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S4180-098-84 (s4180-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4180-098-84 (s4180-il)
Reynolds number: 1,000,000
Max Cl/Cd: 133.88 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4180-il-1000000.txt
Download as CSV file: xf-s4180-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3509   0.11665   0.11496  -0.0167   1.0000   0.0136
 -10.500  -0.3475   0.11261   0.11093  -0.0188   1.0000   0.0137
 -10.250  -0.3425   0.10902   0.10735  -0.0204   1.0000   0.0138
 -10.000  -0.3376   0.10539   0.10373  -0.0220   1.0000   0.0138
  -9.750  -0.3350   0.10147   0.09982  -0.0228   1.0000   0.0140
  -9.500  -0.3269   0.09903   0.09739  -0.0234   1.0000   0.0142
  -9.250  -0.3192   0.09652   0.09490  -0.0242   1.0000   0.0143
  -9.000  -0.3124   0.09384   0.09224  -0.0252   1.0000   0.0145
  -8.750  -0.3064   0.09114   0.08956  -0.0262   1.0000   0.0147
  -8.000  -0.2778   0.08101   0.07946  -0.0344   0.9715   0.0159
  -7.750  -0.2572   0.07273   0.07107  -0.0469   0.9264   0.0172
  -7.500  -0.2292   0.05693   0.05507  -0.0401   0.8337   0.0177
  -7.250  -0.2685   0.06373   0.06187  -0.0524   0.8647   0.0177
  -7.000  -0.2591   0.06087   0.05894  -0.0551   0.8473   0.0179
  -6.750  -0.2476   0.05746   0.05545  -0.0586   0.8314   0.0180
  -6.500  -0.2331   0.05436   0.05228  -0.0619   0.8169   0.0184
  -6.250  -0.2383   0.02292   0.01940  -0.0847   0.8058   0.0175
  -6.000  -0.2160   0.01879   0.01489  -0.0858   0.7954   0.0163
  -5.750  -0.1903   0.01617   0.01180  -0.0863   0.7845   0.0162
  -5.500  -0.1631   0.01453   0.00984  -0.0865   0.7737   0.0163
  -5.250  -0.1355   0.01346   0.00853  -0.0865   0.7629   0.0165
  -5.000  -0.1076   0.01269   0.00756  -0.0865   0.7515   0.0168
  -4.750  -0.0795   0.01207   0.00679  -0.0864   0.7400   0.0170
  -4.500  -0.0512   0.01157   0.00615  -0.0864   0.7287   0.0172
  -4.250  -0.0229   0.01119   0.00564  -0.0863   0.7171   0.0173
  -4.000   0.0050   0.01021   0.00452  -0.0863   0.7053   0.0176
  -3.750   0.0333   0.00962   0.00385  -0.0863   0.6937   0.0180
  -3.500   0.0618   0.00926   0.00341  -0.0863   0.6820   0.0185
  -3.250   0.0903   0.00902   0.00311  -0.0862   0.6701   0.0193
  -2.750   0.1476   0.00858   0.00254  -0.0862   0.6464   0.0207
  -2.500   0.1763   0.00842   0.00231  -0.0861   0.6348   0.0213
  -2.250   0.2051   0.00818   0.00198  -0.0861   0.6235   0.0224
  -2.000   0.2339   0.00804   0.00179  -0.0861   0.6119   0.0239
  -1.750   0.2627   0.00793   0.00164  -0.0861   0.6006   0.0257
  -1.500   0.2915   0.00780   0.00149  -0.0861   0.5897   0.0318
  -1.250   0.3201   0.00763   0.00140  -0.0861   0.5786   0.0627
  -1.000   0.3489   0.00756   0.00136  -0.0862   0.5676   0.0784
  -0.750   0.3775   0.00752   0.00132  -0.0862   0.5574   0.0938
  -0.500   0.4061   0.00748   0.00129  -0.0862   0.5468   0.1150
  -0.250   0.4349   0.00739   0.00127  -0.0863   0.5365   0.1476
   0.000   0.4635   0.00727   0.00127  -0.0864   0.5269   0.2035
   0.250   0.4921   0.00709   0.00129  -0.0866   0.5168   0.2970
   0.500   0.5208   0.00681   0.00133  -0.0868   0.5074   0.4276
   0.750   0.5490   0.00640   0.00142  -0.0871   0.4983   0.6309
   1.000   0.5746   0.00599   0.00152  -0.0865   0.4892   0.8249
   1.250   0.5981   0.00573   0.00151  -0.0850   0.4809   1.0000
   1.500   0.6267   0.00585   0.00154  -0.0850   0.4716   1.0000
   1.750   0.6554   0.00594   0.00158  -0.0850   0.4631   1.0000
   2.000   0.6838   0.00607   0.00163  -0.0850   0.4539   1.0000
   2.250   0.7124   0.00616   0.00168  -0.0850   0.4453   1.0000
   2.500   0.7407   0.00629   0.00174  -0.0850   0.4366   1.0000
   2.750   0.7692   0.00640   0.00180  -0.0850   0.4278   1.0000
   3.000   0.7975   0.00652   0.00188  -0.0850   0.4193   1.0000
   3.250   0.8257   0.00665   0.00196  -0.0850   0.4106   1.0000
   3.500   0.8540   0.00677   0.00204  -0.0850   0.4025   1.0000
   3.750   0.8820   0.00692   0.00214  -0.0850   0.3935   1.0000
   4.000   0.9102   0.00704   0.00223  -0.0849   0.3852   1.0000
   4.250   0.9381   0.00720   0.00234  -0.0849   0.3758   1.0000
   4.500   0.9661   0.00734   0.00246  -0.0849   0.3661   1.0000
   4.750   0.9939   0.00750   0.00258  -0.0848   0.3562   1.0000
   5.000   1.0214   0.00769   0.00271  -0.0848   0.3446   1.0000
   5.250   1.0489   0.00786   0.00285  -0.0847   0.3341   1.0000
   5.500   1.0764   0.00804   0.00300  -0.0846   0.3228   1.0000
   5.750   1.1036   0.00825   0.00316  -0.0845   0.3102   1.0000
   6.000   1.1307   0.00848   0.00334  -0.0844   0.2978   1.0000
   6.250   1.1575   0.00873   0.00354  -0.0843   0.2842   1.0000
   6.500   1.1840   0.00902   0.00376  -0.0842   0.2682   1.0000
   6.750   1.2101   0.00934   0.00400  -0.0840   0.2504   1.0000
   7.000   1.2359   0.00969   0.00428  -0.0837   0.2324   1.0000
   7.250   1.2612   0.01010   0.00459  -0.0835   0.2138   1.0000
   7.500   1.2863   0.01051   0.00491  -0.0832   0.1947   1.0000
   7.750   1.3109   0.01097   0.00527  -0.0828   0.1758   1.0000
   8.000   1.3353   0.01143   0.00565  -0.0825   0.1597   1.0000
   8.250   1.3596   0.01189   0.00603  -0.0821   0.1451   1.0000
   8.500   1.3836   0.01236   0.00644  -0.0817   0.1311   1.0000
   8.750   1.4073   0.01284   0.00686  -0.0812   0.1187   1.0000
   9.000   1.4310   0.01330   0.00728  -0.0807   0.1082   1.0000
   9.250   1.4541   0.01378   0.00772  -0.0802   0.0983   1.0000
   9.500   1.4767   0.01431   0.00820  -0.0796   0.0894   1.0000
   9.750   1.4992   0.01480   0.00867  -0.0790   0.0825   1.0000
  10.000   1.5216   0.01529   0.00915  -0.0784   0.0764   1.0000
  10.250   1.5433   0.01580   0.00965  -0.0777   0.0715   1.0000
  10.500   1.5642   0.01636   0.01022  -0.0769   0.0667   1.0000
  10.750   1.5858   0.01680   0.01069  -0.0762   0.0637   1.0000
  11.000   1.6050   0.01742   0.01128  -0.0752   0.0593   1.0000
  11.250   1.6242   0.01799   0.01188  -0.0741   0.0562   1.0000
  11.500   1.6439   0.01847   0.01241  -0.0732   0.0540   1.0000
  11.750   1.6613   0.01909   0.01304  -0.0720   0.0516   1.0000
  12.000   1.6754   0.01983   0.01379  -0.0703   0.0488   1.0000
  12.250   1.6867   0.02049   0.01450  -0.0681   0.0470   1.0000
  12.500   1.6991   0.02107   0.01515  -0.0661   0.0459   1.0000
  12.750   1.7094   0.02181   0.01593  -0.0641   0.0441   1.0000
  13.000   1.7175   0.02275   0.01690  -0.0620   0.0423   1.0000
  13.250   1.7231   0.02395   0.01813  -0.0599   0.0401   1.0000
  13.500   1.7308   0.02509   0.01935  -0.0583   0.0389   1.0000
  13.750   1.7409   0.02616   0.02049  -0.0570   0.0379   1.0000
  14.000   1.7489   0.02745   0.02184  -0.0557   0.0366   1.0000
  14.250   1.7549   0.02899   0.02343  -0.0546   0.0354   1.0000
  14.500   1.7589   0.03080   0.02528  -0.0535   0.0340   1.0000
  14.750   1.7594   0.03302   0.02756  -0.0525   0.0324   1.0000
  15.000   1.7658   0.03479   0.02942  -0.0519   0.0317   1.0000
  15.250   1.7708   0.03678   0.03149  -0.0514   0.0308   1.0000
  15.500   1.7738   0.03905   0.03384  -0.0510   0.0298   1.0000
  15.750   1.7743   0.04168   0.03652  -0.0508   0.0286   1.0000
  16.000   1.7726   0.04467   0.03957  -0.0508   0.0275   1.0000
  16.250   1.7681   0.04811   0.04309  -0.0511   0.0264   1.0000
  16.500   1.7689   0.05099   0.04606  -0.0513   0.0258   1.0000
  16.750   1.7681   0.05419   0.04936  -0.0518   0.0251   1.0000
  17.000   1.7651   0.05776   0.05303  -0.0525   0.0242   1.0000
  17.250   1.7606   0.06167   0.05702  -0.0535   0.0234   1.0000
  17.500   1.7540   0.06598   0.06140  -0.0546   0.0226   1.0000
  17.750   1.7447   0.07083   0.06633  -0.0561   0.0215   1.0000
  18.000   1.7391   0.07520   0.07081  -0.0575   0.0209   1.0000
  18.250   1.7333   0.07973   0.07543  -0.0591   0.0203   1.0000
  18.500   1.7255   0.08461   0.08041  -0.0609   0.0193   1.0000
  18.750   1.7156   0.08995   0.08584  -0.0629   0.0185   1.0000
  19.000   1.7030   0.09590   0.09187  -0.0654   0.0176   1.0000
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