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CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: CLARK W AIRFOIL (clarkw-il)
Reynolds number: 100,000
Max Cl/Cd: 53.21 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkw-il-100000.txt
Download as CSV file: xf-clarkw-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3558   0.10563   0.10036  -0.0358   1.0000   0.1266
  -9.000  -0.3949   0.10547   0.10040  -0.0384   1.0000   0.1291
  -8.750  -0.4340   0.10512   0.10023  -0.0378   1.0000   0.1295
  -8.500  -0.3757   0.09776   0.09273  -0.0347   1.0000   0.1324
  -8.250  -0.3690   0.09547   0.09047  -0.0325   1.0000   0.1357
  -8.000  -0.3779   0.09372   0.08881  -0.0306   1.0000   0.1392
  -7.750  -0.4029   0.09266   0.08787  -0.0282   1.0000   0.1420
  -7.500  -0.4414   0.09197   0.08733  -0.0264   1.0000   0.1436
  -7.250  -0.4904   0.09033   0.08573  -0.0312   1.0000   0.1450
  -7.000  -0.4656   0.08642   0.08190  -0.0238   1.0000   0.1470
  -6.750  -0.4592   0.08441   0.07992  -0.0201   1.0000   0.1496
  -6.500  -0.4635   0.08233   0.07788  -0.0184   1.0000   0.1529
  -6.000  -0.4846   0.07586   0.07139  -0.0220   1.0000   0.1624
  -5.750  -0.4794   0.07361   0.06917  -0.0191   1.0000   0.1645
  -5.500  -0.4752   0.07134   0.06691  -0.0178   1.0000   0.1683
  -5.250  -0.4687   0.04651   0.04045  -0.0373   1.0000   0.1015
  -5.000  -0.4515   0.04339   0.03718  -0.0370   1.0000   0.0982
  -4.750  -0.4332   0.03969   0.03310  -0.0374   1.0000   0.0969
  -4.500  -0.4125   0.03628   0.02923  -0.0377   1.0000   0.0956
  -4.250  -0.3754   0.03271   0.02499  -0.0406   0.9964   0.0939
  -4.000  -0.3347   0.03029   0.02201  -0.0436   0.9919   0.0943
  -3.750  -0.2949   0.02867   0.01993  -0.0462   0.9866   0.0963
  -3.500  -0.2522   0.02768   0.01845  -0.0491   0.9814   0.1006
  -3.250  -0.2152   0.02646   0.01726  -0.0514   0.9750   0.1055
  -3.000  -0.1692   0.02568   0.01629  -0.0548   0.9701   0.1128
  -2.750  -0.1353   0.02481   0.01549  -0.0562   0.9619   0.1227
  -2.500  -0.0889   0.02405   0.01485  -0.0599   0.9565   0.1513
  -2.250  -0.0561   0.02344   0.01446  -0.0611   0.9471   0.1979
  -2.000  -0.0087   0.02337   0.01455  -0.0650   0.9411   0.2471
  -1.750   0.0203   0.02343   0.01471  -0.0655   0.9302   0.2873
  -1.500   0.0575   0.02345   0.01486  -0.0674   0.9219   0.3331
  -1.250   0.0946   0.02318   0.01470  -0.0692   0.9132   0.3783
  -1.000   0.1286   0.02284   0.01446  -0.0703   0.9042   0.4212
  -0.750   0.1690   0.02225   0.01410  -0.0724   0.8967   0.4696
  -0.500   0.2012   0.02169   0.01388  -0.0731   0.8873   0.5278
  -0.250   0.2722   0.02033   0.01373  -0.0800   0.8835   1.0000
   0.000   0.3303   0.02007   0.01321  -0.0853   0.8787   1.0000
   0.250   0.3585   0.02009   0.01309  -0.0851   0.8663   1.0000
   0.500   0.3968   0.01993   0.01280  -0.0866   0.8571   1.0000
   0.750   0.4393   0.01959   0.01236  -0.0886   0.8488   1.0000
   1.000   0.4697   0.01946   0.01215  -0.0886   0.8373   1.0000
   1.250   0.5164   0.01889   0.01151  -0.0911   0.8307   1.0000
   1.500   0.5430   0.01876   0.01133  -0.0902   0.8175   1.0000
   1.750   0.5728   0.01854   0.01107  -0.0898   0.8051   1.0000
   2.000   0.6099   0.01809   0.01057  -0.0905   0.7950   1.0000
   2.250   0.6426   0.01774   0.01018  -0.0904   0.7827   1.0000
   2.500   0.6699   0.01755   0.00995  -0.0895   0.7677   1.0000
   2.750   0.6977   0.01735   0.00972  -0.0887   0.7524   1.0000
   3.000   0.7256   0.01718   0.00950  -0.0879   0.7365   1.0000
   3.250   0.7534   0.01703   0.00930  -0.0870   0.7197   1.0000
   3.500   0.7809   0.01693   0.00914  -0.0862   0.7024   1.0000
   3.750   0.8085   0.01687   0.00901  -0.0854   0.6847   1.0000
   4.000   0.8313   0.01701   0.00911  -0.0840   0.6646   1.0000
   4.250   0.8554   0.01715   0.00920  -0.0828   0.6451   1.0000
   4.500   0.8801   0.01732   0.00931  -0.0818   0.6263   1.0000
   4.750   0.9050   0.01755   0.00946  -0.0808   0.6081   1.0000
   5.000   0.9296   0.01783   0.00967  -0.0798   0.5906   1.0000
   5.250   0.9538   0.01816   0.00994  -0.0789   0.5737   1.0000
   5.500   0.9776   0.01853   0.01027  -0.0779   0.5574   1.0000
   5.750   1.0011   0.01890   0.01060  -0.0768   0.5407   1.0000
   6.000   1.0241   0.01926   0.01087  -0.0756   0.5233   1.0000
   6.250   1.0450   0.01964   0.01124  -0.0741   0.5056   1.0000
   6.500   1.0672   0.02006   0.01165  -0.0729   0.4895   1.0000
   6.750   1.0907   0.02053   0.01208  -0.0720   0.4750   1.0000
   7.000   1.1121   0.02102   0.01259  -0.0707   0.4601   1.0000
   7.250   1.1329   0.02147   0.01305  -0.0694   0.4442   1.0000
   7.500   1.1530   0.02187   0.01341  -0.0678   0.4265   1.0000
   7.750   1.1695   0.02225   0.01384  -0.0657   0.4077   1.0000
   8.000   1.1860   0.02263   0.01427  -0.0636   0.3891   1.0000
   8.250   1.2025   0.02304   0.01472  -0.0616   0.3712   1.0000
   8.500   1.2180   0.02346   0.01519  -0.0594   0.3529   1.0000
   8.750   1.2319   0.02387   0.01563  -0.0569   0.3337   1.0000
   9.000   1.2437   0.02434   0.01610  -0.0542   0.3132   1.0000
   9.250   1.2512   0.02485   0.01670  -0.0509   0.2886   1.0000
   9.500   1.2555   0.02552   0.01736  -0.0472   0.2605   1.0000
   9.750   1.2544   0.02644   0.01820  -0.0427   0.2286   1.0000
  10.000   1.2500   0.02781   0.01935  -0.0382   0.1956   1.0000
  10.250   1.2457   0.02957   0.02086  -0.0342   0.1668   1.0000
  10.500   1.2436   0.03153   0.02261  -0.0308   0.1459   1.0000
  10.750   1.2451   0.03348   0.02444  -0.0279   0.1306   1.0000
  11.000   1.2500   0.03541   0.02625  -0.0255   0.1192   1.0000
  11.250   1.2589   0.03725   0.02796  -0.0236   0.1098   1.0000
  11.500   1.2696   0.03900   0.02984  -0.0219   0.1020   1.0000
  11.750   1.2885   0.04088   0.03153  -0.0210   0.0950   1.0000
  12.000   1.2979   0.04262   0.03351  -0.0192   0.0898   1.0000
  12.250   1.3259   0.04465   0.03528  -0.0193   0.0836   1.0000
  12.500   1.3322   0.04659   0.03757  -0.0173   0.0806   1.0000
  12.750   1.3411   0.04861   0.03978  -0.0157   0.0771   1.0000
  13.000   1.3744   0.05115   0.04209  -0.0165   0.0723   1.0000
  13.250   1.3715   0.05349   0.04481  -0.0140   0.0710   1.0000
  13.500   1.3696   0.05620   0.04786  -0.0118   0.0695   1.0000
  13.750   1.3665   0.05907   0.05101  -0.0099   0.0680   1.0000
  14.000   1.3641   0.06194   0.05411  -0.0083   0.0664   1.0000
  14.250   1.3632   0.06472   0.05704  -0.0071   0.0648   1.0000
  14.500   1.3692   0.06763   0.05999  -0.0063   0.0630   1.0000
  14.750   1.3671   0.07212   0.06463  -0.0055   0.0620   1.0000
  15.000   1.3473   0.07630   0.06912  -0.0044   0.0618   1.0000
  15.250   1.3258   0.08098   0.07408  -0.0040   0.0618   1.0000
  15.500   1.3028   0.08617   0.07955  -0.0044   0.0618   1.0000
  15.750   1.2785   0.09192   0.08554  -0.0055   0.0618   1.0000
  16.000   1.2534   0.09824   0.09209  -0.0074   0.0620   1.0000
  16.250   1.2201   0.10550   0.09964  -0.0110   0.0624   1.0000
  16.500   1.0532   0.14296   0.13773  -0.0374   0.0717   1.0000
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