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


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 100,000
Max Cl/Cd: 54.1 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-clarkw-il-100000-n5.txt
Download as CSV file: xf-clarkw-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CLARK W 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4002   0.09127   0.08595  -0.0432   1.0000   0.0504
  -9.000  -0.4145   0.08728   0.08204  -0.0434   1.0000   0.0497
  -8.500  -0.5148   0.07182   0.06683  -0.0464   1.0000   0.0470
  -8.250  -0.5335   0.06691   0.06191  -0.0465   1.0000   0.0468
  -8.000  -0.5448   0.05597   0.05064  -0.0541   0.9951   0.0466
  -7.750  -0.5448   0.04475   0.03844  -0.0620   0.9862   0.0471
  -7.500  -0.5215   0.04212   0.03566  -0.0639   0.9817   0.0479
  -7.250  -0.4994   0.03910   0.03230  -0.0655   0.9761   0.0486
  -7.000  -0.4733   0.03585   0.02858  -0.0677   0.9722   0.0491
  -6.750  -0.4516   0.03344   0.02579  -0.0680   0.9660   0.0496
  -6.500  -0.4232   0.03128   0.02325  -0.0694   0.9617   0.0504
  -6.250  -0.3940   0.02946   0.02108  -0.0705   0.9577   0.0512
  -6.000  -0.3683   0.02807   0.01939  -0.0706   0.9518   0.0526
  -5.750  -0.3366   0.02671   0.01769  -0.0718   0.9478   0.0543
  -5.500  -0.3025   0.02547   0.01622  -0.0734   0.9450   0.0557
  -5.250  -0.2788   0.02461   0.01531  -0.0729   0.9380   0.0568
  -5.000  -0.2471   0.02377   0.01439  -0.0739   0.9336   0.0582
  -4.750  -0.2122   0.02295   0.01348  -0.0754   0.9305   0.0601
  -4.500  -0.1862   0.02231   0.01272  -0.0752   0.9240   0.0622
  -4.250  -0.1554   0.02166   0.01199  -0.0758   0.9189   0.0651
  -4.000  -0.1203   0.02109   0.01143  -0.0774   0.9154   0.0701
  -3.750  -0.0915   0.02059   0.01086  -0.0776   0.9097   0.0761
  -3.500  -0.0625   0.02007   0.01035  -0.0779   0.9036   0.0846
  -3.250  -0.0281   0.01948   0.00977  -0.0791   0.8996   0.1010
  -3.000  -0.0001   0.01905   0.00943  -0.0792   0.8931   0.1216
  -2.750   0.0301   0.01868   0.00912  -0.0796   0.8867   0.1472
  -2.500   0.0658   0.01824   0.00879  -0.0810   0.8824   0.1796
  -2.250   0.0908   0.01800   0.00868  -0.0804   0.8728   0.2122
  -2.000   0.1253   0.01764   0.00846  -0.0814   0.8671   0.2534
  -1.750   0.1511   0.01747   0.00836  -0.0808   0.8575   0.2848
  -1.500   0.1844   0.01718   0.00809  -0.0814   0.8515   0.3150
  -1.250   0.2105   0.01703   0.00795  -0.0808   0.8421   0.3395
  -1.000   0.2430   0.01675   0.00768  -0.0813   0.8356   0.3656
  -0.750   0.2693   0.01658   0.00754  -0.0808   0.8258   0.3903
  -0.500   0.3017   0.01623   0.00725  -0.0813   0.8189   0.4200
  -0.250   0.3264   0.01598   0.00713  -0.0805   0.8083   0.4547
   0.000   0.3547   0.01535   0.00685  -0.0802   0.8006   0.5315
   0.250   0.4385   0.01443   0.00694  -0.0902   0.7929   0.9944
   0.500   0.4726   0.01435   0.00672  -0.0911   0.7830   1.0000
   0.750   0.4978   0.01435   0.00661  -0.0903   0.7711   1.0000
   1.000   0.5217   0.01438   0.00656  -0.0892   0.7582   1.0000
   1.250   0.5466   0.01440   0.00649  -0.0884   0.7455   1.0000
   1.500   0.5720   0.01442   0.00641  -0.0875   0.7324   1.0000
   1.750   0.5975   0.01444   0.00634  -0.0867   0.7189   1.0000
   2.000   0.6222   0.01448   0.00630  -0.0858   0.7042   1.0000
   2.250   0.6461   0.01456   0.00630  -0.0847   0.6886   1.0000
   2.500   0.6701   0.01464   0.00632  -0.0837   0.6724   1.0000
   2.750   0.6941   0.01475   0.00634  -0.0826   0.6555   1.0000
   3.000   0.7174   0.01488   0.00641  -0.0815   0.6378   1.0000
   3.250   0.7406   0.01504   0.00650  -0.0803   0.6195   1.0000
   3.500   0.7638   0.01521   0.00660  -0.0792   0.6009   1.0000
   3.750   0.7869   0.01541   0.00673  -0.0781   0.5823   1.0000
   4.000   0.8098   0.01564   0.00688  -0.0769   0.5638   1.0000
   4.250   0.8327   0.01590   0.00706  -0.0758   0.5459   1.0000
   4.500   0.8554   0.01618   0.00727  -0.0747   0.5286   1.0000
   4.750   0.8780   0.01648   0.00752  -0.0736   0.5120   1.0000
   5.000   0.9005   0.01681   0.00779  -0.0725   0.4964   1.0000
   5.250   0.9230   0.01715   0.00809  -0.0714   0.4816   1.0000
   5.500   0.9454   0.01751   0.00844  -0.0704   0.4676   1.0000
   5.750   0.9678   0.01789   0.00880  -0.0693   0.4541   1.0000
   6.000   0.9895   0.01829   0.00916  -0.0682   0.4398   1.0000
   6.250   1.0103   0.01870   0.00953  -0.0669   0.4241   1.0000
   6.500   1.0307   0.01913   0.00994  -0.0655   0.4085   1.0000
   6.750   1.0512   0.01956   0.01035  -0.0642   0.3944   1.0000
   7.000   1.0721   0.02000   0.01082  -0.0630   0.3820   1.0000
   7.250   1.0926   0.02044   0.01133  -0.0618   0.3695   1.0000
   7.500   1.1121   0.02089   0.01181  -0.0604   0.3557   1.0000
   7.750   1.1297   0.02136   0.01230  -0.0587   0.3392   1.0000
   8.000   1.1459   0.02185   0.01279  -0.0568   0.3209   1.0000
   8.250   1.1614   0.02239   0.01332  -0.0549   0.3026   1.0000
   8.500   1.1764   0.02295   0.01389  -0.0529   0.2849   1.0000
   8.750   1.1911   0.02354   0.01452  -0.0509   0.2662   1.0000
   9.000   1.2044   0.02419   0.01519  -0.0488   0.2462   1.0000
   9.250   1.2150   0.02492   0.01590  -0.0462   0.2254   1.0000
   9.500   1.2244   0.02578   0.01675  -0.0437   0.2024   1.0000
   9.750   1.2317   0.02683   0.01771  -0.0410   0.1783   1.0000
  10.000   1.2379   0.02804   0.01883  -0.0384   0.1546   1.0000
  10.500   1.2451   0.03102   0.02165  -0.0332   0.1211   1.0000
  10.750   1.2484   0.03265   0.02326  -0.0309   0.1093   1.0000
  11.000   1.2523   0.03429   0.02497  -0.0287   0.0995   1.0000
  11.250   1.2543   0.03612   0.02683  -0.0266   0.0918   1.0000
  11.500   1.2568   0.03800   0.02877  -0.0248   0.0848   1.0000
  11.750   1.2583   0.04002   0.03085  -0.0231   0.0795   1.0000
  12.000   1.2605   0.04206   0.03299  -0.0216   0.0746   1.0000
  12.250   1.2587   0.04451   0.03545  -0.0202   0.0710   1.0000
  12.500   1.2615   0.04666   0.03774  -0.0191   0.0671   1.0000
  12.750   1.2622   0.04908   0.04027  -0.0181   0.0639   1.0000
  13.000   1.2602   0.05181   0.04303  -0.0173   0.0615   1.0000
  13.250   1.2605   0.05441   0.04574  -0.0165   0.0589   1.0000
  13.500   1.2613   0.05704   0.04851  -0.0160   0.0563   1.0000
  13.750   1.2609   0.05984   0.05141  -0.0156   0.0542   1.0000
  14.000   1.2593   0.06282   0.05444  -0.0153   0.0524   1.0000
  14.250   1.2590   0.06573   0.05742  -0.0150   0.0506   1.0000
  14.500   1.2596   0.06869   0.06057  -0.0149   0.0486   1.0000
  14.750   1.2591   0.07180   0.06382  -0.0149   0.0468   1.0000
  15.000   1.2584   0.07499   0.06710  -0.0151   0.0453   1.0000
  15.250   1.2578   0.07815   0.07030  -0.0154   0.0440   1.0000
  15.500   1.2575   0.08135   0.07358  -0.0155   0.0427   1.0000
  15.750   1.2542   0.08523   0.07770  -0.0162   0.0413   1.0000
  16.000   1.2507   0.08918   0.08183  -0.0171   0.0400   1.0000
  16.250   1.2471   0.09318   0.08598  -0.0182   0.0389   1.0000
  16.500   1.2440   0.09711   0.09003  -0.0193   0.0380   1.0000
  16.750   1.2424   0.10078   0.09376  -0.0202   0.0371   1.0000
  17.000   1.2437   0.10384   0.09682  -0.0208   0.0362   1.0000
  17.250   1.2323   0.10968   0.10293  -0.0233   0.0356   1.0000
  17.500   1.2195   0.11594   0.10945  -0.0263   0.0350   1.0000
  17.750   1.2052   0.12270   0.11645  -0.0299   0.0344   1.0000
  18.000   1.1890   0.13011   0.12409  -0.0340   0.0340   1.0000
  18.250   1.1695   0.13863   0.13284  -0.0391   0.0337   1.0000
  18.500   1.1426   0.14946   0.14390  -0.0460   0.0337   1.0000
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