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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 50,000
Max Cl/Cd: 34.71 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9000-il-50000.txt
Download as CSV file: xf-s9000-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9000 (9%)                                      
  
 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  -0.4124   0.10163   0.09488  -0.0149   1.0000   0.2395
  -8.000  -0.4293   0.10080   0.09420  -0.0156   1.0000   0.2501
  -7.750  -0.4199   0.09714   0.09059  -0.0143   1.0000   0.2639
  -7.500  -0.4107   0.09356   0.08706  -0.0131   1.0000   0.2772
  -7.250  -0.4070   0.09044   0.08402  -0.0118   1.0000   0.2909
  -7.000  -0.4021   0.08725   0.08091  -0.0106   1.0000   0.3030
  -6.750  -0.4020   0.08447   0.07822  -0.0091   1.0000   0.3157
  -6.500  -0.4043   0.08182   0.07569  -0.0072   1.0000   0.3297
  -6.250  -0.4065   0.07926   0.07324  -0.0053   1.0000   0.3439
  -6.000  -0.4082   0.07669   0.07075  -0.0034   1.0000   0.3613
  -5.250  -0.4103   0.05004   0.04317  -0.0423   1.0000   0.1295
  -5.000  -0.3916   0.04428   0.03682  -0.0443   1.0000   0.1151
  -4.750  -0.3689   0.03939   0.03104  -0.0456   1.0000   0.1065
  -4.500  -0.3465   0.03586   0.02697  -0.0454   1.0000   0.1064
  -4.250  -0.3244   0.03290   0.02374  -0.0450   1.0000   0.1116
  -4.000  -0.2997   0.03025   0.02068  -0.0444   1.0000   0.1166
  -3.750  -0.2750   0.02797   0.01804  -0.0437   1.0000   0.1283
  -3.500  -0.2498   0.02590   0.01574  -0.0428   1.0000   0.1441
  -3.250  -0.2255   0.02413   0.01394  -0.0417   1.0000   0.1715
  -3.000  -0.2015   0.02245   0.01237  -0.0405   1.0000   0.2207
  -2.750  -0.1776   0.02033   0.01107  -0.0394   1.0000   0.3441
  -2.500  -0.1694   0.01809   0.01080  -0.0336   1.0000   0.6415
  -2.000  -0.1235   0.01721   0.00986  -0.0276   1.0000   1.0000
  -1.750  -0.1033   0.01722   0.00940  -0.0276   1.0000   1.0000
  -1.500  -0.0822   0.01734   0.00912  -0.0276   1.0000   1.0000
  -1.250  -0.0610   0.01753   0.00897  -0.0275   1.0000   1.0000
  -1.000  -0.0399   0.01777   0.00889  -0.0274   1.0000   1.0000
  -0.750  -0.0191   0.01807   0.00893  -0.0273   1.0000   1.0000
  -0.500   0.0014   0.01842   0.00906  -0.0272   1.0000   1.0000
  -0.250   0.0215   0.01882   0.00926  -0.0271   1.0000   1.0000
   0.000   0.0412   0.01928   0.00953  -0.0270   1.0000   1.0000
   0.250   0.0604   0.01980   0.00990  -0.0269   1.0000   1.0000
   0.500   0.0792   0.02039   0.01035  -0.0269   1.0000   1.0000
   0.750   0.0976   0.02104   0.01089  -0.0270   1.0000   1.0000
   1.000   0.1155   0.02175   0.01150  -0.0271   1.0000   1.0000
   1.250   0.1544   0.02287   0.01253  -0.0312   0.9895   1.0000
   1.500   0.2138   0.02420   0.01379  -0.0386   0.9692   1.0000
   1.750   0.2665   0.02516   0.01471  -0.0445   0.9472   1.0000
   2.000   0.3191   0.02598   0.01554  -0.0499   0.9255   1.0000
   2.250   0.3716   0.02661   0.01622  -0.0549   0.9035   1.0000
   2.500   0.4180   0.02708   0.01675  -0.0585   0.8805   1.0000
   2.750   0.4756   0.02724   0.01702  -0.0633   0.8591   1.0000
   3.000   0.5197   0.02735   0.01728  -0.0656   0.8347   1.0000
   3.250   0.5737   0.02708   0.01716  -0.0688   0.8122   1.0000
   3.500   0.6223   0.02666   0.01689  -0.0706   0.7889   1.0000
   3.750   0.6611   0.02642   0.01683  -0.0708   0.7635   1.0000
   4.000   0.7000   0.02603   0.01657  -0.0706   0.7375   1.0000
   4.250   0.7363   0.02563   0.01632  -0.0698   0.7101   1.0000
   4.500   0.7687   0.02536   0.01613  -0.0684   0.6809   1.0000
   4.750   0.7985   0.02524   0.01606  -0.0667   0.6503   1.0000
   5.000   0.8271   0.02522   0.01606  -0.0650   0.6187   1.0000
   5.250   0.8555   0.02527   0.01611  -0.0632   0.5867   1.0000
   5.500   0.8780   0.02573   0.01659  -0.0612   0.5520   1.0000
   5.750   0.9028   0.02610   0.01691  -0.0593   0.5176   1.0000
   6.000   0.9256   0.02667   0.01742  -0.0573   0.4826   1.0000
   6.250   0.9478   0.02735   0.01808  -0.0554   0.4475   1.0000
   6.500   0.9707   0.02811   0.01872  -0.0537   0.4138   1.0000
   6.750   0.9906   0.02917   0.01981  -0.0519   0.3802   1.0000
   7.000   1.0114   0.03026   0.02083  -0.0502   0.3479   1.0000
   7.250   1.0324   0.03146   0.02199  -0.0486   0.3172   1.0000
   7.500   1.0527   0.03283   0.02330  -0.0470   0.2881   1.0000
   7.750   1.0711   0.03436   0.02487  -0.0453   0.2609   1.0000
   8.000   1.0892   0.03635   0.02701  -0.0438   0.2379   1.0000
   8.250   1.1099   0.03804   0.02857  -0.0425   0.2156   1.0000
   8.500   1.1255   0.04068   0.03154  -0.0408   0.1991   1.0000
   8.750   1.1406   0.04338   0.03451  -0.0391   0.1842   1.0000
   9.000   1.1536   0.04595   0.03738  -0.0374   0.1698   1.0000
   9.250   1.1685   0.04911   0.04071  -0.0360   0.1591   1.0000
   9.500   1.1821   0.05184   0.04354  -0.0345   0.1467   1.0000
   9.750   1.1735   0.05625   0.04869  -0.0316   0.1421   1.0000
  10.000   1.1882   0.05955   0.05198  -0.0305   0.1329   1.0000
  10.250   1.1712   0.06436   0.05737  -0.0278   0.1312   1.0000
  10.500   1.1511   0.06933   0.06273  -0.0258   0.1303   1.0000
  10.750   1.1266   0.07439   0.06803  -0.0241   0.1308   1.0000
  11.000   1.1008   0.07962   0.07341  -0.0232   0.1318   1.0000
  11.250   1.0764   0.08556   0.07943  -0.0240   0.1328   1.0000
  11.500   1.0548   0.09224   0.08617  -0.0260   0.1337   1.0000
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