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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 500,000
Max Cl/Cd: 110.53 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4180-il-500000.txt
Download as CSV file: xf-s4180-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2883   0.08862   0.08646  -0.0279   1.0000   0.0239
  -8.000  -0.2844   0.08565   0.08352  -0.0292   1.0000   0.0244
  -7.500  -0.2817   0.07568   0.07365  -0.0422   0.9791   0.0261
  -7.250  -0.2614   0.07102   0.06898  -0.0467   0.9640   0.0266
  -7.000  -0.2358   0.06799   0.06592  -0.0511   0.9452   0.0272
  -6.750  -0.2199   0.06489   0.06275  -0.0547   0.9199   0.0277
  -6.500  -0.2095   0.06175   0.05951  -0.0577   0.8971   0.0286
  -6.250  -0.1983   0.05761   0.05528  -0.0622   0.8774   0.0298
  -6.000  -0.1838   0.04513   0.04246  -0.0769   0.8587   0.0321
  -5.750  -0.1665   0.04340   0.04066  -0.0772   0.8458   0.0325
  -5.500  -0.1470   0.04215   0.03933  -0.0774   0.8330   0.0333
  -5.250  -0.1251   0.03948   0.03653  -0.0791   0.8204   0.0346
  -5.000  -0.1009   0.02054   0.01588  -0.0874   0.8120   0.0256
  -4.750  -0.0749   0.01747   0.01232  -0.0878   0.8010   0.0247
  -4.500  -0.0474   0.01553   0.01001  -0.0878   0.7896   0.0245
  -4.250  -0.0196   0.01425   0.00843  -0.0877   0.7784   0.0246
  -4.000   0.0081   0.01332   0.00726  -0.0875   0.7672   0.0249
  -3.750   0.0363   0.01272   0.00649  -0.0873   0.7553   0.0256
  -3.500   0.0645   0.01224   0.00586  -0.0871   0.7435   0.0261
  -3.250   0.0923   0.01128   0.00478  -0.0870   0.7319   0.0267
  -3.000   0.1202   0.01075   0.00417  -0.0868   0.7202   0.0276
  -2.750   0.1486   0.01039   0.00376  -0.0867   0.7080   0.0287
  -2.500   0.1770   0.01009   0.00339  -0.0866   0.6958   0.0301
  -2.250   0.2054   0.00986   0.00307  -0.0865   0.6838   0.0316
  -2.000   0.2338   0.00956   0.00273  -0.0864   0.6721   0.0352
  -1.750   0.2624   0.00934   0.00248  -0.0863   0.6598   0.0418
  -1.500   0.2911   0.00908   0.00227  -0.0863   0.6478   0.0691
  -1.250   0.3195   0.00897   0.00218  -0.0863   0.6362   0.0902
  -1.000   0.3478   0.00891   0.00210  -0.0862   0.6247   0.1081
  -0.750   0.3762   0.00880   0.00204  -0.0862   0.6129   0.1352
  -0.500   0.4046   0.00864   0.00199  -0.0863   0.6016   0.1841
  -0.250   0.4329   0.00838   0.00197  -0.0864   0.5907   0.2828
   0.000   0.4609   0.00791   0.00202  -0.0867   0.5799   0.4755
   0.250   0.4863   0.00725   0.00212  -0.0862   0.5694   0.7387
   0.500   0.5081   0.00679   0.00209  -0.0841   0.5596   1.0000
   0.750   0.5366   0.00691   0.00208  -0.0840   0.5493   1.0000
   1.000   0.5651   0.00701   0.00209  -0.0840   0.5392   1.0000
   1.250   0.5935   0.00714   0.00212  -0.0840   0.5297   1.0000
   1.500   0.6219   0.00726   0.00215  -0.0839   0.5199   1.0000
   1.750   0.6502   0.00738   0.00220  -0.0839   0.5106   1.0000
   2.000   0.6783   0.00753   0.00225  -0.0838   0.5015   1.0000
   2.250   0.7067   0.00764   0.00232  -0.0838   0.4921   1.0000
   2.500   0.7347   0.00780   0.00239  -0.0837   0.4835   1.0000
   2.750   0.7629   0.00792   0.00247  -0.0837   0.4740   1.0000
   3.000   0.7909   0.00807   0.00257  -0.0836   0.4652   1.0000
   3.250   0.8188   0.00823   0.00266  -0.0835   0.4560   1.0000
   3.500   0.8468   0.00836   0.00277  -0.0835   0.4470   1.0000
   3.750   0.8743   0.00855   0.00289  -0.0834   0.4383   1.0000
   4.000   0.9024   0.00867   0.00301  -0.0833   0.4292   1.0000
   4.250   0.9299   0.00885   0.00314  -0.0832   0.4206   1.0000
   4.500   0.9575   0.00901   0.00328  -0.0831   0.4112   1.0000
   4.750   0.9851   0.00917   0.00343  -0.0830   0.4021   1.0000
   5.250   1.0397   0.00954   0.00374  -0.0828   0.3819   1.0000
   5.500   1.0668   0.00973   0.00391  -0.0827   0.3714   1.0000
   5.750   1.0936   0.00996   0.00410  -0.0825   0.3603   1.0000
   6.000   1.1205   0.01016   0.00429  -0.0824   0.3490   1.0000
   6.250   1.1473   0.01038   0.00450  -0.0822   0.3373   1.0000
   6.500   1.1737   0.01062   0.00472  -0.0820   0.3244   1.0000
   6.750   1.1998   0.01090   0.00496  -0.0818   0.3111   1.0000
   7.000   1.2257   0.01119   0.00524  -0.0816   0.2967   1.0000
   7.250   1.2512   0.01153   0.00552  -0.0813   0.2799   1.0000
   7.500   1.2760   0.01193   0.00585  -0.0809   0.2610   1.0000
   7.750   1.3001   0.01240   0.00623  -0.0805   0.2420   1.0000
   8.000   1.3241   0.01287   0.00664  -0.0801   0.2220   1.0000
   8.250   1.3470   0.01345   0.00712  -0.0796   0.2008   1.0000
   8.500   1.3694   0.01404   0.00763  -0.0790   0.1811   1.0000
   8.750   1.3915   0.01465   0.00817  -0.0783   0.1633   1.0000
   9.000   1.4130   0.01530   0.00874  -0.0776   0.1473   1.0000
   9.250   1.4339   0.01597   0.00935  -0.0769   0.1328   1.0000
   9.500   1.4542   0.01665   0.00998  -0.0760   0.1201   1.0000
   9.750   1.4741   0.01732   0.01064  -0.0751   0.1097   1.0000
  10.000   1.4929   0.01806   0.01135  -0.0741   0.1007   1.0000
  10.250   1.5110   0.01878   0.01206  -0.0730   0.0931   1.0000
  10.500   1.5286   0.01950   0.01280  -0.0718   0.0874   1.0000
  10.750   1.5448   0.02025   0.01356  -0.0704   0.0823   1.0000
  11.000   1.5572   0.02117   0.01451  -0.0686   0.0776   1.0000
  11.250   1.5709   0.02182   0.01523  -0.0668   0.0746   1.0000
  11.500   1.5799   0.02269   0.01614  -0.0645   0.0715   1.0000
  11.750   1.5838   0.02392   0.01739  -0.0619   0.0685   1.0000
  12.000   1.5897   0.02513   0.01869  -0.0597   0.0664   1.0000
  12.250   1.6000   0.02615   0.01980  -0.0583   0.0643   1.0000
  12.500   1.6084   0.02737   0.02109  -0.0568   0.0619   1.0000
  12.750   1.6126   0.02898   0.02274  -0.0554   0.0596   1.0000
  13.000   1.6091   0.03138   0.02518  -0.0538   0.0570   1.0000
  13.250   1.6189   0.03278   0.02669  -0.0530   0.0556   1.0000
  13.500   1.6265   0.03443   0.02844  -0.0523   0.0539   1.0000
  13.750   1.6319   0.03638   0.03048  -0.0518   0.0522   1.0000
  14.000   1.6340   0.03873   0.03290  -0.0513   0.0507   1.0000
  14.250   1.6320   0.04164   0.03587  -0.0510   0.0492   1.0000
  14.500   1.6239   0.04536   0.03966  -0.0509   0.0476   1.0000
  14.750   1.6279   0.04778   0.04221  -0.0509   0.0468   1.0000
  15.000   1.6323   0.05026   0.04480  -0.0511   0.0455   1.0000
  15.250   1.6342   0.05309   0.04773  -0.0515   0.0442   1.0000
  15.500   1.6340   0.05624   0.05098  -0.0519   0.0430   1.0000
  15.750   1.6316   0.05980   0.05461  -0.0527   0.0419   1.0000
  16.000   1.6261   0.06387   0.05877  -0.0536   0.0409   1.0000
  16.250   1.6164   0.06861   0.06358  -0.0549   0.0397   1.0000
  16.500   1.6132   0.07256   0.06764  -0.0560   0.0389   1.0000
  16.750   1.6138   0.07613   0.07135  -0.0571   0.0380   1.0000
  17.000   1.6124   0.08000   0.07533  -0.0584   0.0370   1.0000
  17.250   1.6100   0.08413   0.07956  -0.0599   0.0361   1.0000
  17.500   1.6066   0.08846   0.08398  -0.0615   0.0351   1.0000
  17.750   1.6010   0.09327   0.08888  -0.0635   0.0342   1.0000
  18.000   1.5928   0.09849   0.09416  -0.0656   0.0333   1.0000
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