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NASA SC(2)-0518 AIRFOIL (sc20518-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NASA SC(2)-0518 AIRFOIL (sc20518-il)
Reynolds number: 50,000
Max Cl/Cd: 26.02 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc20518-il-50000.txt
Download as CSV file: xf-sc20518-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0518 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6573   0.08007   0.07115  -0.0524   1.0000   0.2153
 -10.500  -0.7055   0.07269   0.06376  -0.0523   1.0000   0.2135
 -10.250  -0.7662   0.06699   0.05804  -0.0491   1.0000   0.2112
 -10.000  -0.8184   0.06230   0.05325  -0.0457   1.0000   0.2097
  -9.750  -0.8516   0.05831   0.04907  -0.0429   1.0000   0.2095
  -9.500  -0.8703   0.05487   0.04538  -0.0406   1.0000   0.2105
  -9.250  -0.8802   0.05173   0.04190  -0.0388   1.0000   0.2126
  -9.000  -0.8843   0.04874   0.03849  -0.0377   1.0000   0.2153
  -8.750  -0.8690   0.04683   0.03668  -0.0362   1.0000   0.2196
  -8.500  -0.8552   0.04512   0.03494  -0.0349   1.0000   0.2244
  -8.250  -0.8437   0.04306   0.03264  -0.0341   1.0000   0.2295
  -8.000  -0.8293   0.04118   0.03061  -0.0332   1.0000   0.2353
  -7.750  -0.8117   0.03996   0.02947  -0.0318   1.0000   0.2424
  -7.500  -0.7954   0.03828   0.02749  -0.0315   1.0000   0.2504
  -7.250  -0.7765   0.03732   0.02681  -0.0294   1.0000   0.2590
  -7.000  -0.7584   0.03606   0.02547  -0.0285   1.0000   0.2703
  -6.750  -0.7400   0.03516   0.02471  -0.0269   1.0000   0.2833
  -6.500  -0.7223   0.03432   0.02409  -0.0249   1.0000   0.2988
  -6.250  -0.7050   0.03343   0.02340  -0.0232   1.0000   0.3192
  -6.000  -0.6891   0.03261   0.02294  -0.0210   1.0000   0.3459
  -5.750  -0.6749   0.03205   0.02296  -0.0182   1.0000   0.3846
  -5.500  -0.6630   0.03290   0.02455  -0.0129   1.0000   0.4378
  -5.250  -0.6495   0.03642   0.02849  -0.0045   1.0000   0.4797
  -5.000  -0.6319   0.04011   0.03222   0.0023   1.0000   0.5181
  -4.750  -0.6159   0.04298   0.03501   0.0075   1.0000   0.5534
  -4.500  -0.5978   0.04627   0.03826   0.0140   1.0000   0.5749
  -4.250  -0.5785   0.04903   0.04095   0.0198   1.0000   0.5964
  -4.000  -0.5584   0.05121   0.04306   0.0249   1.0000   0.6182
  -3.750  -0.5384   0.05280   0.04458   0.0291   1.0000   0.6403
  -3.500  -0.5182   0.05392   0.04564   0.0328   1.0000   0.6624
  -3.250  -0.4974   0.05474   0.04638   0.0359   1.0000   0.6849
  -3.000  -0.4746   0.05535   0.04693   0.0385   1.0000   0.7084
  -2.750  -0.4498   0.05584   0.04736   0.0407   1.0000   0.7347
  -2.500  -0.4375   0.05595   0.04742   0.0436   1.0000   0.7617
  -2.250  -0.3711   0.05646   0.04784   0.0404   1.0000   0.7995
  -2.000  -0.3110   0.05611   0.04740   0.0360   1.0000   0.8354
  -1.750  -0.2637   0.05522   0.04644   0.0324   1.0000   0.8644
  -1.500  -0.2462   0.05444   0.04561   0.0325   1.0000   0.8831
  -1.250  -0.2279   0.05361   0.04475   0.0323   1.0000   0.8978
  -1.000  -0.2080   0.05283   0.04394   0.0315   1.0000   0.9105
  -0.750  -0.1901   0.05213   0.04322   0.0310   1.0000   0.9211
  -0.500  -0.1930   0.05166   0.04274   0.0338   1.0000   0.9272
  -0.250  -0.1682   0.05108   0.04215   0.0319   1.0000   0.9359
   0.000  -0.1708   0.05070   0.04176   0.0347   1.0000   0.9405
   0.250  -0.1471   0.05032   0.04139   0.0329   1.0000   0.9471
   0.500  -0.1444   0.05003   0.04110   0.0346   1.0000   0.9501
   0.750  -0.1462   0.04975   0.04084   0.0371   1.0000   0.9526
   1.000  -0.1312   0.04961   0.04071   0.0366   1.0000   0.9569
   1.250  -0.1216   0.04953   0.04066   0.0370   1.0000   0.9601
   1.500  -0.0641   0.05017   0.04134   0.0285   0.9852   0.9644
   1.750   0.0287   0.05102   0.04226   0.0140   0.9596   0.9701
   2.000   0.0972   0.05132   0.04265   0.0045   0.9346   0.9746
   2.250   0.1647   0.05143   0.04284  -0.0041   0.9084   0.9784
   2.500   0.2766   0.05059   0.04216  -0.0190   0.8743   0.9845
   2.750   0.3298   0.04976   0.04145  -0.0235   0.8443   0.9870
   3.000   0.4446   0.04702   0.03892  -0.0359   0.8138   0.9914
   3.250   0.5571   0.04312   0.03529  -0.0469   0.7786   0.9973
   3.500   0.6686   0.03769   0.03012  -0.0556   0.7471   1.0000
   3.750   0.7182   0.03415   0.02670  -0.0548   0.7059   1.0000
   4.000   0.7505   0.03134   0.02387  -0.0514   0.6431   1.0000
   4.250   0.7725   0.02969   0.02161  -0.0466   0.5326   1.0000
   4.500   0.7840   0.03023   0.02113  -0.0425   0.4396   1.0000
   4.750   0.7982   0.03135   0.02162  -0.0402   0.3858   1.0000
   5.000   0.8173   0.03239   0.02229  -0.0389   0.3501   1.0000
   5.250   0.8398   0.03337   0.02294  -0.0383   0.3244   1.0000
   5.500   0.8602   0.03432   0.02378  -0.0374   0.3048   1.0000
   5.750   0.8818   0.03530   0.02462  -0.0367   0.2889   1.0000
   6.000   0.9002   0.03627   0.02559  -0.0355   0.2760   1.0000
   6.250   0.9161   0.03738   0.02679  -0.0340   0.2653   1.0000
   6.500   0.9387   0.03856   0.02776  -0.0336   0.2555   1.0000
   6.750   0.9464   0.03976   0.02930  -0.0308   0.2482   1.0000
   7.000   0.9629   0.04095   0.03045  -0.0295   0.2407   1.0000
   7.250   0.9717   0.04243   0.03211  -0.0270   0.2350   1.0000
   7.500   0.9763   0.04387   0.03380  -0.0240   0.2299   1.0000
   7.750   0.9879   0.04522   0.03516  -0.0220   0.2244   1.0000
   8.000   0.9969   0.04696   0.03694  -0.0198   0.2201   1.0000
   8.250   0.9874   0.04860   0.03897  -0.0148   0.2173   1.0000
   8.500   0.9775   0.05030   0.04097  -0.0100   0.2148   1.0000
   8.750   0.9666   0.05196   0.04287  -0.0052   0.2125   1.0000
   9.000   0.9563   0.05357   0.04466  -0.0006   0.2103   1.0000
   9.250   0.9573   0.05512   0.04625   0.0024   0.2072   1.0000
   9.500   0.9676   0.05737   0.04846   0.0037   0.2039   1.0000
   9.750   0.9469   0.06004   0.05150   0.0080   0.2031   1.0000
  10.000   0.9266   0.06354   0.05537   0.0110   0.2027   1.0000
  10.250   0.8992   0.06766   0.05982   0.0137   0.2027   1.0000
  10.500   0.8683   0.07279   0.06524   0.0150   0.2033   1.0000
  10.750   0.8383   0.07914   0.07181   0.0143   0.2040   1.0000
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