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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 100,000
Max Cl/Cd: 58.75 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4180-il-100000-n5.txt
Download as CSV file: xf-s4180-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4180-098-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.2838   0.09046   0.08584  -0.0308   1.0000   0.0581
  -7.500  -0.2814   0.08783   0.08329  -0.0311   1.0000   0.0585
  -7.250  -0.2843   0.08553   0.08110  -0.0309   1.0000   0.0587
  -6.750  -0.2775   0.07350   0.06911  -0.0449   0.9798   0.0379
  -6.500  -0.2523   0.06954   0.06514  -0.0494   0.9682   0.0370
  -6.250  -0.2253   0.06419   0.05973  -0.0577   0.9542   0.0364
  -6.000  -0.1968   0.05793   0.05334  -0.0673   0.9395   0.0366
  -5.750  -0.1688   0.05181   0.04702  -0.0754   0.9255   0.0366
  -5.500  -0.1424   0.04614   0.04110  -0.0814   0.9116   0.0360
  -5.250  -0.1172   0.04048   0.03508  -0.0861   0.8975   0.0352
  -5.000  -0.0914   0.03502   0.02909  -0.0897   0.8842   0.0348
  -4.750  -0.0648   0.03076   0.02425  -0.0917   0.8718   0.0348
  -4.500  -0.0375   0.02753   0.02043  -0.0928   0.8603   0.0352
  -4.250  -0.0100   0.02512   0.01747  -0.0931   0.8487   0.0364
  -4.000   0.0174   0.02320   0.01499  -0.0931   0.8361   0.0384
  -3.750   0.0440   0.02210   0.01375  -0.0929   0.8240   0.0399
  -3.500   0.0712   0.02094   0.01236  -0.0925   0.8125   0.0413
  -3.250   0.0984   0.01987   0.01105  -0.0920   0.8009   0.0432
  -3.000   0.1256   0.01892   0.00986  -0.0915   0.7884   0.0456
  -2.750   0.1523   0.01825   0.00916  -0.0911   0.7763   0.0496
  -2.500   0.1795   0.01767   0.00842  -0.0905   0.7648   0.0558
  -2.250   0.2063   0.01704   0.00779  -0.0900   0.7532   0.0631
  -2.000   0.2334   0.01655   0.00725  -0.0896   0.7407   0.0770
  -1.750   0.2605   0.01617   0.00687  -0.0892   0.7288   0.0979
  -1.500   0.2875   0.01588   0.00659  -0.0889   0.7175   0.1265
  -1.250   0.3145   0.01554   0.00627  -0.0885   0.7059   0.1546
  -1.000   0.3415   0.01522   0.00602  -0.0881   0.6938   0.1904
  -0.750   0.3684   0.01485   0.00582  -0.0878   0.6825   0.2558
  -0.500   0.3948   0.01430   0.00570  -0.0875   0.6718   0.4054
  -0.250   0.4157   0.01352   0.00573  -0.0856   0.6606   0.6678
   0.000   0.4422   0.01294   0.00552  -0.0840   0.6495   1.0000
   0.250   0.4699   0.01308   0.00540  -0.0837   0.6389   1.0000
   0.500   0.4976   0.01322   0.00534  -0.0834   0.6280   1.0000
   0.750   0.5252   0.01339   0.00533  -0.0832   0.6170   1.0000
   1.000   0.5527   0.01356   0.00531  -0.0829   0.6069   1.0000
   1.250   0.5802   0.01373   0.00533  -0.0826   0.5967   1.0000
   1.500   0.6077   0.01393   0.00540  -0.0824   0.5861   1.0000
   1.750   0.6351   0.01412   0.00545  -0.0821   0.5769   1.0000
   2.000   0.6624   0.01433   0.00556  -0.0819   0.5666   1.0000
   2.250   0.6897   0.01455   0.00568  -0.0817   0.5569   1.0000
   2.500   0.7170   0.01477   0.00578  -0.0814   0.5482   1.0000
   2.750   0.7441   0.01501   0.00598  -0.0812   0.5380   1.0000
   3.000   0.7712   0.01525   0.00612  -0.0809   0.5294   1.0000
   3.250   0.7981   0.01550   0.00634  -0.0807   0.5197   1.0000
   3.500   0.8250   0.01576   0.00655  -0.0804   0.5105   1.0000
   3.750   0.8518   0.01602   0.00674  -0.0801   0.5017   1.0000
   4.000   0.8784   0.01629   0.00703  -0.0799   0.4918   1.0000
   4.250   0.9050   0.01657   0.00725  -0.0795   0.4829   1.0000
   4.500   0.9313   0.01685   0.00753  -0.0792   0.4728   1.0000
   4.750   0.9575   0.01715   0.00785  -0.0789   0.4629   1.0000
   5.000   0.9836   0.01743   0.00807  -0.0785   0.4535   1.0000
   5.250   1.0092   0.01774   0.00843  -0.0782   0.4424   1.0000
   5.500   1.0348   0.01805   0.00876  -0.0778   0.4317   1.0000
   5.750   1.0602   0.01836   0.00907  -0.0773   0.4213   1.0000
   6.000   1.0853   0.01869   0.00943  -0.0769   0.4097   1.0000
   6.250   1.1100   0.01903   0.00982  -0.0764   0.3977   1.0000
   6.500   1.1345   0.01938   0.01023  -0.0759   0.3855   1.0000
   6.750   1.1585   0.01974   0.01061  -0.0753   0.3728   1.0000
   7.000   1.1821   0.02012   0.01101  -0.0747   0.3593   1.0000
   7.250   1.2051   0.02053   0.01147  -0.0740   0.3449   1.0000
   7.500   1.2276   0.02097   0.01196  -0.0733   0.3295   1.0000
   7.750   1.2494   0.02145   0.01248  -0.0725   0.3132   1.0000
   8.000   1.2706   0.02199   0.01305  -0.0717   0.2960   1.0000
   8.250   1.2908   0.02259   0.01368  -0.0708   0.2779   1.0000
   8.500   1.3098   0.02327   0.01436  -0.0698   0.2599   1.0000
   8.750   1.3274   0.02405   0.01511  -0.0687   0.2417   1.0000
   9.000   1.3442   0.02490   0.01596  -0.0675   0.2236   1.0000
   9.250   1.3593   0.02585   0.01692  -0.0662   0.2064   1.0000
   9.500   1.3727   0.02690   0.01796  -0.0647   0.1907   1.0000
   9.750   1.3844   0.02802   0.01909  -0.0631   0.1769   1.0000
  10.000   1.3943   0.02923   0.02030  -0.0613   0.1650   1.0000
  10.250   1.3999   0.03053   0.02159  -0.0590   0.1551   1.0000
  10.500   1.4057   0.03189   0.02302  -0.0570   0.1458   1.0000
  10.750   1.4103   0.03340   0.02458  -0.0551   0.1379   1.0000
  11.000   1.4133   0.03512   0.02634  -0.0534   0.1310   1.0000
  11.250   1.4174   0.03688   0.02818  -0.0520   0.1249   1.0000
  11.500   1.4203   0.03885   0.03021  -0.0508   0.1191   1.0000
  11.750   1.4219   0.04102   0.03241  -0.0498   0.1144   1.0000
  12.000   1.4259   0.04310   0.03465  -0.0489   0.1093   1.0000
  12.250   1.4273   0.04548   0.03709  -0.0483   0.1051   1.0000
  12.500   1.4291   0.04793   0.03957  -0.0477   0.1016   1.0000
  12.750   1.4326   0.05030   0.04211  -0.0473   0.0977   1.0000
  13.000   1.4345   0.05290   0.04482  -0.0470   0.0943   1.0000
  13.250   1.4353   0.05565   0.04759  -0.0469   0.0914   1.0000
  13.500   1.4375   0.05834   0.05039  -0.0468   0.0885   1.0000
  13.750   1.4396   0.06117   0.05342  -0.0468   0.0855   1.0000
  14.000   1.4408   0.06409   0.05647  -0.0470   0.0830   1.0000
  14.250   1.4415   0.06712   0.05958  -0.0473   0.0807   1.0000
  14.500   1.4445   0.06982   0.06226  -0.0473   0.0784   1.0000
  14.750   1.4433   0.07336   0.06604  -0.0480   0.0764   1.0000
  15.000   1.4416   0.07701   0.06991  -0.0487   0.0743   1.0000
  15.250   1.4399   0.08073   0.07379  -0.0496   0.0723   1.0000
  15.500   1.4389   0.08437   0.07756  -0.0506   0.0705   1.0000
  15.750   1.4390   0.08788   0.08114  -0.0515   0.0689   1.0000
  16.000   1.4434   0.09064   0.08391  -0.0518   0.0671   1.0000
  16.250   1.4341   0.09601   0.08958  -0.0540   0.0659   1.0000
  16.500   1.4234   0.10172   0.09555  -0.0565   0.0646   1.0000
  16.750   1.4120   0.10774   0.10181  -0.0594   0.0634   1.0000
  17.000   1.3998   0.11402   0.10831  -0.0625   0.0622   1.0000
  17.250   1.3870   0.12066   0.11514  -0.0661   0.0611   1.0000
  17.500   1.3730   0.12764   0.12229  -0.0700   0.0602   1.0000
  17.750   1.3589   0.13489   0.12970  -0.0742   0.0593   1.0000
  18.000   1.3484   0.14145   0.13639  -0.0781   0.0584   1.0000
  18.250   1.3645   0.14173   0.13660  -0.0775   0.0568   1.0000
  18.500   1.3188   0.15729   0.15244  -0.0881   0.0567   1.0000
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