.7678   0.02200   0.01138  -0.0407   0.5420   1.0000
   5.250   0.7908   0.02225   0.01161  -0.0393   0.5165   1.0000
   5.500   0.8131   0.02259   0.01193  -0.0380   0.4899   1.0000
   5.750   0.8346   0.02302   0.01235  -0.0366   0.4627   1.0000
   6.000   0.8557   0.02353   0.01283  -0.0353   0.4357   1.0000
   6.250   0.8764   0.02410   0.01345  -0.0340   0.4095   1.0000
   6.500   0.8967   0.02475   0.01407  -0.0327   0.3845   1.0000
   6.750   0.9168   0.02544   0.01472  -0.0314   0.3610   1.0000
   7.000   0.9363   0.02622   0.01554  -0.0302   0.3378   1.0000
   7.250   0.9557   0.02704   0.01636  -0.0290   0.3165   1.0000
   7.500   0.9746   0.02793   0.01735  -0.0277   0.2958   1.0000
   7.750   0.9934   0.02885   0.01825  -0.0265   0.2770   1.0000
   8.000   1.0115   0.02985   0.01938  -0.0253   0.2582   1.0000
   8.250   1.0291   0.03088   0.02050  -0.0241   0.2406   1.0000
   8.500   1.0463   0.03197   0.02167  -0.0228   0.2244   1.0000
   8.750   1.0627   0.03310   0.02287  -0.0215   0.2090   1.0000
   9.000   1.0786   0.03431   0.02419  -0.0202   0.1946   1.0000
   9.250   1.0931   0.03557   0.02562  -0.0187   0.1806   1.0000
   9.500   1.1070   0.03694   0.02715  -0.0173   0.1676   1.0000
   9.750   1.1186   0.03836   0.02874  -0.0157   0.1549   1.0000
  10.000   1.1287   0.03990   0.03046  -0.0140   0.1429   1.0000
  10.250   1.1370   0.04156   0.03228  -0.0123   0.1317   1.0000
  10.500   1.1410   0.04321   0.03405  -0.0102   0.1212   1.0000
  10.750   1.1440   0.04493   0.03578  -0.0081   0.1117   1.0000
  11.000   1.1413   0.04703   0.03811  -0.0061   0.1017   1.0000
  11.250   1.1360   0.04943   0.04068  -0.0045   0.0922   1.0000
  11.500   1.1279   0.05195   0.04325  -0.0034   0.0836   1.0000
  11.750   1.1190   0.05482   0.04618  -0.0030   0.0757   1.0000
  12.000   1.1107   0.05838   0.04995  -0.0030   0.0687   1.0000
  12.250   1.1008   0.06198   0.05356  -0.0036   0.0627   1.0000
  12.500   1.0919   0.06646   0.05834  -0.0043   0.0575   1.0000
  12.750   1.0823   0.07092   0.06290  -0.0056   0.0532   1.0000
  13.000   1.0747   0.07526   0.06722  -0.0069   0.0504   1.0000
  13.250   1.0630   0.08104   0.07334  -0.0089   0.0482   1.0000
  13.500   1.0491   0.08732   0.07987  -0.0117   0.0462   1.0000
  13.750   1.0350   0.09397   0.08674  -0.0148   0.0451   1.0000
  14.000   1.0185   0.10153   0.09450  -0.0186   0.0446   1.0000
  14.250   0.9966   0.11100   0.10419  -0.0237   0.0455   1.0000
  14.500   0.9710   0.12213   0.11540  -0.0298   0.0474   1.0000
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