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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 100,000
Max Cl/Cd: 29.89 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1010-il-100000-n5.txt
Download as CSV file: xf-s1010-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7126   0.08509   0.08025   0.0030   1.0000   0.0240
  -9.250  -0.7236   0.07817   0.07346  -0.0020   1.0000   0.0238
  -9.000  -0.7392   0.07043   0.06577  -0.0084   1.0000   0.0234
  -8.750  -0.7561   0.06238   0.05761  -0.0124   1.0000   0.0230
  -8.500  -0.7701   0.05484   0.04981  -0.0148   1.0000   0.0228
  -8.250  -0.7783   0.04797   0.04250  -0.0157   1.0000   0.0229
  -8.000  -0.7791   0.04185   0.03577  -0.0154   1.0000   0.0235
  -7.750  -0.7720   0.03692   0.03016  -0.0145   1.0000   0.0247
  -7.500  -0.7591   0.03333   0.02598  -0.0135   1.0000   0.0270
  -7.250  -0.7408   0.03171   0.02423  -0.0129   1.0000   0.0297
  -7.000  -0.7220   0.02909   0.02110  -0.0118   1.0000   0.0319
  -6.750  -0.7014   0.02662   0.01816  -0.0108   1.0000   0.0345
  -6.500  -0.6795   0.02480   0.01596  -0.0099   1.0000   0.0385
  -6.250  -0.6572   0.02364   0.01473  -0.0092   1.0000   0.0429
  -6.000  -0.6340   0.02206   0.01287  -0.0082   1.0000   0.0470
  -5.750  -0.6114   0.02065   0.01134  -0.0073   1.0000   0.0519
  -5.500  -0.5879   0.01967   0.01022  -0.0064   1.0000   0.0595
  -5.250  -0.5644   0.01892   0.00943  -0.0058   1.0000   0.0705
  -5.000  -0.5408   0.01818   0.00858  -0.0050   1.0000   0.0822
  -4.750  -0.5170   0.01757   0.00792  -0.0043   1.0000   0.0959
  -4.500  -0.4933   0.01694   0.00726  -0.0035   1.0000   0.1096
  -4.250  -0.4696   0.01636   0.00666  -0.0027   1.0000   0.1244
  -4.000  -0.4461   0.01577   0.00606  -0.0019   1.0000   0.1382
  -3.750  -0.4226   0.01525   0.00557  -0.0011   1.0000   0.1560
  -3.500  -0.3993   0.01474   0.00512  -0.0002   1.0000   0.1763
  -3.250  -0.3761   0.01425   0.00466   0.0007   1.0000   0.1998
  -3.000  -0.3532   0.01376   0.00429   0.0016   1.0000   0.2316
  -2.750  -0.3306   0.01325   0.00397   0.0025   1.0000   0.2749
  -2.500  -0.3087   0.01266   0.00369   0.0036   1.0000   0.3412
  -2.250  -0.2881   0.01192   0.00345   0.0049   1.0000   0.4513
  -2.000  -0.2703   0.01101   0.00335   0.0073   1.0000   0.6335
  -1.750  -0.2472   0.01068   0.00355   0.0098   1.0000   0.8138
  -1.500  -0.2109   0.01067   0.00359   0.0092   1.0000   0.8932
  -1.250  -0.1650   0.01072   0.00354   0.0061   1.0000   0.9414
  -1.000  -0.1129   0.01074   0.00347   0.0014   1.0000   0.9727
  -0.750  -0.0561   0.01069   0.00333  -0.0046   1.0000   0.9962
  -0.500  -0.0318   0.01064   0.00323  -0.0042   1.0000   1.0000
  -0.250  -0.0159   0.01060   0.00319  -0.0021   1.0000   1.0000
   0.000   0.0000   0.01059   0.00317   0.0000   1.0000   1.0000
   0.250   0.0159   0.01060   0.00319   0.0021   1.0000   1.0000
   0.500   0.0319   0.01063   0.00323   0.0042   1.0000   1.0000
   0.750   0.0563   0.01069   0.00333   0.0045   0.9960   1.0000
   1.000   0.1126   0.01074   0.00347  -0.0013   0.9729   1.0000
   1.250   0.1647   0.01072   0.00354  -0.0060   0.9416   1.0000
   1.500   0.2108   0.01067   0.00359  -0.0091   0.8933   1.0000
   1.750   0.2470   0.01067   0.00355  -0.0098   0.8143   1.0000
   2.000   0.2701   0.01101   0.00335  -0.0073   0.6335   1.0000
   2.250   0.2879   0.01192   0.00345  -0.0048   0.4516   1.0000
   2.500   0.3085   0.01266   0.00369  -0.0035   0.3418   1.0000
   2.750   0.3304   0.01325   0.00397  -0.0025   0.2752   1.0000
   3.000   0.3530   0.01376   0.00429  -0.0015   0.2317   1.0000
   3.250   0.3759   0.01425   0.00465  -0.0006   0.1998   1.0000
   3.500   0.3992   0.01474   0.00512   0.0003   0.1764   1.0000
   3.750   0.4224   0.01525   0.00556   0.0011   0.1559   1.0000
   4.000   0.4459   0.01577   0.00606   0.0019   0.1383   1.0000
   4.250   0.4694   0.01636   0.00666   0.0028   0.1245   1.0000
   4.500   0.4931   0.01694   0.00726   0.0036   0.1095   1.0000
   4.750   0.5169   0.01756   0.00792   0.0043   0.0960   1.0000
   5.000   0.5407   0.01818   0.00858   0.0050   0.0822   1.0000
   5.250   0.5644   0.01892   0.00943   0.0058   0.0705   1.0000
   5.500   0.5879   0.01967   0.01022   0.0064   0.0595   1.0000
   5.750   0.6114   0.02066   0.01134   0.0073   0.0519   1.0000
   6.000   0.6341   0.02206   0.01287   0.0082   0.0470   1.0000
   6.250   0.6573   0.02364   0.01473   0.0092   0.0429   1.0000
   6.500   0.6796   0.02481   0.01597   0.0098   0.0385   1.0000
   6.750   0.7016   0.02663   0.01817   0.0107   0.0344   1.0000
   7.000   0.7223   0.02910   0.02111   0.0118   0.0319   1.0000
   7.250   0.7411   0.03173   0.02424   0.0128   0.0297   1.0000
   7.500   0.7594   0.03337   0.02602   0.0135   0.0270   1.0000
   7.750   0.7723   0.03698   0.03022   0.0144   0.0247   1.0000
   8.000   0.7794   0.04194   0.03588   0.0153   0.0234   1.0000
   8.250   0.7788   0.04802   0.04254   0.0155   0.0229   1.0000
   8.500   0.7706   0.05493   0.04990   0.0146   0.0228   1.0000
   8.750   0.7564   0.06258   0.05782   0.0122   0.0230   1.0000
   9.000   0.7399   0.07057   0.06591   0.0081   0.0234   1.0000
   9.250   0.7244   0.07832   0.07362   0.0017   0.0238   1.0000
   9.500   0.7140   0.08509   0.08026  -0.0032   0.0241   1.0000
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