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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 500,000
Max Cl/Cd: 84.39 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9000-il-500000-n5.txt
Download as CSV file: xf-s9000-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4711   0.07338   0.07118  -0.0319   1.0000   0.0051
  -8.250  -0.4841   0.06933   0.06719  -0.0329   1.0000   0.0050
  -8.000  -0.5016   0.06400   0.06192  -0.0363   1.0000   0.0050
  -7.750  -0.5123   0.05700   0.05488  -0.0417   1.0000   0.0049
  -7.500  -0.5127   0.04743   0.04510  -0.0486   0.9981   0.0048
  -7.250  -0.5018   0.03278   0.02974  -0.0578   0.9920   0.0045
  -7.000  -0.4819   0.02434   0.02040  -0.0612   0.9869   0.0043
  -6.750  -0.4532   0.02024   0.01563  -0.0632   0.9842   0.0042
  -6.500  -0.4261   0.01787   0.01284  -0.0637   0.9803   0.0042
  -6.250  -0.3971   0.01623   0.01090  -0.0644   0.9763   0.0042
  -6.000  -0.3656   0.01489   0.00933  -0.0655   0.9732   0.0042
  -5.750  -0.3327   0.01379   0.00806  -0.0668   0.9709   0.0043
  -5.500  -0.3058   0.01293   0.00707  -0.0667   0.9645   0.0045
  -5.250  -0.2740   0.01218   0.00620  -0.0676   0.9599   0.0046
  -5.000  -0.2423   0.01150   0.00541  -0.0685   0.9549   0.0048
  -4.750  -0.2124   0.01098   0.00480  -0.0689   0.9476   0.0051
  -4.500  -0.1793   0.01039   0.00414  -0.0700   0.9424   0.0058
  -4.250  -0.1482   0.00999   0.00367  -0.0707   0.9345   0.0071
  -4.000  -0.1148   0.00957   0.00322  -0.0718   0.9272   0.0102
  -3.750  -0.0822   0.00919   0.00286  -0.0728   0.9169   0.0196
  -3.500  -0.0508   0.00886   0.00257  -0.0735   0.9040   0.0348
  -3.250  -0.0208   0.00852   0.00230  -0.0740   0.8894   0.0627
  -3.000   0.0080   0.00825   0.00207  -0.0742   0.8737   0.0937
  -2.750   0.0358   0.00799   0.00189  -0.0741   0.8577   0.1334
  -2.500   0.0631   0.00775   0.00174  -0.0740   0.8417   0.1801
  -2.250   0.0901   0.00754   0.00160  -0.0739   0.8254   0.2300
  -2.000   0.1168   0.00731   0.00150  -0.0737   0.8076   0.2931
  -1.750   0.1434   0.00712   0.00141  -0.0734   0.7887   0.3544
  -1.500   0.1700   0.00696   0.00133  -0.0732   0.7701   0.4119
  -1.000   0.2229   0.00661   0.00125  -0.0726   0.7340   0.5507
  -0.750   0.2488   0.00646   0.00125  -0.0722   0.7148   0.6261
  -0.500   0.2747   0.00639   0.00127  -0.0716   0.6949   0.6860
  -0.250   0.3007   0.00642   0.00129  -0.0711   0.6732   0.7248
   0.000   0.3267   0.00646   0.00131  -0.0705   0.6506   0.7545
   0.250   0.3524   0.00652   0.00134  -0.0699   0.6292   0.7818
   0.500   0.3784   0.00659   0.00138  -0.0694   0.6088   0.8040
   0.750   0.4042   0.00667   0.00142  -0.0688   0.5887   0.8236
   1.250   0.4545   0.00687   0.00153  -0.0673   0.5445   0.8624
   1.500   0.4789   0.00699   0.00159  -0.0665   0.5181   0.8811
   2.000   0.5263   0.00722   0.00172  -0.0644   0.4726   0.9228
   2.250   0.5518   0.00732   0.00178  -0.0637   0.4526   0.9486
   2.500   0.5841   0.00747   0.00185  -0.0647   0.4294   0.9802
   2.750   0.6135   0.00766   0.00194  -0.0651   0.4060   1.0000
   3.000   0.6400   0.00788   0.00207  -0.0649   0.3845   1.0000
   3.250   0.6661   0.00814   0.00221  -0.0647   0.3575   1.0000
   3.500   0.6921   0.00841   0.00236  -0.0645   0.3305   1.0000
   3.750   0.7185   0.00865   0.00252  -0.0643   0.3096   1.0000
   4.000   0.7447   0.00892   0.00271  -0.0640   0.2888   1.0000
   4.250   0.7708   0.00919   0.00290  -0.0638   0.2677   1.0000
   4.500   0.7969   0.00945   0.00310  -0.0636   0.2497   1.0000
   4.750   0.8228   0.00975   0.00333  -0.0633   0.2309   1.0000
   5.000   0.8479   0.01012   0.00359  -0.0629   0.2042   1.0000
   5.250   0.8732   0.01047   0.00386  -0.0626   0.1814   1.0000
   5.500   0.8987   0.01080   0.00413  -0.0623   0.1644   1.0000
   5.750   0.9241   0.01113   0.00442  -0.0620   0.1497   1.0000
   6.000   0.9493   0.01148   0.00473  -0.0616   0.1360   1.0000
   6.250   0.9745   0.01182   0.00505  -0.0613   0.1234   1.0000
   6.500   0.9993   0.01220   0.00539  -0.0609   0.1097   1.0000
   6.750   1.0238   0.01262   0.00576  -0.0604   0.0958   1.0000
   7.000   1.0482   0.01302   0.00617  -0.0600   0.0848   1.0000
   7.250   1.0721   0.01348   0.00659  -0.0595   0.0729   1.0000
   7.500   1.0959   0.01395   0.00703  -0.0589   0.0620   1.0000
   7.750   1.1193   0.01443   0.00750  -0.0584   0.0526   1.0000
   8.000   1.1424   0.01495   0.00800  -0.0577   0.0446   1.0000
   8.250   1.1656   0.01544   0.00852  -0.0571   0.0389   1.0000
   8.500   1.1884   0.01595   0.00906  -0.0565   0.0343   1.0000
   8.750   1.2111   0.01646   0.00960  -0.0558   0.0300   1.0000
   9.000   1.2328   0.01705   0.01022  -0.0550   0.0255   1.0000
   9.250   1.2547   0.01760   0.01081  -0.0542   0.0217   1.0000
   9.500   1.2752   0.01827   0.01151  -0.0533   0.0180   1.0000
   9.750   1.2955   0.01894   0.01224  -0.0523   0.0149   1.0000
  10.000   1.3146   0.01970   0.01303  -0.0512   0.0123   1.0000
  10.250   1.3334   0.02044   0.01382  -0.0501   0.0102   1.0000
  10.500   1.3508   0.02128   0.01472  -0.0488   0.0087   1.0000
  10.750   1.3688   0.02200   0.01552  -0.0476   0.0074   1.0000
  11.000   1.3844   0.02288   0.01647  -0.0461   0.0064   1.0000
  11.250   1.3990   0.02379   0.01747  -0.0444   0.0058   1.0000
  11.500   1.4120   0.02461   0.01841  -0.0425   0.0052   1.0000
  11.750   1.4228   0.02551   0.01943  -0.0403   0.0048   1.0000
  12.000   1.4316   0.02653   0.02054  -0.0380   0.0043   1.0000
  12.250   1.4376   0.02777   0.02188  -0.0355   0.0039   1.0000
  12.500   1.4445   0.02896   0.02319  -0.0333   0.0035   1.0000
  12.750   1.4496   0.03033   0.02470  -0.0311   0.0033   1.0000
  13.000   1.4542   0.03181   0.02630  -0.0292   0.0029   1.0000
  13.250   1.4567   0.03353   0.02815  -0.0275   0.0027   1.0000
  13.500   1.4571   0.03558   0.03032  -0.0260   0.0025   1.0000
  13.750   1.4536   0.03815   0.03303  -0.0247   0.0023   1.0000
  14.000   1.4513   0.04079   0.03582  -0.0240   0.0022   1.0000
  14.250   1.4473   0.04386   0.03905  -0.0238   0.0020   1.0000
  14.500   1.4419   0.04733   0.04268  -0.0241   0.0020   1.0000
  14.750   1.4343   0.05137   0.04688  -0.0249   0.0018   1.0000
  15.000   1.4249   0.05599   0.05166  -0.0264   0.0018   1.0000
  15.250   1.4133   0.06128   0.05712  -0.0286   0.0017   1.0000
  15.500   1.4002   0.06715   0.06316  -0.0313   0.0017   1.0000
  15.750   1.3848   0.07376   0.06994  -0.0347   0.0016   1.0000
  16.000   1.3647   0.08164   0.07800  -0.0389   0.0017   1.0000
  16.250   1.3438   0.09004   0.08657  -0.0435   0.0017   1.0000
  16.500   1.3206   0.09925   0.09595  -0.0487   0.0018   1.0000
  16.750   1.2967   0.10892   0.10578  -0.0541   0.0018   1.0000
  17.000   1.2721   0.11905   0.11606  -0.0598   0.0019   1.0000
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