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CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: CLARK K AIRFOIL (clarkk-il)
Reynolds number: 100,000
Max Cl/Cd: 54.69 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkk-il-100000-n5.txt
Download as CSV file: xf-clarkk-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4392   0.08905   0.08376  -0.0502   1.0000   0.0716
  -9.250  -0.4322   0.08673   0.08147  -0.0483   1.0000   0.0709
  -9.000  -0.4332   0.08403   0.07882  -0.0471   1.0000   0.0700
  -8.750  -0.4448   0.08095   0.07582  -0.0463   1.0000   0.0691
  -8.500  -0.4672   0.07782   0.07280  -0.0452   1.0000   0.0684
  -8.250  -0.4897   0.07360   0.06864  -0.0455   1.0000   0.0678
  -8.000  -0.5117   0.06892   0.06395  -0.0458   1.0000   0.0674
  -7.750  -0.5107   0.06015   0.05489  -0.0537   0.9935   0.0674
  -7.500  -0.4994   0.05231   0.04657  -0.0603   0.9853   0.0671
  -7.250  -0.4828   0.04690   0.04066  -0.0642   0.9778   0.0677
  -7.000  -0.4609   0.04272   0.03591  -0.0672   0.9717   0.0690
  -6.750  -0.4370   0.03952   0.03223  -0.0690   0.9653   0.0694
  -6.500  -0.4102   0.03687   0.02912  -0.0706   0.9598   0.0697
  -6.250  -0.3828   0.03486   0.02664  -0.0719   0.9537   0.0706
  -6.000  -0.3507   0.03338   0.02464  -0.0736   0.9493   0.0716
  -5.750  -0.3245   0.03163   0.02260  -0.0741   0.9424   0.0720
  -5.500  -0.2909   0.02989   0.02060  -0.0759   0.9385   0.0723
  -5.250  -0.2624   0.02849   0.01900  -0.0765   0.9322   0.0726
  -5.000  -0.2304   0.02719   0.01751  -0.0777   0.9269   0.0730
  -4.750  -0.1953   0.02592   0.01614  -0.0794   0.9234   0.0742
  -4.500  -0.1691   0.02504   0.01517  -0.0793   0.9154   0.0754
  -4.250  -0.1358   0.02413   0.01416  -0.0805   0.9105   0.0764
  -4.000  -0.1041   0.02333   0.01325  -0.0812   0.9050   0.0768
  -3.750  -0.0756   0.02265   0.01249  -0.0813   0.8975   0.0772
  -3.500  -0.0416   0.02192   0.01171  -0.0824   0.8930   0.0776
  -3.250  -0.0149   0.02138   0.01114  -0.0822   0.8850   0.0781
  -3.000   0.0159   0.02080   0.01053  -0.0826   0.8788   0.0788
  -2.750   0.0477   0.02025   0.00996  -0.0833   0.8735   0.0795
  -2.500   0.0731   0.01986   0.00957  -0.0827   0.8646   0.0806
  -2.250   0.1050   0.01940   0.00908  -0.0833   0.8591   0.0823
  -2.000   0.1303   0.01913   0.00878  -0.0828   0.8501   0.0835
  -1.750   0.1601   0.01865   0.00830  -0.0830   0.8437   0.0848
  -1.500   0.1867   0.01834   0.00798  -0.0826   0.8353   0.0858
  -1.250   0.2154   0.01802   0.00764  -0.0826   0.8278   0.0871
  -1.000   0.2433   0.01777   0.00737  -0.0824   0.8198   0.0887
  -0.750   0.2714   0.01755   0.00712  -0.0822   0.8115   0.0905
  -0.500   0.2994   0.01736   0.00691  -0.0820   0.8032   0.0928
  -0.250   0.3274   0.01718   0.00671  -0.0818   0.7945   0.0958
   0.000   0.3546   0.01699   0.00658  -0.0814   0.7854   0.1030
   0.250   0.3825   0.01645   0.00651  -0.0814   0.7769   0.2136
   0.500   0.4087   0.01622   0.00650  -0.0810   0.7667   0.2767
   0.750   0.4370   0.01568   0.00640  -0.0810   0.7585   0.4072
   1.000   0.4584   0.01515   0.00651  -0.0796   0.7470   0.5847
   1.250   0.4864   0.01449   0.00663  -0.0783   0.7371   0.8486
   1.500   0.5445   0.01430   0.00645  -0.0839   0.7260   1.0000
   1.750   0.5683   0.01439   0.00646  -0.0829   0.7123   1.0000
   2.000   0.5927   0.01447   0.00644  -0.0820   0.6982   1.0000
   2.250   0.6174   0.01454   0.00642  -0.0811   0.6840   1.0000
   2.500   0.6423   0.01463   0.00643  -0.0803   0.6698   1.0000
   2.750   0.6674   0.01473   0.00645  -0.0795   0.6561   1.0000
   3.000   0.6927   0.01485   0.00649  -0.0788   0.6427   1.0000
   3.250   0.7168   0.01500   0.00660  -0.0779   0.6280   1.0000
   3.500   0.7411   0.01516   0.00671  -0.0771   0.6132   1.0000
   3.750   0.7654   0.01533   0.00685  -0.0762   0.5981   1.0000
   4.000   0.7897   0.01552   0.00699  -0.0754   0.5827   1.0000
   4.250   0.8137   0.01572   0.00715  -0.0745   0.5668   1.0000
   4.500   0.8376   0.01595   0.00734  -0.0736   0.5504   1.0000
   4.750   0.8612   0.01619   0.00754  -0.0727   0.5335   1.0000
   5.000   0.8845   0.01646   0.00777  -0.0717   0.5161   1.0000
   5.250   0.9075   0.01676   0.00804  -0.0707   0.4984   1.0000
   5.500   0.9300   0.01708   0.00832  -0.0697   0.4801   1.0000
   5.750   0.9523   0.01743   0.00864  -0.0686   0.4616   1.0000
   6.000   0.9741   0.01781   0.00900  -0.0675   0.4427   1.0000
   6.250   0.9955   0.01821   0.00938  -0.0664   0.4236   1.0000
   6.500   1.0166   0.01865   0.00981  -0.0652   0.4047   1.0000
   6.750   1.0373   0.01911   0.01025  -0.0640   0.3869   1.0000
   7.000   1.0579   0.01961   0.01073  -0.0627   0.3702   1.0000
   7.250   1.0782   0.02014   0.01125  -0.0615   0.3543   1.0000
   7.500   1.0980   0.02070   0.01181  -0.0602   0.3389   1.0000
   7.750   1.1168   0.02128   0.01238  -0.0588   0.3229   1.0000
   8.000   1.1341   0.02190   0.01297  -0.0573   0.3052   1.0000
   8.250   1.1497   0.02256   0.01360  -0.0555   0.2862   1.0000
   8.500   1.1644   0.02326   0.01424  -0.0536   0.2678   1.0000
   8.750   1.1785   0.02398   0.01494  -0.0517   0.2497   1.0000
   9.000   1.1915   0.02472   0.01568  -0.0497   0.2301   1.0000
   9.250   1.2028   0.02549   0.01646  -0.0474   0.2118   1.0000
   9.500   1.2142   0.02633   0.01733  -0.0453   0.1942   1.0000
   9.750   1.2242   0.02728   0.01828  -0.0431   0.1737   1.0000
  10.000   1.2327   0.02839   0.01935  -0.0409   0.1464   1.0000
  10.250   1.2351   0.02999   0.02074  -0.0383   0.1082   1.0000
  10.500   1.2326   0.03214   0.02260  -0.0355   0.0776   1.0000
  10.750   1.2323   0.03422   0.02461  -0.0331   0.0624   1.0000
  11.000   1.2326   0.03634   0.02671  -0.0309   0.0545   1.0000
  11.250   1.2342   0.03840   0.02885  -0.0291   0.0494   1.0000
  11.500   1.2327   0.04079   0.03128  -0.0274   0.0461   1.0000
  11.750   1.2339   0.04304   0.03368  -0.0261   0.0434   1.0000
  12.000   1.2331   0.04555   0.03633  -0.0249   0.0414   1.0000
  12.250   1.2307   0.04833   0.03923  -0.0240   0.0399   1.0000
  12.500   1.2258   0.05147   0.04247  -0.0232   0.0385   1.0000
  12.750   1.2195   0.05486   0.04595  -0.0227   0.0374   1.0000
  13.000   1.2178   0.05789   0.04917  -0.0224   0.0363   1.0000
  13.250   1.2152   0.06109   0.05252  -0.0222   0.0351   1.0000
  13.500   1.2121   0.06443   0.05600  -0.0222   0.0341   1.0000
  13.750   1.2093   0.06783   0.05952  -0.0223   0.0332   1.0000
  14.000   1.2068   0.07122   0.06302  -0.0224   0.0324   1.0000
  14.250   1.2050   0.07458   0.06648  -0.0225   0.0317   1.0000
  14.500   1.2036   0.07791   0.06987  -0.0227   0.0309   1.0000
  14.750   1.2036   0.08096   0.07297  -0.0226   0.0302   1.0000
  15.000   1.2058   0.08372   0.07577  -0.0222   0.0293   1.0000
  15.250   1.2057   0.08715   0.07940  -0.0227   0.0287   1.0000
  15.500   1.2050   0.09074   0.08317  -0.0234   0.0280   1.0000
  15.750   1.2036   0.09448   0.08709  -0.0241   0.0274   1.0000
  16.000   1.2020   0.09832   0.09108  -0.0250   0.0269   1.0000
  16.250   1.1995   0.10237   0.09530  -0.0260   0.0265   1.0000
  16.500   1.1959   0.10669   0.09979  -0.0274   0.0261   1.0000
  16.750   1.1907   0.11143   0.10470  -0.0292   0.0258   1.0000
  17.000   1.1842   0.11654   0.10998  -0.0314   0.0255   1.0000
  17.250   1.1763   0.12204   0.11565  -0.0341   0.0252   1.0000
  17.500   1.1671   0.12799   0.12178  -0.0372   0.0250   1.0000
  17.750   1.1561   0.13457   0.12854  -0.0409   0.0248   1.0000
  18.000   1.1427   0.14199   0.13615  -0.0455   0.0247   1.0000
  18.250   1.1241   0.15123   0.14560  -0.0514   0.0247   1.0000
  18.500   1.0886   0.16613   0.16080  -0.0614   0.0252   1.0000
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