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CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: CLARK V AIRFOIL (clarkv-il)
Reynolds number: 50,000
Max Cl/Cd: 35.49 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-clarkv-il-50000.txt
Download as CSV file: xf-clarkv-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3884   0.10313   0.09630  -0.0199   1.0000   0.3075
  -7.750  -0.3981   0.10103   0.09429  -0.0178   1.0000   0.3165
  -7.500  -0.4211   0.10054   0.09395  -0.0147   1.0000   0.3277
  -7.250  -0.4050   0.09661   0.09002  -0.0129   1.0000   0.3400
  -7.000  -0.4093   0.09421   0.08768  -0.0103   1.0000   0.3510
  -6.750  -0.4586   0.09524   0.08896  -0.0049   1.0000   0.3602
  -6.500  -0.4535   0.09228   0.08603  -0.0022   1.0000   0.3755
  -6.250  -0.4596   0.09010   0.08392   0.0010   1.0000   0.3915
  -6.000  -0.4732   0.08838   0.08230   0.0043   1.0000   0.4083
  -5.750  -0.4453   0.08427   0.07815   0.0072   1.0000   0.4305
  -5.500  -0.4483   0.08208   0.07603   0.0107   1.0000   0.4500
  -5.000  -0.4817   0.05571   0.04851  -0.0336   1.0000   0.1907
  -4.750  -0.4577   0.04914   0.04105  -0.0377   1.0000   0.1701
  -4.500  -0.4361   0.04548   0.03708  -0.0384   1.0000   0.1652
  -4.250  -0.4108   0.04174   0.03268  -0.0397   1.0000   0.1608
  -4.000  -0.3870   0.03944   0.02997  -0.0400   1.0000   0.1633
  -3.750  -0.3620   0.03733   0.02741  -0.0402   1.0000   0.1662
  -3.500  -0.3359   0.03540   0.02500  -0.0404   1.0000   0.1683
  -3.250  -0.3094   0.03384   0.02291  -0.0404   1.0000   0.1719
  -3.000  -0.2862   0.03257   0.02167  -0.0401   1.0000   0.1808
  -2.750  -0.2611   0.03146   0.02034  -0.0399   1.0000   0.1911
  -2.500  -0.2356   0.03049   0.01921  -0.0395   1.0000   0.2038
  -2.250  -0.2117   0.02966   0.01851  -0.0391   1.0000   0.2255
  -2.000  -0.1858   0.02890   0.01783  -0.0389   1.0000   0.2619
  -1.750  -0.1577   0.02787   0.01738  -0.0391   1.0000   0.3503
  -1.500  -0.1415   0.02475   0.01719  -0.0331   1.0000   0.9552
  -1.250  -0.1202   0.02499   0.01673  -0.0332   1.0000   1.0000
  -1.000  -0.0986   0.02545   0.01674  -0.0332   1.0000   1.0000
  -0.750  -0.0776   0.02595   0.01690  -0.0331   1.0000   1.0000
  -0.500  -0.0570   0.02650   0.01715  -0.0330   1.0000   1.0000
  -0.250  -0.0367   0.02709   0.01748  -0.0329   1.0000   1.0000
   0.000  -0.0167   0.02772   0.01789  -0.0328   1.0000   1.0000
   0.250   0.0030   0.02840   0.01837  -0.0327   1.0000   1.0000
   0.500   0.0225   0.02913   0.01892  -0.0326   1.0000   1.0000
   0.750   0.0418   0.02989   0.01953  -0.0325   1.0000   1.0000
   1.000   0.0607   0.03071   0.02022  -0.0325   1.0000   1.0000
   1.250   0.0794   0.03157   0.02096  -0.0325   1.0000   1.0000
   1.500   0.0977   0.03249   0.02177  -0.0325   1.0000   1.0000
   1.750   0.1474   0.03423   0.02339  -0.0384   0.9864   1.0000
   2.000   0.1995   0.03595   0.02500  -0.0445   0.9694   1.0000
   2.250   0.2398   0.03720   0.02618  -0.0483   0.9520   1.0000
   2.500   0.2802   0.03840   0.02734  -0.0519   0.9349   1.0000
   2.750   0.3205   0.03952   0.02844  -0.0553   0.9181   1.0000
   3.000   0.3610   0.04057   0.02948  -0.0585   0.9014   1.0000
   3.250   0.4025   0.04155   0.03047  -0.0617   0.8851   1.0000
   3.500   0.4343   0.04236   0.03130  -0.0632   0.8676   1.0000
   3.750   0.4648   0.04312   0.03211  -0.0644   0.8494   1.0000
   4.000   0.4992   0.04382   0.03288  -0.0660   0.8314   1.0000
   4.250   0.5373   0.04438   0.03351  -0.0679   0.8135   1.0000
   4.500   0.5794   0.04471   0.03393  -0.0700   0.7959   1.0000
   4.750   0.6098   0.04512   0.03445  -0.0704   0.7762   1.0000
   5.000   0.6409   0.04539   0.03483  -0.0706   0.7557   1.0000
   5.250   0.6843   0.04501   0.03461  -0.0718   0.7367   1.0000
   5.500   0.7349   0.04396   0.03373  -0.0732   0.7189   1.0000
   5.750   0.7563   0.04419   0.03409  -0.0716   0.6960   1.0000
   6.000   0.8021   0.04284   0.03295  -0.0718   0.6774   1.0000
   6.250   0.8555   0.04064   0.03098  -0.0722   0.6603   1.0000
   6.500   0.9265   0.03739   0.02803  -0.0743   0.6427   1.0000
   6.750   0.9605   0.03650   0.02731  -0.0731   0.6178   1.0000
   7.000   1.0203   0.03411   0.02512  -0.0744   0.5915   1.0000
   7.250   1.0645   0.03286   0.02393  -0.0742   0.5600   1.0000
   7.500   1.0986   0.03232   0.02339  -0.0732   0.5263   1.0000
   7.750   1.1287   0.03221   0.02323  -0.0718   0.4925   1.0000
   8.000   1.1547   0.03254   0.02346  -0.0703   0.4601   1.0000
   8.250   1.1763   0.03327   0.02413  -0.0685   0.4299   1.0000
   8.500   1.1955   0.03423   0.02507  -0.0664   0.4011   1.0000
   8.750   1.2143   0.03536   0.02616  -0.0645   0.3733   1.0000
   9.000   1.2330   0.03658   0.02729  -0.0625   0.3456   1.0000
   9.250   1.2506   0.03784   0.02841  -0.0605   0.3173   1.0000
   9.500   1.2656   0.03908   0.02948  -0.0581   0.2887   1.0000
   9.750   1.2674   0.04047   0.03102  -0.0540   0.2638   1.0000
  10.000   1.2719   0.04174   0.03221  -0.0504   0.2380   1.0000
  10.250   1.2773   0.04305   0.03331  -0.0470   0.2120   1.0000
  10.500   1.2766   0.04482   0.03511  -0.0429   0.1894   1.0000
  10.750   1.2815   0.04695   0.03711  -0.0398   0.1672   1.0000
  11.000   1.2834   0.04941   0.03967  -0.0364   0.1504   1.0000
  11.250   1.2888   0.05206   0.04238  -0.0336   0.1372   1.0000
  11.500   1.3002   0.05492   0.04528  -0.0318   0.1263   1.0000
  11.750   1.2929   0.05781   0.04856  -0.0279   0.1206   1.0000
  12.000   1.3049   0.06089   0.05163  -0.0265   0.1135   1.0000
  12.250   1.2887   0.06444   0.05562  -0.0224   0.1117   1.0000
  12.500   1.2710   0.06827   0.05983  -0.0188   0.1103   1.0000
  12.750   1.2499   0.07242   0.06430  -0.0159   0.1095   1.0000
  13.000   1.2245   0.07707   0.06926  -0.0136   0.1094   1.0000
  13.250   1.1945   0.08246   0.07493  -0.0124   0.1099   1.0000
  13.500   1.1614   0.08876   0.08146  -0.0126   0.1110   1.0000
  13.750   1.1276   0.09598   0.08886  -0.0142   0.1123   1.0000
  14.000   1.0955   0.10407   0.09704  -0.0170   0.1135   1.0000
  14.250   1.0673   0.11278   0.10582  -0.0207   0.1145   1.0000
  14.500   0.8971   0.16139   0.15405  -0.0560   0.1631   1.0000
  14.750   0.8944   0.16826   0.16091  -0.0589   0.1668   1.0000
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