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S1010 HPV airfoil (s1010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S1010 HPV airfoil (s1010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 66.31 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1010-il-1000000.txt
Download as CSV file: xf-s1010-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.9927   0.04542   0.04355  -0.0209   1.0000   0.0048
 -11.000  -1.0265   0.03903   0.03682  -0.0196   1.0000   0.0047
 -10.750  -1.0229   0.03626   0.03385  -0.0188   1.0000   0.0048
 -10.500  -1.0266   0.03199   0.02921  -0.0174   1.0000   0.0048
 -10.250  -1.0187   0.02916   0.02609  -0.0162   1.0000   0.0049
 -10.000  -1.0058   0.02694   0.02362  -0.0152   1.0000   0.0050
  -9.750  -0.9917   0.02474   0.02115  -0.0141   1.0000   0.0051
  -9.500  -0.9745   0.02299   0.01916  -0.0131   1.0000   0.0052
  -9.250  -0.9552   0.02156   0.01752  -0.0122   1.0000   0.0053
  -9.000  -0.9349   0.02025   0.01601  -0.0114   1.0000   0.0054
  -8.750  -0.9214   0.01725   0.01258  -0.0098   1.0000   0.0056
  -8.500  -0.9013   0.01577   0.01092  -0.0088   1.0000   0.0062
  -8.250  -0.8773   0.01515   0.01024  -0.0083   1.0000   0.0066
  -8.000  -0.8529   0.01462   0.00965  -0.0078   1.0000   0.0072
  -7.750  -0.8286   0.01401   0.00895  -0.0072   1.0000   0.0078
  -7.500  -0.8040   0.01347   0.00833  -0.0067   1.0000   0.0083
  -7.250  -0.7818   0.01232   0.00700  -0.0057   1.0000   0.0094
  -7.000  -0.7575   0.01174   0.00637  -0.0051   1.0000   0.0107
  -6.750  -0.7324   0.01135   0.00594  -0.0046   1.0000   0.0120
  -6.500  -0.7070   0.01107   0.00562  -0.0041   1.0000   0.0129
  -6.250  -0.6836   0.01032   0.00477  -0.0032   1.0000   0.0151
  -6.000  -0.6589   0.00994   0.00438  -0.0026   1.0000   0.0172
  -5.750  -0.6340   0.00967   0.00407  -0.0020   1.0000   0.0190
  -5.500  -0.6098   0.00927   0.00361  -0.0012   1.0000   0.0213
  -5.250  -0.5858   0.00888   0.00325  -0.0004   1.0000   0.0266
  -5.000  -0.5617   0.00852   0.00293   0.0004   1.0000   0.0353
  -4.750  -0.5377   0.00824   0.00269   0.0012   1.0000   0.0459
  -4.500  -0.5135   0.00803   0.00249   0.0020   1.0000   0.0537
  -4.250  -0.4896   0.00782   0.00230   0.0028   1.0000   0.0618
  -4.000  -0.4659   0.00761   0.00212   0.0037   1.0000   0.0706
  -3.750  -0.4424   0.00744   0.00197   0.0046   1.0000   0.0795
  -3.500  -0.4192   0.00727   0.00184   0.0056   1.0000   0.0900
  -3.250  -0.3964   0.00711   0.00172   0.0066   1.0000   0.1030
  -3.000  -0.3718   0.00695   0.00162   0.0072   0.9997   0.1176
  -2.750  -0.3380   0.00676   0.00152   0.0058   0.9979   0.1377
  -2.500  -0.3006   0.00658   0.00143   0.0037   0.9953   0.1599
  -2.250  -0.2578   0.00633   0.00131   0.0005   0.9900   0.1913
  -2.000  -0.2131   0.00605   0.00118  -0.0032   0.9840   0.2319
  -1.750  -0.1797   0.00578   0.00109  -0.0044   0.9756   0.2808
  -1.500  -0.1479   0.00541   0.00099  -0.0054   0.9668   0.3581
  -1.250  -0.1197   0.00499   0.00090  -0.0055   0.9554   0.4576
  -1.000  -0.0955   0.00444   0.00081  -0.0047   0.9413   0.5959
  -0.750  -0.0735   0.00393   0.00078  -0.0033   0.9255   0.7414
  -0.500  -0.0497   0.00376   0.00079  -0.0021   0.9080   0.8078
  -0.250  -0.0248   0.00371   0.00079  -0.0010   0.8898   0.8424
   0.000   0.0000   0.00369   0.00079   0.0000   0.8690   0.8690
   0.250   0.0249   0.00371   0.00079   0.0010   0.8424   0.8898
   0.500   0.0498   0.00376   0.00079   0.0021   0.8082   0.9084
   0.750   0.0735   0.00393   0.00078   0.0033   0.7411   0.9256
   1.000   0.0955   0.00444   0.00081   0.0047   0.5950   0.9413
   1.250   0.1198   0.00499   0.00090   0.0055   0.4571   0.9553
   1.500   0.1480   0.00540   0.00099   0.0053   0.3599   0.9668
   1.750   0.1798   0.00578   0.00109   0.0044   0.2808   0.9757
   2.000   0.2131   0.00605   0.00118   0.0032   0.2319   0.9840
   2.250   0.2579   0.00633   0.00131  -0.0005   0.1913   0.9900
   2.500   0.3008   0.00658   0.00143  -0.0038   0.1600   0.9953
   2.750   0.3381   0.00676   0.00152  -0.0059   0.1378   0.9979
   3.000   0.3719   0.00695   0.00162  -0.0073   0.1174   0.9997
   3.250   0.3964   0.00711   0.00172  -0.0066   0.1033   1.0000
   3.500   0.4192   0.00727   0.00184  -0.0056   0.0902   1.0000
   3.750   0.4424   0.00744   0.00197  -0.0046   0.0795   1.0000
   4.000   0.4659   0.00761   0.00212  -0.0037   0.0707   1.0000
   4.250   0.4896   0.00782   0.00230  -0.0028   0.0618   1.0000
   4.500   0.5135   0.00803   0.00249  -0.0020   0.0537   1.0000
   4.750   0.5377   0.00824   0.00269  -0.0012   0.0460   1.0000
   5.000   0.5618   0.00852   0.00293  -0.0004   0.0353   1.0000
   5.250   0.5858   0.00888   0.00325   0.0004   0.0265   1.0000
   5.500   0.6099   0.00927   0.00361   0.0012   0.0214   1.0000
   5.750   0.6341   0.00967   0.00407   0.0020   0.0190   1.0000
   6.000   0.6591   0.00994   0.00438   0.0026   0.0173   1.0000
   6.250   0.6837   0.01032   0.00477   0.0032   0.0151   1.0000
   6.500   0.7071   0.01107   0.00562   0.0041   0.0129   1.0000
   6.750   0.7325   0.01136   0.00595   0.0046   0.0120   1.0000
   7.000   0.7576   0.01173   0.00636   0.0051   0.0107   1.0000
   7.250   0.7819   0.01232   0.00700   0.0057   0.0094   1.0000
   7.500   0.8037   0.01355   0.00841   0.0067   0.0084   1.0000
   7.750   0.8287   0.01399   0.00893   0.0072   0.0078   1.0000
   8.000   0.8529   0.01464   0.00967   0.0078   0.0073   1.0000
   8.250   0.8774   0.01516   0.01025   0.0083   0.0066   1.0000
   8.500   0.9014   0.01575   0.01090   0.0088   0.0062   1.0000
   8.750   0.9218   0.01717   0.01250   0.0097   0.0057   1.0000
   9.000   0.9350   0.02025   0.01600   0.0114   0.0054   1.0000
   9.250   0.9555   0.02151   0.01747   0.0122   0.0053   1.0000
   9.500   0.9752   0.02286   0.01901   0.0130   0.0052   1.0000
   9.750   0.9916   0.02477   0.02117   0.0141   0.0051   1.0000
  10.000   1.0069   0.02676   0.02341   0.0151   0.0050   1.0000
  10.250   1.0184   0.02924   0.02617   0.0163   0.0049   1.0000
  10.500   1.0268   0.03199   0.02921   0.0174   0.0048   1.0000
  10.750   1.0236   0.03619   0.03377   0.0188   0.0048   1.0000
  11.000   1.0146   0.04068   0.03857   0.0197   0.0048   1.0000
  11.250   0.9919   0.04557   0.04370   0.0208   0.0048   1.0000
  11.750   0.8393   0.08870   0.08709  -0.0099   0.0054   1.0000
  12.000   0.8296   0.09517   0.09356  -0.0133   0.0055   1.0000
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