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CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CLARK Z AIRFOIL (clarkz-il)
Reynolds number: 100,000
Max Cl/Cd: 54.02 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkz-il-100000.txt
Download as CSV file: xf-clarkz-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK Z AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3364   0.09620   0.09138  -0.0319   1.0000   0.1146
  -7.750  -0.3480   0.09481   0.09008  -0.0293   1.0000   0.1164
  -7.500  -0.3662   0.09376   0.08914  -0.0262   1.0000   0.1180
  -7.250  -0.3902   0.09299   0.08848  -0.0227   1.0000   0.1193
  -7.000  -0.4139   0.09179   0.08738  -0.0214   1.0000   0.1211
  -6.750  -0.4556   0.09063   0.08620  -0.0285   1.0000   0.1237
  -6.500  -0.4606   0.08666   0.08227  -0.0279   1.0000   0.1248
  -6.250  -0.4548   0.08388   0.07959  -0.0233   1.0000   0.1260
  -6.000  -0.4457   0.08148   0.07722  -0.0211   0.9988   0.1281
  -5.750  -0.4119   0.07584   0.07118  -0.0390   0.9882   0.1407
  -5.500  -0.3880   0.07195   0.06748  -0.0369   0.9845   0.1432
  -5.250  -0.3618   0.06914   0.06466  -0.0387   0.9781   0.1494
  -5.000  -0.3288   0.06417   0.05948  -0.0476   0.9707   0.1602
  -4.750  -0.3044   0.06154   0.05684  -0.0491   0.9628   0.1668
  -4.500  -0.2691   0.05754   0.05267  -0.0553   0.9566   0.1791
  -4.250  -0.2435   0.05462   0.04954  -0.0590   0.9470   0.1939
  -4.000  -0.2061   0.05167   0.04647  -0.0634   0.9416   0.2110
  -3.750  -0.1834   0.04954   0.04427  -0.0643   0.9320   0.2284
  -3.500  -0.1483   0.04701   0.04177  -0.0666   0.9266   0.2488
  -3.250  -0.0779   0.03513   0.02747  -0.0766   0.9216   0.1064
  -3.000  -0.0430   0.03274   0.02476  -0.0782   0.9140   0.1028
  -2.750   0.0042   0.03055   0.02212  -0.0816   0.9097   0.1015
  -2.500   0.0325   0.02949   0.02081  -0.0817   0.8998   0.1036
  -2.250   0.0784   0.02801   0.01901  -0.0845   0.8947   0.1053
  -2.000   0.1105   0.02708   0.01786  -0.0850   0.8857   0.1072
  -1.750   0.1538   0.02575   0.01646  -0.0874   0.8797   0.1113
  -1.500   0.2049   0.02469   0.01538  -0.0911   0.8763   0.1223
  -1.250   0.2289   0.02402   0.01484  -0.0902   0.8646   0.1310
  -1.000   0.2741   0.02282   0.01373  -0.0925   0.8604   0.1567
  -0.750   0.2973   0.02189   0.01323  -0.0915   0.8490   0.2154
  -0.500   0.3645   0.01879   0.01247  -0.0969   0.8469   1.0000
  -0.250   0.3934   0.01876   0.01221  -0.0966   0.8366   1.0000
   0.000   0.4306   0.01846   0.01170  -0.0975   0.8289   1.0000
   0.250   0.4551   0.01852   0.01161  -0.0965   0.8171   1.0000
   0.500   0.4942   0.01811   0.01103  -0.0976   0.8107   1.0000
   0.750   0.5166   0.01820   0.01101  -0.0962   0.7977   1.0000
   1.000   0.5429   0.01820   0.01090  -0.0954   0.7863   1.0000
   1.250   0.5778   0.01786   0.01043  -0.0957   0.7782   1.0000
   1.500   0.6010   0.01795   0.01045  -0.0945   0.7649   1.0000
   1.750   0.6271   0.01797   0.01038  -0.0936   0.7528   1.0000
   2.000   0.6589   0.01776   0.01006  -0.0935   0.7430   1.0000
   2.250   0.6849   0.01777   0.01000  -0.0926   0.7301   1.0000
   2.500   0.7096   0.01787   0.01003  -0.0916   0.7165   1.0000
   2.750   0.7356   0.01793   0.01003  -0.0907   0.7034   1.0000
   3.000   0.7634   0.01794   0.00995  -0.0901   0.6910   1.0000
   3.250   0.7925   0.01790   0.00981  -0.0897   0.6789   1.0000
   3.500   0.8167   0.01808   0.00995  -0.0887   0.6643   1.0000
   3.750   0.8413   0.01827   0.01010  -0.0878   0.6499   1.0000
   4.000   0.8664   0.01846   0.01024  -0.0869   0.6358   1.0000
   4.250   0.8919   0.01865   0.01039  -0.0861   0.6220   1.0000
   4.500   0.9181   0.01883   0.01050  -0.0854   0.6086   1.0000
   4.750   0.9455   0.01899   0.01057  -0.0849   0.5958   1.0000
   5.000   0.9696   0.01927   0.01083  -0.0840   0.5815   1.0000
   5.250   0.9931   0.01958   0.01114  -0.0831   0.5671   1.0000
   5.500   1.0168   0.01988   0.01141  -0.0821   0.5527   1.0000
   5.750   1.0407   0.02011   0.01162  -0.0811   0.5376   1.0000
   6.000   1.0640   0.02029   0.01174  -0.0799   0.5212   1.0000
   6.250   1.0868   0.02046   0.01185  -0.0787   0.5043   1.0000
   6.500   1.1093   0.02071   0.01206  -0.0775   0.4883   1.0000
   6.750   1.1318   0.02106   0.01240  -0.0765   0.4738   1.0000
   7.000   1.1543   0.02143   0.01275  -0.0754   0.4597   1.0000
   7.250   1.1768   0.02180   0.01311  -0.0744   0.4456   1.0000
   7.500   1.1988   0.02219   0.01348  -0.0733   0.4311   1.0000
   7.750   1.2201   0.02259   0.01385  -0.0721   0.4163   1.0000
   8.000   1.2405   0.02302   0.01426  -0.0707   0.4011   1.0000
   8.250   1.2592   0.02346   0.01473  -0.0692   0.3849   1.0000
   8.500   1.2757   0.02394   0.01525  -0.0673   0.3676   1.0000
   8.750   1.2903   0.02445   0.01581  -0.0651   0.3489   1.0000
   9.000   1.3033   0.02501   0.01640  -0.0627   0.3288   1.0000
   9.250   1.3149   0.02565   0.01698  -0.0602   0.3076   1.0000
   9.500   1.3232   0.02647   0.01777  -0.0572   0.2844   1.0000
   9.750   1.3297   0.02741   0.01862  -0.0541   0.2616   1.0000
  10.000   1.3359   0.02850   0.01954  -0.0510   0.2418   1.0000
  10.250   1.3428   0.02969   0.02066  -0.0482   0.2248   1.0000
  10.500   1.3537   0.03094   0.02179  -0.0460   0.2114   1.0000
  10.750   1.3663   0.03217   0.02301  -0.0442   0.2003   1.0000
  11.000   1.3802   0.03349   0.02437  -0.0426   0.1911   1.0000
  11.250   1.4011   0.03479   0.02551  -0.0419   0.1832   1.0000
  11.500   1.4130   0.03613   0.02705  -0.0401   0.1766   1.0000
  11.750   1.4394   0.03746   0.02826  -0.0403   0.1704   1.0000
  12.000   1.4540   0.03903   0.03004  -0.0389   0.1657   1.0000
  12.250   1.4674   0.04044   0.03158  -0.0374   0.1606   1.0000
  12.500   1.4941   0.04192   0.03293  -0.0378   0.1545   1.0000
  12.750   1.4923   0.04349   0.03482  -0.0347   0.1506   1.0000
  13.000   1.4990   0.04485   0.03627  -0.0327   0.1455   1.0000
  13.250   1.5129   0.04634   0.03771  -0.0317   0.1397   1.0000
  13.500   1.5051   0.04817   0.03983  -0.0287   0.1359   1.0000
  13.750   1.5110   0.04953   0.04121  -0.0271   0.1307   1.0000
  14.000   1.5192   0.05137   0.04310  -0.0258   0.1260   1.0000
  14.250   1.5100   0.05374   0.04578  -0.0234   0.1230   1.0000
  14.500   1.5086   0.05581   0.04799  -0.0219   0.1191   1.0000
  14.750   1.5245   0.05739   0.04946  -0.0213   0.1137   1.0000
  15.000   1.5072   0.06055   0.05298  -0.0193   0.1113   1.0000
  15.250   1.4940   0.06371   0.05639  -0.0180   0.1081   1.0000
  15.500   1.0945   0.13557   0.13005  -0.0482   0.1433   1.0000
  15.750   1.0739   0.14587   0.14035  -0.0528   0.1422   1.0000
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