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SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SD7003-085-88 (sd7003-il)
Reynolds number: 50,000
Max Cl/Cd: 29.32 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7003-il-50000.txt
Download as CSV file: xf-sd7003-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7003-085-88                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4952   0.10034   0.09346   0.0092   1.0000   0.2808
  -8.000  -0.4923   0.09715   0.09033   0.0092   1.0000   0.2943
  -7.750  -0.4895   0.09396   0.08720   0.0093   1.0000   0.3084
  -7.250  -0.4816   0.08744   0.08077   0.0101   1.0000   0.3379
  -7.000  -0.4743   0.08438   0.07776   0.0113   1.0000   0.3600
  -6.750  -0.4777   0.08177   0.07525   0.0124   1.0000   0.3804
  -6.500  -0.4618   0.07787   0.07134   0.0137   1.0000   0.3992
  -6.250  -0.4576   0.07472   0.06825   0.0147   1.0000   0.4155
  -6.000  -0.5038   0.04834   0.04068  -0.0336   1.0000   0.1408
  -5.750  -0.4874   0.04356   0.03541  -0.0346   1.0000   0.1412
  -5.500  -0.4683   0.03918   0.03025  -0.0353   1.0000   0.1432
  -5.250  -0.4472   0.03586   0.02688  -0.0348   1.0000   0.1481
  -5.000  -0.4242   0.03291   0.02321  -0.0346   1.0000   0.1575
  -4.750  -0.4011   0.03035   0.02057  -0.0338   1.0000   0.1674
  -4.500  -0.3774   0.02822   0.01818  -0.0331   1.0000   0.1828
  -4.250  -0.3528   0.02623   0.01592  -0.0323   1.0000   0.1996
  -4.000  -0.3287   0.02449   0.01415  -0.0314   1.0000   0.2201
  -3.750  -0.3046   0.02301   0.01264  -0.0304   1.0000   0.2477
  -3.500  -0.2806   0.02155   0.01130  -0.0293   1.0000   0.2809
  -3.250  -0.2573   0.02020   0.01014  -0.0280   1.0000   0.3342
  -3.000  -0.2359   0.01867   0.00919  -0.0263   1.0000   0.4229
  -2.750  -0.2221   0.01715   0.00877  -0.0222   1.0000   0.5774
  -2.500  -0.2185   0.01642   0.00883  -0.0145   1.0000   0.7412
  -2.250  -0.1949   0.01612   0.00869  -0.0088   1.0000   0.9125
  -2.000  -0.0848   0.01570   0.00744  -0.0246   1.0000   1.0000
  -1.750  -0.0821   0.01541   0.00698  -0.0218   1.0000   1.0000
  -1.500  -0.0722   0.01529   0.00666  -0.0198   1.0000   1.0000
  -1.250  -0.0572   0.01527   0.00644  -0.0185   1.0000   1.0000
  -1.000  -0.0401   0.01533   0.00631  -0.0175   1.0000   1.0000
  -0.750  -0.0222   0.01545   0.00627  -0.0166   1.0000   1.0000
  -0.500  -0.0040   0.01564   0.00629  -0.0159   1.0000   1.0000
  -0.250   0.0139   0.01589   0.00642  -0.0152   1.0000   1.0000
   0.000   0.0315   0.01621   0.00663  -0.0147   1.0000   1.0000
   0.250   0.0487   0.01661   0.00695  -0.0142   1.0000   1.0000
   0.500   0.0652   0.01711   0.00735  -0.0139   1.0000   1.0000
   0.750   0.0812   0.01769   0.00788  -0.0138   1.0000   1.0000
   1.000   0.0965   0.01838   0.00852  -0.0139   1.0000   1.0000
   1.250   0.1671   0.01954   0.00968  -0.0237   0.9728   1.0000
   1.500   0.2442   0.02031   0.01051  -0.0338   0.9415   1.0000
   1.750   0.3133   0.02063   0.01095  -0.0414   0.9080   1.0000
   2.000   0.3804   0.02063   0.01109  -0.0477   0.8753   1.0000
   2.250   0.4344   0.02049   0.01107  -0.0507   0.8420   1.0000
   2.500   0.4767   0.02037   0.01100  -0.0512   0.8088   1.0000
   2.750   0.5058   0.02051   0.01114  -0.0497   0.7731   1.0000
   3.000   0.5329   0.02067   0.01130  -0.0477   0.7387   1.0000
   3.250   0.5585   0.02086   0.01143  -0.0454   0.7052   1.0000
   3.500   0.5814   0.02125   0.01178  -0.0431   0.6697   1.0000
   3.750   0.6048   0.02164   0.01210  -0.0409   0.6353   1.0000
   4.000   0.6284   0.02205   0.01244  -0.0388   0.6022   1.0000
   4.250   0.6514   0.02260   0.01292  -0.0369   0.5682   1.0000
   4.500   0.6745   0.02322   0.01349  -0.0352   0.5346   1.0000
   4.750   0.6979   0.02388   0.01407  -0.0335   0.5026   1.0000
   5.000   0.7213   0.02460   0.01474  -0.0319   0.4714   1.0000
   5.250   0.7447   0.02542   0.01551  -0.0305   0.4415   1.0000
   5.500   0.7680   0.02633   0.01638  -0.0292   0.4126   1.0000
   5.750   0.7910   0.02734   0.01741  -0.0279   0.3850   1.0000
   6.000   0.8141   0.02847   0.01857  -0.0268   0.3592   1.0000
   6.250   0.8379   0.02951   0.01950  -0.0256   0.3353   1.0000
   6.500   0.8595   0.03099   0.02117  -0.0246   0.3118   1.0000
   6.750   0.8824   0.03229   0.02245  -0.0234   0.2903   1.0000
   7.000   0.9030   0.03408   0.02451  -0.0224   0.2701   1.0000
   7.250   0.9254   0.03549   0.02590  -0.0213   0.2505   1.0000
   7.500   0.9467   0.03745   0.02794  -0.0203   0.2337   1.0000
   7.750   0.9634   0.03974   0.03058  -0.0192   0.2166   1.0000
   8.000   0.9808   0.04233   0.03342  -0.0181   0.2025   1.0000
   8.250   0.9960   0.04487   0.03620  -0.0170   0.1879   1.0000
   8.500   1.0125   0.04763   0.03915  -0.0159   0.1757   1.0000
   8.750   1.0285   0.05015   0.04176  -0.0148   0.1628   1.0000
   9.000   1.0200   0.05590   0.04830  -0.0140   0.1585   1.0000
   9.250   1.0360   0.05852   0.05091  -0.0129   0.1481   1.0000
   9.500   1.0184   0.06484   0.05775  -0.0129   0.1470   1.0000
   9.750   0.9971   0.07137   0.06457  -0.0137   0.1471   1.0000
  10.000   0.9750   0.07792   0.07126  -0.0151   0.1480   1.0000
  10.250   0.9540   0.08433   0.07770  -0.0168   0.1489   1.0000
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