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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 200,000
Max Cl/Cd: 78.75 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4180-il-200000.txt
Download as CSV file: xf-s4180-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3046   0.10061   0.09718  -0.0286   1.0000   0.0458
  -8.500  -0.3087   0.09817   0.09481  -0.0327   1.0000   0.0462
  -8.250  -0.3054   0.09367   0.09037  -0.0336   1.0000   0.0466
  -8.000  -0.2896   0.09011   0.08681  -0.0312   1.0000   0.0474
  -7.750  -0.2800   0.08745   0.08419  -0.0305   1.0000   0.0483
  -7.500  -0.2745   0.08505   0.08184  -0.0305   1.0000   0.0493
  -7.250  -0.2745   0.08301   0.07989  -0.0300   1.0000   0.0509
  -7.000  -0.2910   0.08219   0.07921  -0.0269   1.0000   0.0514
  -6.750  -0.2820   0.07900   0.07605  -0.0321   0.9917   0.0536
  -6.500  -0.2386   0.06902   0.06597  -0.0590   0.9767   0.0568
  -6.250  -0.2138   0.06600   0.06298  -0.0584   0.9721   0.0580
  -6.000  -0.1853   0.06261   0.05957  -0.0621   0.9626   0.0598
  -5.750  -0.1526   0.05817   0.05505  -0.0698   0.9512   0.0630
  -5.500  -0.1147   0.04945   0.04592  -0.0866   0.9337   0.0688
  -5.250  -0.0954   0.04705   0.04355  -0.0862   0.9210   0.0700
  -5.000  -0.0763   0.04486   0.04132  -0.0862   0.9072   0.0720
  -4.750  -0.0467   0.04074   0.03645  -0.0923   0.8917   0.0812
  -4.500  -0.0299   0.03736   0.03317  -0.0916   0.8797   0.0827
  -4.250  -0.0105   0.03571   0.03153  -0.0907   0.8660   0.0854
  -4.000   0.0239   0.02564   0.02021  -0.0942   0.8549   0.0535
  -3.750   0.0531   0.02125   0.01479  -0.0941   0.8441   0.0460
  -3.500   0.0793   0.01927   0.01244  -0.0935   0.8326   0.0458
  -3.250   0.1063   0.01793   0.01078  -0.0930   0.8198   0.0462
  -3.000   0.1328   0.01634   0.00899  -0.0925   0.8078   0.0476
  -2.750   0.1593   0.01572   0.00830  -0.0919   0.7960   0.0508
  -2.500   0.1864   0.01505   0.00747  -0.0912   0.7844   0.0540
  -2.250   0.2137   0.01418   0.00651  -0.0907   0.7716   0.0574
  -2.000   0.2410   0.01361   0.00592  -0.0902   0.7591   0.0646
  -1.750   0.2685   0.01301   0.00532  -0.0898   0.7473   0.0829
  -1.500   0.2959   0.01258   0.00491  -0.0894   0.7360   0.1137
  -1.250   0.3236   0.01234   0.00467  -0.0892   0.7230   0.1412
  -1.000   0.3511   0.01204   0.00451  -0.0890   0.7104   0.1811
  -0.750   0.3786   0.01155   0.00431  -0.0890   0.6986   0.2618
  -0.500   0.4027   0.01047   0.00431  -0.0884   0.6877   0.5903
  -0.250   0.4234   0.00957   0.00418  -0.0854   0.6759   1.0000
   0.000   0.4516   0.00969   0.00409  -0.0852   0.6638   1.0000
   0.250   0.4796   0.00983   0.00402  -0.0850   0.6525   1.0000
   0.500   0.5076   0.00998   0.00396  -0.0847   0.6419   1.0000
   0.750   0.5356   0.01011   0.00397  -0.0846   0.6299   1.0000
   1.000   0.5636   0.01027   0.00399  -0.0844   0.6189   1.0000
   1.250   0.5915   0.01044   0.00400  -0.0842   0.6090   1.0000
   1.500   0.6194   0.01060   0.00406  -0.0840   0.5979   1.0000
   1.750   0.6472   0.01078   0.00414  -0.0839   0.5875   1.0000
   2.000   0.6750   0.01098   0.00419  -0.0837   0.5784   1.0000
   2.250   0.7028   0.01114   0.00431  -0.0836   0.5676   1.0000
   2.500   0.7305   0.01135   0.00443  -0.0834   0.5581   1.0000
   2.750   0.7581   0.01155   0.00453  -0.0832   0.5488   1.0000
   3.000   0.7857   0.01174   0.00470  -0.0831   0.5387   1.0000
   3.250   0.8132   0.01197   0.00483  -0.0829   0.5298   1.0000
   3.500   0.8406   0.01216   0.00499  -0.0827   0.5198   1.0000
   3.750   0.8679   0.01238   0.00517  -0.0825   0.5102   1.0000
   4.000   0.8952   0.01261   0.00532  -0.0823   0.5012   1.0000
   4.250   0.9222   0.01280   0.00553  -0.0821   0.4907   1.0000
   4.500   0.9492   0.01304   0.00572  -0.0818   0.4813   1.0000
   4.750   0.9761   0.01325   0.00591  -0.0816   0.4715   1.0000
   5.000   1.0028   0.01347   0.00615  -0.0813   0.4611   1.0000
   5.250   1.0295   0.01372   0.00635  -0.0811   0.4516   1.0000
   5.500   1.0558   0.01393   0.00658  -0.0807   0.4409   1.0000
   5.750   1.0820   0.01416   0.00683  -0.0804   0.4298   1.0000
   6.000   1.1080   0.01441   0.00706  -0.0801   0.4190   1.0000
   6.250   1.1339   0.01466   0.00728  -0.0797   0.4078   1.0000
   6.500   1.1593   0.01487   0.00756  -0.0793   0.3951   1.0000
   6.750   1.1845   0.01511   0.00784  -0.0789   0.3822   1.0000
   7.000   1.2094   0.01538   0.00812  -0.0785   0.3690   1.0000
   7.250   1.2340   0.01567   0.00844  -0.0780   0.3552   1.0000
   7.500   1.2581   0.01598   0.00877  -0.0774   0.3406   1.0000
   7.750   1.2817   0.01632   0.00913  -0.0768   0.3243   1.0000
   8.000   1.3046   0.01671   0.00953  -0.0762   0.3068   1.0000
   8.250   1.3267   0.01719   0.00997  -0.0755   0.2883   1.0000
   8.500   1.3479   0.01772   0.01050  -0.0746   0.2675   1.0000
   8.750   1.3675   0.01839   0.01110  -0.0737   0.2452   1.0000
   9.000   1.3859   0.01917   0.01182  -0.0726   0.2229   1.0000
   9.250   1.4025   0.02008   0.01265  -0.0713   0.2020   1.0000
   9.500   1.4171   0.02112   0.01358  -0.0698   0.1836   1.0000
   9.750   1.4312   0.02216   0.01458  -0.0683   0.1670   1.0000
  10.000   1.4431   0.02329   0.01568  -0.0665   0.1536   1.0000
  10.500   1.4627   0.02558   0.01796  -0.0625   0.1334   1.0000
  10.750   1.4682   0.02689   0.01925  -0.0600   0.1263   1.0000
  11.000   1.4752   0.02813   0.02054  -0.0579   0.1195   1.0000
  11.250   1.4800   0.02970   0.02209  -0.0559   0.1141   1.0000
  11.500   1.4880   0.03104   0.02356  -0.0543   0.1089   1.0000
  11.750   1.4929   0.03274   0.02523  -0.0528   0.1045   1.0000
  12.000   1.4998   0.03442   0.02699  -0.0514   0.1004   1.0000
  12.250   1.5068   0.03604   0.02873  -0.0502   0.0965   1.0000
  12.500   1.5128   0.03785   0.03057  -0.0492   0.0931   1.0000
  12.750   1.5207   0.03979   0.03248  -0.0480   0.0897   1.0000
  13.000   1.5264   0.04168   0.03457  -0.0472   0.0869   1.0000
  13.250   1.5320   0.04366   0.03666  -0.0465   0.0841   1.0000
  13.500   1.5375   0.04569   0.03874  -0.0458   0.0814   1.0000
  13.750   1.5504   0.04758   0.04055  -0.0448   0.0783   1.0000
  14.000   1.5529   0.04994   0.04315  -0.0444   0.0767   1.0000
  14.250   1.5558   0.05242   0.04582  -0.0441   0.0747   1.0000
  14.500   1.5592   0.05490   0.04845  -0.0438   0.0726   1.0000
  14.750   1.5635   0.05730   0.05092  -0.0437   0.0707   1.0000
  15.000   1.5711   0.05953   0.05315  -0.0433   0.0686   1.0000
  15.250   1.5774   0.06231   0.05606  -0.0428   0.0666   1.0000
  15.500   1.5741   0.06568   0.05966  -0.0432   0.0656   1.0000
  15.750   1.5707   0.06922   0.06342  -0.0437   0.0643   1.0000
  16.000   1.5658   0.07299   0.06739  -0.0444   0.0629   1.0000
  16.250   1.5620   0.07674   0.07130  -0.0454   0.0616   1.0000
  16.500   1.5600   0.08024   0.07490  -0.0463   0.0601   1.0000
  16.750   1.5632   0.08312   0.07781  -0.0469   0.0585   1.0000
  17.000   1.5613   0.08720   0.08198  -0.0474   0.0567   1.0000
  17.250   1.5468   0.09282   0.08786  -0.0500   0.0561   1.0000
  17.500   1.5315   0.09886   0.09414  -0.0529   0.0554   1.0000
  17.750   1.5150   0.10540   0.10092  -0.0562   0.0547   1.0000
  18.000   1.4972   0.11244   0.10820  -0.0601   0.0540   1.0000
  18.250   1.4774   0.12021   0.11620  -0.0646   0.0534   1.0000
  18.500   1.4516   0.12945   0.12568  -0.0702   0.0532   1.0000
  18.750   1.4014   0.14476   0.14130  -0.0802   0.0543   1.0000
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