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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 200,000
Max Cl/Cd: 37.31 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1010-il-200000.txt
Download as CSV file: xf-s1010-il-200000.csv

 
  
       XFOIL         Version 6.96
  
 Calculated polar for: S1010 HPV airfoil                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5767   0.09424   0.09095   0.0091   1.0000   0.0594
  -9.250  -0.5864   0.08850   0.08524   0.0055   1.0000   0.0611
  -9.000  -0.6729   0.09063   0.08721   0.0073   1.0000   0.0563
  -8.750  -0.6770   0.08591   0.08250   0.0042   1.0000   0.0575
  -8.500  -0.6859   0.08067   0.07734  -0.0001   1.0000   0.0585
  -8.250  -0.7587   0.05187   0.04793  -0.0159   1.0000   0.0278
  -8.000  -0.7635   0.04541   0.04111  -0.0160   1.0000   0.0273
  -7.500  -0.7543   0.03503   0.02955  -0.0141   1.0000   0.0287
  -7.250  -0.7448   0.02984   0.02381  -0.0129   1.0000   0.0297
  -7.000  -0.7275   0.02671   0.02029  -0.0117   1.0000   0.0308
  -6.750  -0.7070   0.02452   0.01780  -0.0107   1.0000   0.0327
  -6.500  -0.6845   0.02293   0.01590  -0.0097   1.0000   0.0360
  -6.250  -0.6611   0.02154   0.01413  -0.0086   1.0000   0.0392
  -6.000  -0.6393   0.01914   0.01156  -0.0077   1.0000   0.0429
  -5.750  -0.6150   0.01832   0.01059  -0.0069   1.0000   0.0485
  -5.500  -0.5918   0.01679   0.00896  -0.0059   1.0000   0.0544
  -5.250  -0.5673   0.01601   0.00804  -0.0050   1.0000   0.0626
  -5.000  -0.5437   0.01519   0.00722  -0.0042   1.0000   0.0753
  -4.750  -0.5199   0.01450   0.00650  -0.0034   1.0000   0.0888
  -4.500  -0.4961   0.01391   0.00589  -0.0026   1.0000   0.1026
  -4.250  -0.4726   0.01334   0.00537  -0.0018   1.0000   0.1178
  -4.000  -0.4492   0.01282   0.00491  -0.0009   1.0000   0.1336
  -3.750  -0.4258   0.01232   0.00446   0.0000   1.0000   0.1505
  -3.500  -0.4023   0.01188   0.00405   0.0009   1.0000   0.1713
  -3.250  -0.3796   0.01134   0.00363   0.0018   1.0000   0.1945
  -3.000  -0.3568   0.01085   0.00329   0.0028   1.0000   0.2256
  -2.750  -0.3348   0.01028   0.00299   0.0037   1.0000   0.2735
  -2.500  -0.3142   0.00956   0.00273   0.0049   1.0000   0.3658
  -2.250  -0.2981   0.00849   0.00253   0.0070   1.0000   0.5528
  -2.000  -0.2868   0.00769   0.00271   0.0116   1.0000   0.7963
  -1.750  -0.2627   0.00767   0.00286   0.0137   1.0000   0.8938
  -1.500  -0.2131   0.00786   0.00301   0.0103   1.0000   0.9493
  -1.250  -0.1492   0.00802   0.00303   0.0034   1.0000   0.9764
  -1.000  -0.0836   0.00804   0.00294  -0.0041   1.0000   0.9925
  -0.750  -0.0378   0.00795   0.00280  -0.0080   1.0000   1.0000
  -0.500  -0.0239   0.00788   0.00271  -0.0056   1.0000   1.0000
  -0.250  -0.0114   0.00784   0.00267  -0.0029   1.0000   1.0000
   0.000   0.0000   0.00783   0.00266   0.0000   1.0000   1.0000
   0.250   0.0114   0.00784   0.00267   0.0029   1.0000   1.0000
   0.500   0.0239   0.00788   0.00271   0.0056   1.0000   1.0000
   0.750   0.0379   0.00795   0.00280   0.0080   1.0000   1.0000
   1.000   0.0840   0.00804   0.00294   0.0041   0.9924   1.0000
   1.250   0.1486   0.00802   0.00303  -0.0033   0.9767   1.0000
   1.500   0.2133   0.00786   0.00301  -0.0103   0.9491   1.0000
   1.750   0.2627   0.00767   0.00286  -0.0137   0.8942   1.0000
   2.000   0.2869   0.00769   0.00271  -0.0116   0.7965   1.0000
   2.250   0.2982   0.00849   0.00253  -0.0070   0.5527   1.0000
   2.500   0.3143   0.00956   0.00273  -0.0049   0.3661   1.0000
   2.750   0.3349   0.01028   0.00299  -0.0038   0.2738   1.0000
   3.000   0.3569   0.01085   0.00329  -0.0028   0.2257   1.0000
   3.250   0.3797   0.01134   0.00363  -0.0018   0.1946   1.0000
   3.500   0.4023   0.01188   0.00405  -0.0009   0.1713   1.0000
   3.750   0.4258   0.01232   0.00446   0.0000   0.1505   1.0000
   4.000   0.4492   0.01282   0.00491   0.0009   0.1336   1.0000
   4.250   0.4727   0.01334   0.00537   0.0018   0.1178   1.0000
   4.500   0.4961   0.01392   0.00589   0.0026   0.1025   1.0000
   4.750   0.5199   0.01451   0.00650   0.0034   0.0888   1.0000
   5.000   0.5437   0.01519   0.00722   0.0042   0.0753   1.0000
   5.250   0.5674   0.01600   0.00804   0.0050   0.0625   1.0000
   5.500   0.5919   0.01679   0.00896   0.0059   0.0544   1.0000
   5.750   0.6150   0.01832   0.01058   0.0069   0.0486   1.0000
   6.000   0.6394   0.01914   0.01155   0.0077   0.0429   1.0000
   6.250   0.6611   0.02153   0.01412   0.0086   0.0392   1.0000
   6.500   0.6845   0.02296   0.01594   0.0097   0.0361   1.0000
   6.750   0.7070   0.02453   0.01781   0.0107   0.0327   1.0000
   7.000   0.7275   0.02673   0.02032   0.0117   0.0308   1.0000
   7.250   0.7449   0.02984   0.02380   0.0129   0.0297   1.0000
   7.500   0.7555   0.03469   0.02918   0.0141   0.0289   1.0000
   7.750   0.7595   0.04031   0.03546   0.0153   0.0279   1.0000
   8.000   0.7636   0.04538   0.04104   0.0160   0.0276   1.0000
   8.250   0.7591   0.05181   0.04784   0.0159   0.0279   1.0000
   8.500   0.6863   0.08070   0.07738   0.0000   0.0584   1.0000
   8.750   0.6775   0.08597   0.08259  -0.0043   0.0577   1.0000
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