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S4320 (s4320-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.34 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4320-il-1000000.txt
Download as CSV file: xf-s4320-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4320                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2970   0.10313   0.10155  -0.0287   1.0000   0.0095
  -9.250  -0.2934   0.09961   0.09805  -0.0305   1.0000   0.0095
  -9.000  -0.2896   0.09612   0.09458  -0.0320   1.0000   0.0096
  -8.750  -0.2848   0.09308   0.09156  -0.0330   1.0000   0.0096
  -8.500  -0.2734   0.08873   0.08722  -0.0368   0.9792   0.0097
  -8.250  -0.2460   0.08241   0.08087  -0.0462   0.9607   0.0097
  -8.000  -0.2287   0.07578   0.07415  -0.0546   0.9291   0.0101
  -7.750  -0.2266   0.07239   0.07063  -0.0561   0.8924   0.0101
  -7.500  -0.2216   0.07096   0.06911  -0.0557   0.8691   0.0103
  -7.250  -0.2192   0.06902   0.06710  -0.0559   0.8491   0.0106
  -7.000  -0.2127   0.06640   0.06443  -0.0578   0.8325   0.0110
  -6.750  -0.2063   0.06267   0.06064  -0.0614   0.8177   0.0111
  -6.500  -0.1958   0.05875   0.05667  -0.0657   0.8047   0.0117
  -6.250  -0.1797   0.05248   0.05030  -0.0732   0.7931   0.0131
  -6.000  -0.1601   0.04643   0.04412  -0.0792   0.7828   0.0133
  -5.750  -0.1396   0.03878   0.03627  -0.0850   0.7739   0.0133
  -5.250  -0.1041   0.01870   0.01474  -0.0935   0.7587   0.0119
  -4.750  -0.0497   0.01519   0.01051  -0.0938   0.7434   0.0131
  -4.250   0.0048   0.01261   0.00748  -0.0942   0.7288   0.0151
  -3.750   0.0609   0.01143   0.00607  -0.0941   0.7146   0.0167
  -3.500   0.0889   0.01081   0.00531  -0.0940   0.7077   0.0172
  -3.250   0.1173   0.01026   0.00466  -0.0940   0.7008   0.0176
  -3.000   0.1456   0.00999   0.00430  -0.0939   0.6939   0.0181
  -2.750   0.1736   0.00912   0.00333  -0.0939   0.6873   0.0191
  -2.500   0.2019   0.00864   0.00278  -0.0939   0.6804   0.0199
  -2.250   0.2303   0.00835   0.00243  -0.0940   0.6738   0.0206
  -2.000   0.2589   0.00812   0.00215  -0.0940   0.6666   0.0213
  -1.750   0.2874   0.00794   0.00190  -0.0940   0.6600   0.0220
  -1.500   0.3160   0.00778   0.00170  -0.0940   0.6526   0.0232
  -1.250   0.3445   0.00767   0.00153  -0.0940   0.6456   0.0243
  -1.000   0.3732   0.00754   0.00135  -0.0940   0.6381   0.0265
  -0.750   0.4017   0.00745   0.00124  -0.0940   0.6310   0.0317
  -0.500   0.4302   0.00712   0.00116  -0.0942   0.6234   0.1168
  -0.250   0.4584   0.00686   0.00114  -0.0944   0.6162   0.2114
   0.000   0.4867   0.00658   0.00115  -0.0946   0.6086   0.3287
   0.250   0.5147   0.00631   0.00117  -0.0947   0.6014   0.4510
   0.500   0.5424   0.00599   0.00122  -0.0948   0.5934   0.6018
   0.750   0.5676   0.00554   0.00131  -0.0942   0.5858   0.8041
   1.000   0.5945   0.00522   0.00130  -0.0936   0.5772   1.0000
   1.250   0.6230   0.00529   0.00131  -0.0937   0.5685   1.0000
   1.500   0.6512   0.00538   0.00133  -0.0937   0.5592   1.0000
   1.750   0.6795   0.00547   0.00136  -0.0937   0.5491   1.0000
   2.000   0.7077   0.00555   0.00140  -0.0937   0.5392   1.0000
   2.250   0.7358   0.00566   0.00144  -0.0937   0.5287   1.0000
   2.500   0.7637   0.00578   0.00150  -0.0937   0.5171   1.0000
   2.750   0.7917   0.00590   0.00156  -0.0937   0.5048   1.0000
   3.000   0.8195   0.00602   0.00163  -0.0937   0.4922   1.0000
   3.250   0.8473   0.00616   0.00171  -0.0936   0.4791   1.0000
   3.500   0.8748   0.00632   0.00181  -0.0936   0.4644   1.0000
   3.750   0.9022   0.00649   0.00192  -0.0935   0.4491   1.0000
   4.000   0.9294   0.00667   0.00204  -0.0935   0.4330   1.0000
   4.500   0.9835   0.00709   0.00232  -0.0933   0.3989   1.0000
   4.750   1.0102   0.00732   0.00247  -0.0932   0.3804   1.0000
   5.000   1.0367   0.00758   0.00265  -0.0930   0.3609   1.0000
   5.250   1.0631   0.00785   0.00284  -0.0929   0.3429   1.0000
   5.500   1.0893   0.00812   0.00305  -0.0927   0.3237   1.0000
   5.750   1.1152   0.00843   0.00327  -0.0925   0.3048   1.0000
   6.000   1.1409   0.00875   0.00351  -0.0923   0.2867   1.0000
   6.250   1.1668   0.00904   0.00375  -0.0920   0.2714   1.0000
   6.500   1.1924   0.00934   0.00400  -0.0918   0.2560   1.0000
   6.750   1.2178   0.00966   0.00426  -0.0915   0.2404   1.0000
   7.000   1.2431   0.00999   0.00454  -0.0913   0.2254   1.0000
   7.250   1.2677   0.01037   0.00485  -0.0909   0.2078   1.0000
   7.500   1.2919   0.01078   0.00518  -0.0905   0.1909   1.0000
   7.750   1.3161   0.01118   0.00551  -0.0901   0.1762   1.0000
   8.250   1.3629   0.01207   0.00626  -0.0891   0.1447   1.0000
   8.500   1.3859   0.01253   0.00667  -0.0886   0.1306   1.0000
   8.750   1.4086   0.01299   0.00709  -0.0880   0.1184   1.0000
   9.000   1.4306   0.01350   0.00754  -0.0873   0.1059   1.0000
   9.250   1.4521   0.01403   0.00801  -0.0865   0.0940   1.0000
   9.500   1.4728   0.01460   0.00853  -0.0857   0.0820   1.0000
   9.750   1.4925   0.01522   0.00909  -0.0847   0.0701   1.0000
  10.000   1.5110   0.01590   0.00971  -0.0836   0.0579   1.0000
  10.250   1.5267   0.01674   0.01046  -0.0821   0.0433   1.0000
  10.500   1.5370   0.01793   0.01149  -0.0799   0.0251   1.0000
  10.750   1.5398   0.01940   0.01284  -0.0765   0.0091   1.0000
  11.000   1.5465   0.02032   0.01378  -0.0735   0.0065   1.0000
  11.250   1.5533   0.02127   0.01481  -0.0708   0.0054   1.0000
  11.500   1.5612   0.02225   0.01586  -0.0684   0.0049   1.0000
  11.750   1.5704   0.02321   0.01690  -0.0665   0.0047   1.0000
  12.000   1.5785   0.02433   0.01810  -0.0645   0.0044   1.0000
  12.250   1.5854   0.02560   0.01945  -0.0627   0.0042   1.0000
  12.500   1.5907   0.02708   0.02101  -0.0610   0.0039   1.0000
  12.750   1.5939   0.02883   0.02286  -0.0593   0.0037   1.0000
  13.000   1.5957   0.03081   0.02494  -0.0578   0.0035   1.0000
  13.250   1.5907   0.03353   0.02781  -0.0562   0.0033   1.0000
  13.500   1.5918   0.03582   0.03021  -0.0552   0.0032   1.0000
  13.750   1.5952   0.03797   0.03245  -0.0545   0.0032   1.0000
  14.000   1.5948   0.04060   0.03520  -0.0538   0.0031   1.0000
  14.250   1.5957   0.04321   0.03791  -0.0534   0.0030   1.0000
  14.500   1.5934   0.04629   0.04109  -0.0532   0.0030   1.0000
  14.750   1.5895   0.04967   0.04460  -0.0532   0.0029   1.0000
  15.000   1.5849   0.05330   0.04834  -0.0535   0.0028   1.0000
  15.250   1.5778   0.05744   0.05261  -0.0541   0.0028   1.0000
  15.500   1.5726   0.06150   0.05678  -0.0549   0.0027   1.0000
  15.750   1.5658   0.06598   0.06138  -0.0560   0.0027   1.0000
  16.000   1.5543   0.07137   0.06691  -0.0576   0.0026   1.0000
  16.250   1.5472   0.07630   0.07194  -0.0593   0.0026   1.0000
  16.500   1.5357   0.08210   0.07788  -0.0614   0.0026   1.0000
  16.750   1.5228   0.08837   0.08428  -0.0639   0.0026   1.0000
  17.000   1.5120   0.09446   0.09048  -0.0665   0.0025   1.0000
  17.250   1.4983   0.10125   0.09741  -0.0695   0.0025   1.0000
  17.500   1.4846   0.10822   0.10451  -0.0728   0.0024   1.0000
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