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


Details Polar file
Airfoil: CLARK V AIRFOIL (clarkv-il)
Reynolds number: 100,000
Max Cl/Cd: 56.28 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkv-il-100000-n5.txt
Download as CSV file: xf-clarkv-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK V 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  -0.4521   0.09358   0.08857  -0.0437   1.0000   0.0420
  -9.250  -0.4668   0.08972   0.08480  -0.0435   1.0000   0.0419
  -9.000  -0.4855   0.08585   0.08101  -0.0431   1.0000   0.0419
  -8.750  -0.5092   0.08218   0.07745  -0.0423   1.0000   0.0418
  -8.500  -0.5357   0.07800   0.07335  -0.0422   1.0000   0.0415
  -8.250  -0.5557   0.06986   0.06518  -0.0473   0.9982   0.0414
  -8.000  -0.5616   0.05778   0.05263  -0.0574   0.9904   0.0422
  -7.750  -0.5582   0.04878   0.04286  -0.0627   0.9843   0.0434
  -7.500  -0.5472   0.04299   0.03626  -0.0646   0.9785   0.0441
  -7.250  -0.5229   0.04057   0.03369  -0.0662   0.9753   0.0456
  -7.000  -0.4993   0.03912   0.03211  -0.0670   0.9709   0.0474
  -6.750  -0.4755   0.03677   0.02938  -0.0679   0.9666   0.0492
  -6.500  -0.4477   0.03407   0.02617  -0.0693   0.9635   0.0505
  -6.250  -0.4223   0.03203   0.02365  -0.0697   0.9594   0.0523
  -6.000  -0.3956   0.03049   0.02155  -0.0700   0.9547   0.0543
  -5.750  -0.3657   0.02884   0.01979  -0.0712   0.9516   0.0558
  -5.500  -0.3327   0.02762   0.01841  -0.0727   0.9492   0.0574
  -5.250  -0.3085   0.02665   0.01730  -0.0723   0.9437   0.0589
  -5.000  -0.2789   0.02577   0.01623  -0.0729   0.9395   0.0613
  -4.750  -0.2455   0.02499   0.01524  -0.0742   0.9363   0.0647
  -4.500  -0.2116   0.02406   0.01422  -0.0756   0.9338   0.0672
  -4.250  -0.1897   0.02338   0.01355  -0.0747   0.9270   0.0696
  -4.000  -0.1584   0.02273   0.01285  -0.0756   0.9230   0.0733
  -3.750  -0.1239   0.02212   0.01214  -0.0770   0.9201   0.0783
  -3.500  -0.0999   0.02159   0.01165  -0.0765   0.9138   0.0848
  -3.250  -0.0698   0.02111   0.01115  -0.0772   0.9090   0.0957
  -3.000  -0.0355   0.02055   0.01066  -0.0787   0.9058   0.1123
  -2.750  -0.0098   0.02016   0.01034  -0.0784   0.8995   0.1369
  -2.500   0.0198   0.01962   0.01003  -0.0791   0.8944   0.1854
  -2.250   0.0533   0.01888   0.00983  -0.0807   0.8913   0.2991
  -2.000   0.0781   0.01841   0.00978  -0.0803   0.8849   0.4111
  -1.750   0.1067   0.01797   0.00967  -0.0805   0.8797   0.5084
  -1.500   0.1391   0.01745   0.00953  -0.0810   0.8766   0.6169
  -1.250   0.1590   0.01711   0.00964  -0.0786   0.8695   0.7481
  -1.000   0.2073   0.01690   0.00970  -0.0814   0.8670   0.9320
  -0.750   0.2657   0.01681   0.00946  -0.0877   0.8649   1.0000
  -0.500   0.3020   0.01665   0.00914  -0.0893   0.8614   1.0000
  -0.250   0.3212   0.01671   0.00910  -0.0877   0.8517   1.0000
   0.000   0.3564   0.01656   0.00883  -0.0891   0.8475   1.0000
   0.250   0.3780   0.01662   0.00881  -0.0879   0.8384   1.0000
   0.500   0.4122   0.01647   0.00858  -0.0890   0.8334   1.0000
   0.750   0.4360   0.01651   0.00855  -0.0882   0.8245   1.0000
   1.000   0.4703   0.01632   0.00830  -0.0892   0.8185   1.0000
   1.250   0.4953   0.01628   0.00820  -0.0884   0.8079   1.0000
   1.500   0.5301   0.01602   0.00788  -0.0894   0.8000   1.0000
   1.750   0.5572   0.01594   0.00777  -0.0889   0.7890   1.0000
   2.000   0.5831   0.01592   0.00773  -0.0884   0.7781   1.0000
   2.250   0.6164   0.01578   0.00755  -0.0891   0.7698   1.0000
   2.500   0.6424   0.01579   0.00756  -0.0886   0.7583   1.0000
   2.750   0.6684   0.01582   0.00758  -0.0880   0.7464   1.0000
   3.000   0.6967   0.01580   0.00757  -0.0879   0.7346   1.0000
   3.250   0.7257   0.01577   0.00753  -0.0879   0.7221   1.0000
   3.500   0.7528   0.01576   0.00751  -0.0874   0.7069   1.0000
   3.750   0.7785   0.01579   0.00753  -0.0867   0.6891   1.0000
   4.000   0.8045   0.01583   0.00754  -0.0860   0.6703   1.0000
   4.250   0.8308   0.01590   0.00759  -0.0855   0.6518   1.0000
   4.500   0.8569   0.01601   0.00768  -0.0849   0.6334   1.0000
   4.750   0.8800   0.01620   0.00786  -0.0838   0.6133   1.0000
   5.000   0.9036   0.01640   0.00804  -0.0828   0.5923   1.0000
   5.250   0.9270   0.01663   0.00825  -0.0818   0.5704   1.0000
   5.500   0.9485   0.01691   0.00851  -0.0805   0.5466   1.0000
   5.750   0.9697   0.01723   0.00878  -0.0791   0.5215   1.0000
   6.000   0.9898   0.01760   0.00908  -0.0776   0.4951   1.0000
   6.250   1.0083   0.01803   0.00945  -0.0758   0.4661   1.0000
   6.500   1.0252   0.01853   0.00983  -0.0737   0.4347   1.0000
   6.750   1.0407   0.01910   0.01027  -0.0715   0.4031   1.0000
   7.000   1.0560   0.01971   0.01077  -0.0694   0.3741   1.0000
   7.250   1.0716   0.02033   0.01134  -0.0673   0.3492   1.0000
   7.500   1.0866   0.02100   0.01193  -0.0652   0.3276   1.0000
   7.750   1.1014   0.02165   0.01256  -0.0631   0.3076   1.0000
   8.000   1.1159   0.02233   0.01323  -0.0610   0.2885   1.0000
   8.250   1.1300   0.02304   0.01394  -0.0589   0.2704   1.0000
   8.500   1.1438   0.02379   0.01471  -0.0568   0.2535   1.0000
   8.750   1.1572   0.02457   0.01549  -0.0547   0.2375   1.0000
   9.000   1.1698   0.02540   0.01633  -0.0525   0.2217   1.0000
   9.250   1.1816   0.02628   0.01721  -0.0504   0.2045   1.0000
   9.500   1.1920   0.02723   0.01815  -0.0482   0.1849   1.0000
   9.750   1.2005   0.02831   0.01916  -0.0458   0.1649   1.0000
  10.000   1.2097   0.02942   0.02026  -0.0437   0.1454   1.0000
  10.250   1.2201   0.03051   0.02138  -0.0418   0.1286   1.0000
  10.500   1.2293   0.03171   0.02259  -0.0398   0.1123   1.0000
  10.750   1.2365   0.03309   0.02395  -0.0378   0.0968   1.0000
  11.000   1.2416   0.03468   0.02550  -0.0356   0.0826   1.0000
  11.250   1.2454   0.03645   0.02725  -0.0335   0.0691   1.0000
  11.500   1.2482   0.03836   0.02918  -0.0314   0.0576   1.0000
  11.750   1.2500   0.04040   0.03131  -0.0294   0.0494   1.0000
  12.000   1.2505   0.04261   0.03359  -0.0275   0.0440   1.0000
  12.250   1.2495   0.04501   0.03605  -0.0257   0.0401   1.0000
  12.500   1.2483   0.04751   0.03866  -0.0242   0.0371   1.0000
  12.750   1.2473   0.05008   0.04137  -0.0228   0.0347   1.0000
  13.000   1.2444   0.05292   0.04432  -0.0217   0.0331   1.0000
  13.250   1.2389   0.05611   0.04761  -0.0208   0.0319   1.0000
  13.500   1.2358   0.05920   0.05085  -0.0200   0.0308   1.0000
  13.750   1.2331   0.06236   0.05420  -0.0195   0.0296   1.0000
  14.000   1.2297   0.06570   0.05769  -0.0193   0.0284   1.0000
  14.250   1.2256   0.06924   0.06137  -0.0193   0.0274   1.0000
  14.500   1.2207   0.07301   0.06528  -0.0196   0.0265   1.0000
  14.750   1.2148   0.07699   0.06936  -0.0201   0.0258   1.0000
  15.000   1.2094   0.08097   0.07343  -0.0205   0.0252   1.0000
  15.250   1.2059   0.08488   0.07755  -0.0211   0.0246   1.0000
  15.500   1.2018   0.08896   0.08181  -0.0218   0.0242   1.0000
  15.750   1.1970   0.09325   0.08629  -0.0227   0.0237   1.0000
  16.000   1.1913   0.09778   0.09102  -0.0239   0.0233   1.0000
  16.250   1.1846   0.10263   0.09605  -0.0255   0.0230   1.0000
  16.500   1.1768   0.10785   0.10145  -0.0275   0.0226   1.0000
  16.750   1.1679   0.11343   0.10722  -0.0300   0.0223   1.0000
  17.000   1.1577   0.11943   0.11340  -0.0329   0.0221   1.0000
  17.250   1.1465   0.12591   0.12007  -0.0363   0.0219   1.0000
  17.500   1.1335   0.13306   0.12740  -0.0403   0.0217   1.0000
  17.750   1.1181   0.14116   0.13569  -0.0451   0.0217   1.0000
  18.000   1.0972   0.15122   0.14597  -0.0514   0.0218   1.0000
  18.250   1.0587   0.16752   0.16252  -0.0617   0.0226   1.0000
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