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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 50,000
Max Cl/Cd: 36.35 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkk-il-50000-n5.txt
Download as CSV file: xf-clarkk-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK K AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3918   0.11491   0.10738  -0.0335   1.0000   0.1838
  -9.500  -0.4024   0.11242   0.10499  -0.0352   1.0000   0.1843
  -9.250  -0.4210   0.09819   0.09074  -0.0441   1.0000   0.1096
  -9.000  -0.4071   0.09530   0.08783  -0.0422   1.0000   0.1075
  -8.750  -0.4107   0.09206   0.08466  -0.0421   1.0000   0.1061
  -8.500  -0.4207   0.08890   0.08160  -0.0419   1.0000   0.1051
  -8.250  -0.4360   0.08579   0.07861  -0.0414   1.0000   0.1041
  -8.000  -0.4514   0.08209   0.07501  -0.0419   1.0000   0.1029
  -7.500  -0.5154   0.06827   0.06095  -0.0477   1.0000   0.0964
  -7.250  -0.5171   0.06500   0.05761  -0.0466   1.0000   0.0959
  -7.000  -0.5174   0.06167   0.05416  -0.0457   1.0000   0.0954
  -6.750  -0.5163   0.05819   0.05049  -0.0451   1.0000   0.0950
  -6.500  -0.5140   0.05442   0.04639  -0.0449   1.0000   0.0952
  -6.250  -0.5085   0.05075   0.04225  -0.0448   1.0000   0.0959
  -6.000  -0.4981   0.04772   0.03881  -0.0444   1.0000   0.0963
  -5.750  -0.4804   0.04495   0.03566  -0.0448   0.9986   0.0962
  -5.500  -0.4486   0.04207   0.03230  -0.0475   0.9932   0.0962
  -5.250  -0.4165   0.03963   0.02938  -0.0499   0.9874   0.0964
  -5.000  -0.3841   0.03765   0.02719  -0.0521   0.9819   0.0980
  -4.750  -0.3509   0.03609   0.02542  -0.0542   0.9759   0.0999
  -4.500  -0.3177   0.03459   0.02360  -0.0560   0.9698   0.1009
  -4.250  -0.2823   0.03322   0.02191  -0.0580   0.9639   0.1013
  -4.000  -0.2495   0.03210   0.02053  -0.0594   0.9572   0.1018
  -3.750  -0.2132   0.03112   0.01932  -0.0613   0.9514   0.1026
  -3.500  -0.1816   0.03032   0.01836  -0.0623   0.9439   0.1035
  -3.250  -0.1448   0.02963   0.01751  -0.0642   0.9381   0.1059
  -3.000  -0.1145   0.02910   0.01681  -0.0648   0.9300   0.1085
  -2.750  -0.0773   0.02853   0.01616  -0.0667   0.9241   0.1108
  -2.500  -0.0479   0.02809   0.01567  -0.0672   0.9156   0.1125
  -2.250  -0.0110   0.02767   0.01519  -0.0690   0.9093   0.1146
  -2.000   0.0181   0.02739   0.01484  -0.0695   0.9006   0.1170
  -1.750   0.0546   0.02708   0.01446  -0.0712   0.8939   0.1205
  -1.500   0.0841   0.02687   0.01424  -0.0716   0.8850   0.1245
  -1.250   0.1196   0.02656   0.01400  -0.0732   0.8779   0.1328
  -0.750   0.1833   0.02592   0.01381  -0.0751   0.8616   0.2156
  -0.500   0.2123   0.02531   0.01382  -0.0757   0.8533   0.3417
  -0.250   0.2391   0.02454   0.01386  -0.0754   0.8451   0.5193
   0.000   0.2658   0.02384   0.01402  -0.0737   0.8375   0.7735
   0.250   0.3171   0.02371   0.01392  -0.0777   0.8290   1.0000
   0.500   0.3465   0.02384   0.01387  -0.0779   0.8197   1.0000
   0.750   0.3771   0.02392   0.01381  -0.0782   0.8105   1.0000
   1.000   0.4023   0.02413   0.01389  -0.0776   0.7994   1.0000
   1.250   0.4375   0.02407   0.01370  -0.0785   0.7919   1.0000
   1.500   0.4601   0.02432   0.01387  -0.0775   0.7795   1.0000
   1.750   0.4877   0.02444   0.01390  -0.0772   0.7689   1.0000
   2.000   0.5200   0.02438   0.01376  -0.0774   0.7597   1.0000
   2.250   0.5435   0.02459   0.01392  -0.0765   0.7469   1.0000
   2.500   0.5703   0.02468   0.01395  -0.0759   0.7352   1.0000
   2.750   0.6042   0.02447   0.01370  -0.0761   0.7257   1.0000
   3.000   0.6275   0.02463   0.01383  -0.0750   0.7115   1.0000
   3.250   0.6522   0.02473   0.01392  -0.0740   0.6975   1.0000
   3.500   0.6779   0.02478   0.01396  -0.0731   0.6836   1.0000
   3.750   0.7046   0.02478   0.01395  -0.0723   0.6698   1.0000
   4.000   0.7319   0.02476   0.01393  -0.0716   0.6560   1.0000
   4.250   0.7596   0.02473   0.01389  -0.0709   0.6421   1.0000
   4.500   0.7843   0.02485   0.01402  -0.0699   0.6269   1.0000
   4.750   0.8082   0.02501   0.01422  -0.0688   0.6111   1.0000
   5.000   0.8323   0.02518   0.01441  -0.0677   0.5949   1.0000
   5.250   0.8565   0.02536   0.01461  -0.0666   0.5785   1.0000
   5.500   0.8807   0.02555   0.01484  -0.0656   0.5617   1.0000
   5.750   0.9048   0.02577   0.01507  -0.0645   0.5445   1.0000
   6.000   0.9277   0.02608   0.01540  -0.0633   0.5267   1.0000
   6.250   0.9495   0.02648   0.01585  -0.0621   0.5084   1.0000
   6.500   0.9710   0.02691   0.01631  -0.0608   0.4899   1.0000
   6.750   0.9925   0.02739   0.01682  -0.0596   0.4719   1.0000
   7.000   1.0138   0.02791   0.01740  -0.0584   0.4543   1.0000
   7.250   1.0349   0.02847   0.01800  -0.0571   0.4371   1.0000
   7.500   1.0558   0.02909   0.01867  -0.0560   0.4208   1.0000
   7.750   1.0765   0.02976   0.01941  -0.0548   0.4053   1.0000
   8.000   1.0971   0.03046   0.02017  -0.0536   0.3906   1.0000
   8.250   1.1183   0.03119   0.02095  -0.0526   0.3770   1.0000
   8.500   1.1396   0.03192   0.02176  -0.0515   0.3639   1.0000
   8.750   1.1570   0.03285   0.02283  -0.0501   0.3506   1.0000
   9.000   1.1737   0.03376   0.02387  -0.0486   0.3371   1.0000
   9.250   1.1864   0.03458   0.02476  -0.0464   0.3212   1.0000
   9.500   1.1939   0.03538   0.02557  -0.0437   0.3030   1.0000
   9.750   1.1957   0.03623   0.02638  -0.0403   0.2837   1.0000
  10.000   1.1927   0.03741   0.02757  -0.0367   0.2647   1.0000
  10.250   1.1903   0.03882   0.02903  -0.0337   0.2459   1.0000
  10.500   1.1895   0.04039   0.03068  -0.0312   0.2282   1.0000
  10.750   1.1899   0.04212   0.03251  -0.0291   0.2116   1.0000
  11.000   1.1886   0.04413   0.03462  -0.0273   0.1936   1.0000
  11.250   1.1848   0.04649   0.03704  -0.0257   0.1737   1.0000
  11.500   1.1799   0.04925   0.03989  -0.0245   0.1509   1.0000
  11.750   1.1720   0.05250   0.04306  -0.0236   0.1294   1.0000
  12.000   1.1635   0.05610   0.04659  -0.0230   0.1109   1.0000
  12.250   1.1543   0.05997   0.05037  -0.0226   0.0984   1.0000
  12.500   1.1448   0.06405   0.05438  -0.0226   0.0901   1.0000
  12.750   1.1385   0.06792   0.05830  -0.0225   0.0830   1.0000
  13.000   1.1308   0.07201   0.06238  -0.0227   0.0783   1.0000
  13.250   1.1258   0.07589   0.06633  -0.0229   0.0738   1.0000
  13.500   1.1217   0.07975   0.07029  -0.0232   0.0698   1.0000
  13.750   1.1174   0.08363   0.07420  -0.0236   0.0667   1.0000
  14.000   1.1153   0.08730   0.07793  -0.0239   0.0641   1.0000
  14.250   1.1143   0.09099   0.08183  -0.0242   0.0616   1.0000
  14.500   1.1128   0.09479   0.08579  -0.0248   0.0592   1.0000
  14.750   1.1119   0.09845   0.08951  -0.0253   0.0571   1.0000
  15.000   1.1132   0.10164   0.09266  -0.0256   0.0552   1.0000
  15.250   1.1087   0.10643   0.09774  -0.0270   0.0538   1.0000
  15.500   1.1031   0.11154   0.10311  -0.0288   0.0526   1.0000
  15.750   1.0959   0.11711   0.10892  -0.0309   0.0517   1.0000
  16.000   1.0860   0.12348   0.11552  -0.0338   0.0510   1.0000
  16.250   1.0719   0.13111   0.12338  -0.0378   0.0506   1.0000
  16.500   1.0505   0.14115   0.13366  -0.0436   0.0507   1.0000
  16.750   1.0156   0.15622   0.14893  -0.0527   0.0514   1.0000
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