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S4061-096-84 (s4061-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S4061-096-84 (s4061-il)
Reynolds number: 200,000
Max Cl/Cd: 81.21 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4061-il-200000-n5.txt
Download as CSV file: xf-s4061-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4061-096-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3427   0.09016   0.08673  -0.0368   1.0000   0.0150
  -8.750  -0.3365   0.08774   0.08434  -0.0376   1.0000   0.0147
  -8.500  -0.3355   0.08419   0.08086  -0.0391   1.0000   0.0146
  -8.250  -0.3317   0.08065   0.07737  -0.0414   0.9916   0.0143
  -8.000  -0.3184   0.07534   0.07206  -0.0480   0.9683   0.0141
  -7.750  -0.3083   0.06942   0.06614  -0.0553   0.9489   0.0140
  -7.500  -0.3000   0.06374   0.06043  -0.0625   0.9315   0.0136
  -7.250  -0.2951   0.05639   0.05302  -0.0712   0.9150   0.0133
  -7.000  -0.3051   0.03819   0.03427  -0.0859   0.8971   0.0124
  -6.750  -0.2976   0.03018   0.02538  -0.0893   0.8868   0.0124
  -6.500  -0.2777   0.02757   0.02236  -0.0899   0.8782   0.0130
  -6.250  -0.2568   0.02498   0.01926  -0.0900   0.8714   0.0138
  -6.000  -0.2338   0.02262   0.01638  -0.0900   0.8637   0.0143
  -5.750  -0.2099   0.02073   0.01405  -0.0896   0.8573   0.0146
  -5.500  -0.1847   0.01926   0.01225  -0.0893   0.8504   0.0148
  -5.250  -0.1592   0.01809   0.01080  -0.0888   0.8438   0.0151
  -5.000  -0.1340   0.01696   0.00955  -0.0885   0.8377   0.0157
  -4.750  -0.1080   0.01615   0.00864  -0.0883   0.8307   0.0164
  -4.250  -0.0549   0.01485   0.00706  -0.0877   0.8180   0.0188
  -4.000  -0.0283   0.01431   0.00644  -0.0875   0.8120   0.0213
  -3.750  -0.0010   0.01384   0.00586  -0.0873   0.8055   0.0244
  -3.500   0.0262   0.01330   0.00526  -0.0871   0.7989   0.0302
  -3.250   0.0533   0.01279   0.00476  -0.0869   0.7931   0.0477
  -3.000   0.0806   0.01243   0.00447  -0.0868   0.7860   0.0748
  -2.750   0.1076   0.01210   0.00425  -0.0867   0.7803   0.1117
  -2.500   0.1351   0.01185   0.00406  -0.0866   0.7730   0.1444
  -2.250   0.1624   0.01162   0.00385  -0.0865   0.7668   0.1724
  -2.000   0.1899   0.01142   0.00369  -0.0864   0.7599   0.2043
  -1.750   0.2173   0.01121   0.00354  -0.0863   0.7532   0.2427
  -1.500   0.2446   0.01100   0.00343  -0.0862   0.7467   0.2890
  -1.250   0.2719   0.01078   0.00334  -0.0861   0.7395   0.3439
  -1.000   0.2988   0.01056   0.00325  -0.0859   0.7332   0.4079
  -0.750   0.3254   0.01030   0.00323  -0.0856   0.7257   0.4855
  -0.500   0.3510   0.01001   0.00318  -0.0850   0.7195   0.5826
  -0.250   0.3745   0.00964   0.00321  -0.0838   0.7117   0.7069
   0.250   0.4383   0.00915   0.00304  -0.0844   0.6973   1.0000
   0.500   0.4658   0.00922   0.00299  -0.0842   0.6904   1.0000
   0.750   0.4934   0.00930   0.00300  -0.0841   0.6820   1.0000
   1.250   0.5485   0.00948   0.00301  -0.0838   0.6660   1.0000
   1.500   0.5759   0.00957   0.00302  -0.0837   0.6580   1.0000
   1.750   0.6033   0.00967   0.00306  -0.0835   0.6486   1.0000
   2.000   0.6306   0.00977   0.00311  -0.0833   0.6388   1.0000
   2.250   0.6577   0.00988   0.00315  -0.0831   0.6286   1.0000
   2.500   0.6848   0.00999   0.00321  -0.0829   0.6174   1.0000
   2.750   0.7119   0.01011   0.00330  -0.0827   0.6061   1.0000
   3.000   0.7389   0.01024   0.00339  -0.0825   0.5949   1.0000
   3.250   0.7658   0.01038   0.00350  -0.0822   0.5833   1.0000
   3.750   0.8191   0.01069   0.00375  -0.0817   0.5577   1.0000
   4.000   0.8456   0.01086   0.00391  -0.0815   0.5441   1.0000
   4.250   0.8720   0.01105   0.00408  -0.0812   0.5297   1.0000
   4.500   0.8980   0.01125   0.00426  -0.0808   0.5144   1.0000
   4.750   0.9238   0.01148   0.00447  -0.0805   0.4979   1.0000
   5.000   0.9493   0.01173   0.00469  -0.0801   0.4798   1.0000
   5.250   0.9745   0.01200   0.00494  -0.0796   0.4599   1.0000
   5.500   0.9990   0.01232   0.00520  -0.0791   0.4387   1.0000
   5.750   1.0233   0.01266   0.00552  -0.0786   0.4154   1.0000
   6.000   1.0468   0.01306   0.00585  -0.0780   0.3907   1.0000
   6.250   1.0696   0.01352   0.00623  -0.0773   0.3636   1.0000
   6.500   1.0916   0.01404   0.00667  -0.0765   0.3348   1.0000
   6.750   1.1129   0.01461   0.00715  -0.0757   0.3051   1.0000
   7.000   1.1332   0.01526   0.00768  -0.0747   0.2747   1.0000
   7.250   1.1530   0.01594   0.00826  -0.0737   0.2470   1.0000
   7.500   1.1729   0.01661   0.00888  -0.0728   0.2228   1.0000
   7.750   1.1924   0.01728   0.00950  -0.0718   0.2021   1.0000
   8.000   1.2112   0.01799   0.01016  -0.0707   0.1809   1.0000
   8.250   1.2289   0.01876   0.01087  -0.0695   0.1602   1.0000
   8.500   1.2452   0.01960   0.01162  -0.0682   0.1374   1.0000
   8.750   1.2603   0.02050   0.01244  -0.0667   0.1145   1.0000
   9.000   1.2739   0.02147   0.01331  -0.0651   0.0949   1.0000
   9.250   1.2868   0.02239   0.01418  -0.0633   0.0788   1.0000
   9.500   1.2979   0.02331   0.01510  -0.0613   0.0674   1.0000
   9.750   1.3081   0.02432   0.01611  -0.0592   0.0574   1.0000
  10.000   1.3175   0.02543   0.01724  -0.0573   0.0483   1.0000
  10.250   1.3257   0.02667   0.01849  -0.0553   0.0405   1.0000
  10.500   1.3329   0.02804   0.01988  -0.0535   0.0330   1.0000
  10.750   1.3401   0.02948   0.02138  -0.0517   0.0275   1.0000
  11.000   1.3457   0.03110   0.02306  -0.0500   0.0238   1.0000
  11.250   1.3515   0.03275   0.02479  -0.0485   0.0210   1.0000
  11.500   1.3551   0.03466   0.02677  -0.0471   0.0195   1.0000
  11.750   1.3600   0.03652   0.02877  -0.0458   0.0183   1.0000
  12.000   1.3637   0.03856   0.03097  -0.0447   0.0174   1.0000
  12.250   1.3662   0.04078   0.03331  -0.0437   0.0166   1.0000
  12.500   1.3679   0.04318   0.03582  -0.0429   0.0160   1.0000
  12.750   1.3668   0.04595   0.03870  -0.0423   0.0155   1.0000
  13.000   1.3641   0.04899   0.04186  -0.0418   0.0152   1.0000
  13.250   1.3637   0.05190   0.04492  -0.0415   0.0148   1.0000
  13.500   1.3628   0.05497   0.04815  -0.0414   0.0145   1.0000
  13.750   1.3612   0.05819   0.05152  -0.0415   0.0141   1.0000
  14.000   1.3595   0.06156   0.05504  -0.0418   0.0137   1.0000
  14.250   1.3573   0.06513   0.05875  -0.0422   0.0134   1.0000
  14.500   1.3546   0.06890   0.06268  -0.0430   0.0130   1.0000
  14.750   1.3514   0.07285   0.06675  -0.0439   0.0126   1.0000
  15.000   1.3472   0.07706   0.07110  -0.0450   0.0125   1.0000
  15.250   1.3425   0.08152   0.07568  -0.0464   0.0122   1.0000
  15.500   1.3375   0.08609   0.08039  -0.0479   0.0120   1.0000
  15.750   1.3322   0.09082   0.08524  -0.0495   0.0119   1.0000
  16.000   1.3263   0.09571   0.09025  -0.0512   0.0117   1.0000
  16.250   1.3205   0.10070   0.09536  -0.0531   0.0116   1.0000
  16.500   1.3150   0.10584   0.10066  -0.0552   0.0115   1.0000
  16.750   1.3088   0.11125   0.10624  -0.0576   0.0114   1.0000
  17.000   1.3022   0.11688   0.11205  -0.0603   0.0113   1.0000
  17.250   1.2947   0.12282   0.11817  -0.0634   0.0112   1.0000
  17.500   1.2866   0.12899   0.12452  -0.0666   0.0112   1.0000
  17.750   1.2776   0.13560   0.13130  -0.0704   0.0111   1.0000
  18.000   1.2679   0.14252   0.13840  -0.0745   0.0111   1.0000
  18.250   1.2572   0.14993   0.14599  -0.0790   0.0110   1.0000
  18.500   1.2457   0.15779   0.15401  -0.0840   0.0110   1.0000
  18.750   1.2327   0.16632   0.16272  -0.0895   0.0110   1.0000
  19.000   1.2182   0.17569   0.17224  -0.0957   0.0111   1.0000
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