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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 69.21 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1010-il-1000000-n5.txt
Download as CSV file: xf-s1010-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.9092   0.10699   0.10526   0.0181   1.0000   0.0025
 -13.500  -1.0247   0.07966   0.07783   0.0013   1.0000   0.0021
 -13.250  -1.1632   0.04517   0.04300  -0.0243   1.0000   0.0017
 -13.000  -1.1967   0.03985   0.03746  -0.0231   1.0000   0.0018
 -12.750  -1.2085   0.03627   0.03365  -0.0212   1.0000   0.0018
 -12.500  -1.2096   0.03320   0.03034  -0.0198   1.0000   0.0018
 -12.250  -1.2058   0.03044   0.02733  -0.0184   1.0000   0.0019
 -12.000  -1.1963   0.02823   0.02490  -0.0173   1.0000   0.0019
 -11.750  -1.1828   0.02646   0.02294  -0.0163   1.0000   0.0020
 -11.500  -1.1668   0.02495   0.02127  -0.0153   1.0000   0.0021
 -11.250  -1.1494   0.02357   0.01972  -0.0145   1.0000   0.0022
 -11.000  -1.1301   0.02244   0.01846  -0.0138   1.0000   0.0023
 -10.750  -1.1106   0.02128   0.01714  -0.0130   1.0000   0.0024
 -10.500  -1.0907   0.02011   0.01579  -0.0122   1.0000   0.0024
 -10.250  -1.0694   0.01916   0.01470  -0.0116   1.0000   0.0025
 -10.000  -1.0477   0.01822   0.01362  -0.0109   1.0000   0.0026
  -9.750  -1.0253   0.01739   0.01267  -0.0103   1.0000   0.0028
  -9.500  -1.0026   0.01657   0.01172  -0.0097   1.0000   0.0029
  -9.250  -0.9795   0.01583   0.01086  -0.0091   1.0000   0.0030
  -9.000  -0.9560   0.01513   0.01005  -0.0085   1.0000   0.0031
  -8.750  -0.9319   0.01453   0.00936  -0.0080   1.0000   0.0032
  -8.500  -0.9076   0.01398   0.00872  -0.0075   1.0000   0.0033
  -8.250  -0.8841   0.01317   0.00776  -0.0068   1.0000   0.0040
  -8.000  -0.8597   0.01262   0.00718  -0.0063   1.0000   0.0048
  -7.750  -0.8348   0.01219   0.00672  -0.0058   1.0000   0.0057
  -7.500  -0.8097   0.01180   0.00628  -0.0054   1.0000   0.0063
  -7.250  -0.7849   0.01135   0.00578  -0.0049   1.0000   0.0077
  -7.000  -0.7598   0.01098   0.00541  -0.0044   1.0000   0.0092
  -6.750  -0.7345   0.01069   0.00508  -0.0039   1.0000   0.0104
  -6.500  -0.7092   0.01042   0.00476  -0.0034   1.0000   0.0111
  -6.250  -0.6840   0.01016   0.00446  -0.0029   1.0000   0.0116
  -6.000  -0.6593   0.00979   0.00405  -0.0022   1.0000   0.0132
  -5.750  -0.6347   0.00948   0.00374  -0.0016   1.0000   0.0150
  -5.500  -0.6101   0.00921   0.00346  -0.0009   1.0000   0.0164
  -5.250  -0.5855   0.00898   0.00320  -0.0002   1.0000   0.0175
  -5.000  -0.5612   0.00868   0.00292   0.0005   1.0000   0.0219
  -4.750  -0.5371   0.00842   0.00266   0.0013   1.0000   0.0281
  -4.500  -0.5131   0.00817   0.00245   0.0021   1.0000   0.0361
  -4.250  -0.4825   0.00794   0.00226   0.0015   0.9982   0.0434
  -4.000  -0.4509   0.00777   0.00209   0.0006   0.9961   0.0490
  -3.750  -0.4190   0.00757   0.00193  -0.0003   0.9941   0.0576
  -3.500  -0.3885   0.00739   0.00179  -0.0009   0.9914   0.0653
  -3.000  -0.3259   0.00705   0.00152  -0.0024   0.9859   0.0866
  -2.750  -0.2938   0.00688   0.00142  -0.0034   0.9832   0.1008
  -2.500  -0.2613   0.00669   0.00131  -0.0044   0.9743   0.1189
  -2.250  -0.2269   0.00654   0.00117  -0.0056   0.9481   0.1328
  -2.000  -0.2016   0.00649   0.00106  -0.0047   0.9072   0.1454
  -1.750  -0.1766   0.00644   0.00097  -0.0038   0.8773   0.1610
  -1.500  -0.1510   0.00636   0.00089  -0.0032   0.8503   0.1849
  -1.250  -0.1249   0.00628   0.00081  -0.0027   0.8248   0.2103
  -1.000  -0.0989   0.00618   0.00075  -0.0023   0.7964   0.2457
  -0.750  -0.0734   0.00614   0.00069  -0.0017   0.7498   0.2832
  -0.500  -0.0493   0.00624   0.00064  -0.0010   0.6531   0.3351
  -0.250  -0.0250   0.00640   0.00063  -0.0004   0.5456   0.3925
   0.000   0.0000   0.00641   0.00063   0.0000   0.4678   0.4680
   0.250   0.0249   0.00641   0.00063   0.0004   0.3909   0.5460
   0.500   0.0493   0.00624   0.00064   0.0009   0.3348   0.6523
   0.750   0.0734   0.00614   0.00069   0.0017   0.2826   0.7499
   1.000   0.0990   0.00618   0.00075   0.0023   0.2459   0.7965
   1.250   0.1249   0.00628   0.00081   0.0027   0.2104   0.8247
   1.500   0.1510   0.00636   0.00089   0.0032   0.1847   0.8500
   1.750   0.1766   0.00644   0.00097   0.0038   0.1613   0.8771
   2.000   0.2017   0.00649   0.00106   0.0047   0.1454   0.9072
   2.250   0.2270   0.00654   0.00117   0.0056   0.1328   0.9481
   2.500   0.2614   0.00669   0.00131   0.0043   0.1189   0.9744
   2.750   0.2940   0.00687   0.00142   0.0033   0.1024   0.9833
   3.000   0.3261   0.00705   0.00152   0.0024   0.0864   0.9859
   3.500   0.3887   0.00739   0.00179   0.0008   0.0655   0.9916
   3.750   0.4193   0.00757   0.00193   0.0002   0.0574   0.9942
   4.000   0.4512   0.00777   0.00209  -0.0007   0.0490   0.9962
   4.250   0.4828   0.00795   0.00226  -0.0015   0.0433   0.9984
   4.500   0.5127   0.00817   0.00245  -0.0020   0.0362   1.0000
   4.750   0.5366   0.00842   0.00266  -0.0012   0.0282   1.0000
   5.000   0.5608   0.00868   0.00292  -0.0005   0.0220   1.0000
   5.250   0.5851   0.00898   0.00320   0.0003   0.0176   1.0000
   5.500   0.6098   0.00921   0.00346   0.0010   0.0165   1.0000
   5.750   0.6344   0.00948   0.00374   0.0017   0.0150   1.0000
   6.000   0.6591   0.00979   0.00405   0.0023   0.0132   1.0000
   6.250   0.6838   0.01016   0.00446   0.0029   0.0115   1.0000
   6.500   0.7091   0.01043   0.00476   0.0034   0.0111   1.0000
   6.750   0.7345   0.01069   0.00508   0.0039   0.0104   1.0000
   7.000   0.7599   0.01098   0.00541   0.0044   0.0092   1.0000
   7.250   0.7850   0.01135   0.00579   0.0048   0.0078   1.0000
   7.500   0.8099   0.01180   0.00627   0.0054   0.0063   1.0000
   7.750   0.8350   0.01219   0.00672   0.0058   0.0057   1.0000
   8.000   0.8598   0.01263   0.00719   0.0063   0.0048   1.0000
   8.250   0.8843   0.01317   0.00776   0.0068   0.0040   1.0000
   8.500   0.9079   0.01397   0.00871   0.0074   0.0033   1.0000
   8.750   0.9322   0.01453   0.00935   0.0079   0.0032   1.0000
   9.000   0.9562   0.01514   0.01006   0.0085   0.0031   1.0000
   9.250   0.9798   0.01582   0.01086   0.0090   0.0030   1.0000
   9.500   1.0031   0.01654   0.01168   0.0096   0.0029   1.0000
   9.750   1.0259   0.01734   0.01261   0.0102   0.0027   1.0000
  10.000   1.0481   0.01822   0.01362   0.0108   0.0026   1.0000
  10.250   1.0699   0.01914   0.01467   0.0115   0.0025   1.0000
  10.500   1.0909   0.02017   0.01585   0.0122   0.0024   1.0000
  10.750   1.1116   0.02117   0.01702   0.0128   0.0023   1.0000
  11.000   1.1312   0.02234   0.01834   0.0136   0.0023   1.0000
  11.250   1.1497   0.02362   0.01978   0.0144   0.0022   1.0000
  11.500   1.1677   0.02491   0.02122   0.0152   0.0021   1.0000
  11.750   1.1841   0.02637   0.02283   0.0161   0.0020   1.0000
  12.000   1.1967   0.02829   0.02497   0.0171   0.0019   1.0000
  12.250   1.2062   0.03050   0.02739   0.0183   0.0019   1.0000
  12.500   1.2112   0.03311   0.03024   0.0196   0.0019   1.0000
  12.750   1.2095   0.03628   0.03366   0.0210   0.0018   1.0000
  13.000   1.1886   0.04075   0.03840   0.0232   0.0017   1.0000
  13.250   1.1499   0.04722   0.04512   0.0231   0.0017   1.0000
  13.500   1.0185   0.08114   0.07931  -0.0025   0.0021   1.0000
  13.750   0.9106   0.10708   0.10534  -0.0183   0.0025   1.0000
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