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CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: CLARK V AIRFOIL (clarkv-il)
Reynolds number: 500,000
Max Cl/Cd: 110.42 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkv-il-500000.txt
Download as CSV file: xf-clarkv-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4826   0.09144   0.08924  -0.0432   0.9994   0.0326
  -9.750  -0.5294   0.07145   0.06928  -0.0574   0.9955   0.0271
  -9.500  -0.6205   0.03791   0.03464  -0.0854   0.9793   0.0249
  -9.250  -0.6151   0.03177   0.02775  -0.0868   0.9745   0.0258
  -9.000  -0.5959   0.02781   0.02320  -0.0884   0.9723   0.0269
  -8.750  -0.5657   0.02653   0.02187  -0.0902   0.9713   0.0279
  -8.500  -0.5472   0.02611   0.02145  -0.0889   0.9656   0.0287
  -8.250  -0.5195   0.02496   0.02015  -0.0897   0.9630   0.0297
  -8.000  -0.4906   0.02339   0.01830  -0.0908   0.9611   0.0308
  -7.750  -0.4585   0.02231   0.01696  -0.0922   0.9597   0.0319
  -7.500  -0.4283   0.02023   0.01458  -0.0936   0.9586   0.0332
  -7.250  -0.3944   0.01917   0.01347  -0.0955   0.9579   0.0343
  -7.000  -0.3765   0.01855   0.01279  -0.0937   0.9515   0.0351
  -6.750  -0.3451   0.01784   0.01199  -0.0947   0.9492   0.0363
  -6.500  -0.3112   0.01715   0.01121  -0.0961   0.9477   0.0377
  -6.250  -0.2761   0.01643   0.01038  -0.0978   0.9466   0.0386
  -6.000  -0.2410   0.01585   0.00970  -0.0994   0.9455   0.0393
  -5.750  -0.2090   0.01447   0.00825  -0.1006   0.9443   0.0410
  -5.500  -0.1749   0.01387   0.00764  -0.1021   0.9432   0.0425
  -5.250  -0.1569   0.01350   0.00724  -0.1000   0.9359   0.0435
  -5.000  -0.1257   0.01299   0.00671  -0.1007   0.9334   0.0450
  -4.750  -0.0934   0.01252   0.00619  -0.1017   0.9314   0.0465
  -4.500  -0.0605   0.01213   0.00576  -0.1027   0.9296   0.0479
  -4.250  -0.0372   0.01157   0.00519  -0.1018   0.9244   0.0508
  -4.000  -0.0096   0.01122   0.00484  -0.1017   0.9200   0.0536
  -3.750   0.0212   0.01089   0.00448  -0.1022   0.9171   0.0571
  -3.500   0.0526   0.01043   0.00404  -0.1029   0.9146   0.0648
  -3.250   0.0762   0.01012   0.00379  -0.1020   0.9083   0.0788
  -3.000   0.1041   0.00971   0.00348  -0.1020   0.9038   0.1077
  -2.750   0.1342   0.00928   0.00322  -0.1025   0.9004   0.1558
  -2.500   0.1587   0.00891   0.00307  -0.1019   0.8943   0.2132
  -2.250   0.1855   0.00849   0.00291  -0.1018   0.8889   0.2952
  -2.000   0.2148   0.00811   0.00275  -0.1022   0.8848   0.3690
  -1.750   0.2388   0.00786   0.00269  -0.1014   0.8773   0.4316
  -1.500   0.2662   0.00752   0.00257  -0.1013   0.8718   0.5072
  -1.250   0.2905   0.00717   0.00252  -0.1006   0.8648   0.5988
  -1.000   0.3142   0.00677   0.00248  -0.0995   0.8576   0.7081
  -0.750   0.3366   0.00647   0.00248  -0.0979   0.8485   0.8068
  -0.500   0.3626   0.00631   0.00246  -0.0968   0.8393   0.8851
  -0.250   0.3914   0.00630   0.00248  -0.0965   0.8288   0.9268
   0.000   0.4255   0.00634   0.00248  -0.0976   0.8205   0.9523
   0.250   0.4662   0.00640   0.00248  -0.1001   0.8121   0.9727
   0.500   0.5132   0.00647   0.00250  -0.1042   0.8034   0.9853
   1.000   0.6054   0.00653   0.00244  -0.1121   0.7830   1.0000
   1.250   0.6288   0.00657   0.00240  -0.1112   0.7688   1.0000
   1.500   0.6516   0.00662   0.00238  -0.1101   0.7529   1.0000
   1.750   0.6744   0.00669   0.00238  -0.1091   0.7378   1.0000
   2.000   0.6974   0.00677   0.00240  -0.1081   0.7243   1.0000
   2.250   0.7202   0.00686   0.00243  -0.1070   0.7102   1.0000
   2.500   0.7425   0.00696   0.00248  -0.1058   0.6949   1.0000
   2.750   0.7645   0.00708   0.00254  -0.1045   0.6791   1.0000
   3.000   0.7865   0.00721   0.00261  -0.1033   0.6635   1.0000
   3.250   0.8082   0.00736   0.00269  -0.1020   0.6475   1.0000
   3.500   0.8295   0.00752   0.00279  -0.1006   0.6306   1.0000
   3.750   0.8502   0.00770   0.00290  -0.0991   0.6122   1.0000
   4.000   0.8706   0.00789   0.00302  -0.0975   0.5913   1.0000
   4.250   0.8905   0.00812   0.00316  -0.0958   0.5683   1.0000
   4.500   0.9101   0.00836   0.00331  -0.0941   0.5429   1.0000
   4.750   0.9290   0.00866   0.00349  -0.0923   0.5143   1.0000
   5.000   0.9481   0.00897   0.00368  -0.0906   0.4857   1.0000
   5.250   0.9674   0.00930   0.00390  -0.0889   0.4570   1.0000
   5.500   0.9862   0.00968   0.00415  -0.0872   0.4253   1.0000
   5.750   1.0047   0.01010   0.00443  -0.0855   0.3926   1.0000
   6.000   1.0234   0.01053   0.00473  -0.0838   0.3638   1.0000
   6.250   1.0422   0.01097   0.00505  -0.0822   0.3363   1.0000
   6.500   1.0609   0.01143   0.00539  -0.0806   0.3085   1.0000
   6.750   1.0796   0.01189   0.00573  -0.0791   0.2818   1.0000
   7.000   1.0978   0.01237   0.00609  -0.0774   0.2562   1.0000
   7.250   1.1151   0.01285   0.00645  -0.0756   0.2305   1.0000
   7.500   1.1328   0.01332   0.00684  -0.0739   0.2087   1.0000
   7.750   1.1507   0.01379   0.00723  -0.0723   0.1907   1.0000
   8.000   1.1685   0.01429   0.00766  -0.0707   0.1741   1.0000
   8.250   1.1861   0.01479   0.00811  -0.0690   0.1586   1.0000
   8.500   1.2038   0.01531   0.00857  -0.0675   0.1435   1.0000
   8.750   1.2209   0.01586   0.00906  -0.0658   0.1271   1.0000
   9.000   1.2372   0.01647   0.00959  -0.0641   0.1078   1.0000
   9.250   1.2509   0.01724   0.01025  -0.0621   0.0885   1.0000
   9.500   1.2640   0.01806   0.01098  -0.0599   0.0694   1.0000
   9.750   1.2723   0.01922   0.01195  -0.0572   0.0440   1.0000
  10.000   1.2809   0.02038   0.01301  -0.0545   0.0316   1.0000
  10.250   1.2932   0.02130   0.01396  -0.0524   0.0275   1.0000
  10.500   1.3026   0.02241   0.01509  -0.0499   0.0247   1.0000
  10.750   1.3161   0.02325   0.01601  -0.0481   0.0231   1.0000
  11.000   1.3274   0.02424   0.01706  -0.0462   0.0217   1.0000
  11.250   1.3343   0.02556   0.01843  -0.0437   0.0205   1.0000
  11.500   1.3409   0.02692   0.01988  -0.0414   0.0197   1.0000
  11.750   1.3505   0.02809   0.02114  -0.0395   0.0190   1.0000
  12.000   1.3586   0.02940   0.02254  -0.0376   0.0184   1.0000
  12.250   1.3655   0.03083   0.02406  -0.0356   0.0178   1.0000
  12.500   1.3710   0.03241   0.02571  -0.0338   0.0172   1.0000
  12.750   1.3731   0.03433   0.02769  -0.0318   0.0167   1.0000
  13.000   1.3684   0.03688   0.03034  -0.0294   0.0161   1.0000
  13.250   1.3711   0.03891   0.03247  -0.0279   0.0158   1.0000
  13.500   1.3766   0.04075   0.03441  -0.0266   0.0154   1.0000
  13.750   1.3799   0.04282   0.03659  -0.0254   0.0151   1.0000
  14.000   1.3820   0.04509   0.03896  -0.0243   0.0148   1.0000
  14.250   1.3836   0.04750   0.04148  -0.0234   0.0144   1.0000
  14.500   1.3844   0.05005   0.04414  -0.0226   0.0142   1.0000
  14.750   1.3846   0.05275   0.04693  -0.0219   0.0139   1.0000
  15.000   1.3840   0.05562   0.04988  -0.0214   0.0136   1.0000
  15.250   1.3827   0.05865   0.05300  -0.0211   0.0134   1.0000
  15.500   1.3802   0.06186   0.05629  -0.0208   0.0132   1.0000
  15.750   1.3760   0.06527   0.05978  -0.0205   0.0130   1.0000
  16.000   1.3704   0.06884   0.06345  -0.0199   0.0128   1.0000
  16.250   1.3657   0.07248   0.06722  -0.0197   0.0126   1.0000
  16.500   1.3626   0.07619   0.07106  -0.0203   0.0125   1.0000
  16.750   1.3584   0.08013   0.07517  -0.0211   0.0124   1.0000
  17.000   1.3533   0.08432   0.07950  -0.0221   0.0123   1.0000
  17.250   1.3473   0.08875   0.08408  -0.0233   0.0122   1.0000
  17.500   1.3405   0.09340   0.08887  -0.0248   0.0120   1.0000
  17.750   1.3327   0.09828   0.09391  -0.0265   0.0119   1.0000
  18.000   1.3242   0.10341   0.09918  -0.0285   0.0118   1.0000
  18.250   1.3153   0.10873   0.10464  -0.0308   0.0116   1.0000
  18.500   1.3056   0.11433   0.11039  -0.0333   0.0115   1.0000
  18.750   1.2956   0.12010   0.11630  -0.0361   0.0114   1.0000
  19.000   1.2845   0.12618   0.12252  -0.0393   0.0114   1.0000
  19.250   1.2736   0.13243   0.12891  -0.0427   0.0113   1.0000
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