Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S9032 (9%) (s9032-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S9032 (9%) (s9032-il)
Reynolds number: 100,000
Max Cl/Cd: 34.21 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9032-il-100000-n5.txt
Download as CSV file: xf-s9032-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9032 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.8009   0.08345   0.07836  -0.0040   1.0000   0.0359
 -11.250  -0.8901   0.06185   0.05644  -0.0222   1.0000   0.0324
 -11.000  -0.9174   0.05612   0.05047  -0.0249   1.0000   0.0323
 -10.750  -0.9352   0.05238   0.04650  -0.0243   1.0000   0.0324
 -10.500  -0.9415   0.04956   0.04348  -0.0232   1.0000   0.0332
 -10.250  -0.9432   0.04669   0.04033  -0.0221   1.0000   0.0342
 -10.000  -0.9418   0.04367   0.03698  -0.0210   1.0000   0.0353
  -9.750  -0.9368   0.04060   0.03352  -0.0197   1.0000   0.0364
  -9.500  -0.9277   0.03769   0.03018  -0.0185   1.0000   0.0374
  -9.250  -0.9148   0.03514   0.02721  -0.0173   1.0000   0.0386
  -9.000  -0.8991   0.03284   0.02459  -0.0162   1.0000   0.0397
  -8.750  -0.8820   0.03109   0.02278  -0.0153   1.0000   0.0416
  -8.500  -0.8631   0.02983   0.02138  -0.0145   1.0000   0.0443
  -8.250  -0.8433   0.02838   0.01971  -0.0136   1.0000   0.0473
  -8.000  -0.8226   0.02689   0.01792  -0.0126   1.0000   0.0500
  -7.750  -0.8031   0.02539   0.01640  -0.0116   1.0000   0.0529
  -7.500  -0.7822   0.02428   0.01522  -0.0107   1.0000   0.0569
  -7.250  -0.7602   0.02329   0.01404  -0.0098   1.0000   0.0627
  -7.000  -0.7394   0.02229   0.01304  -0.0090   1.0000   0.0690
  -6.750  -0.7172   0.02137   0.01200  -0.0081   1.0000   0.0762
  -6.500  -0.6951   0.02058   0.01119  -0.0073   1.0000   0.0854
  -6.250  -0.6730   0.01977   0.01038  -0.0065   1.0000   0.0950
  -6.000  -0.6504   0.01904   0.00964  -0.0056   1.0000   0.1069
  -5.750  -0.6278   0.01835   0.00893  -0.0048   1.0000   0.1203
  -5.500  -0.6049   0.01771   0.00831  -0.0040   1.0000   0.1361
  -5.250  -0.5819   0.01710   0.00772  -0.0032   1.0000   0.1537
  -5.000  -0.5588   0.01653   0.00718  -0.0024   1.0000   0.1724
  -4.750  -0.5359   0.01598   0.00671  -0.0016   1.0000   0.1953
  -4.500  -0.5129   0.01547   0.00627  -0.0008   1.0000   0.2213
  -4.250  -0.4899   0.01499   0.00589   0.0001   1.0000   0.2503
  -4.000  -0.4669   0.01455   0.00556   0.0010   1.0000   0.2824
  -3.750  -0.4442   0.01412   0.00527   0.0019   1.0000   0.3182
  -3.500  -0.4215   0.01372   0.00499   0.0029   1.0000   0.3556
  -3.250  -0.3990   0.01334   0.00477   0.0039   1.0000   0.3935
  -3.000  -0.3764   0.01301   0.00457   0.0050   1.0000   0.4325
  -2.750  -0.3540   0.01269   0.00441   0.0061   1.0000   0.4726
  -2.500  -0.3317   0.01240   0.00428   0.0074   1.0000   0.5144
  -2.250  -0.3096   0.01213   0.00419   0.0086   1.0000   0.5580
  -2.000  -0.2877   0.01190   0.00414   0.0100   1.0000   0.6020
  -1.750  -0.2656   0.01170   0.00411   0.0114   1.0000   0.6450
  -1.500  -0.2437   0.01154   0.00409   0.0128   1.0000   0.6865
  -1.250  -0.2222   0.01141   0.00412   0.0143   1.0000   0.7283
  -1.000  -0.1934   0.01133   0.00420   0.0144   0.9950   0.7732
  -0.750  -0.1504   0.01131   0.00431   0.0118   0.9812   0.8221
  -0.500  -0.1042   0.01131   0.00441   0.0087   0.9664   0.8660
  -0.250  -0.0535   0.01133   0.00447   0.0047   0.9491   0.9010
   0.000   0.0000   0.01133   0.00449   0.0000   0.9280   0.9280
   0.250   0.0535   0.01133   0.00447  -0.0047   0.9010   0.9491
   0.500   0.1042   0.01131   0.00441  -0.0087   0.8661   0.9663
   0.750   0.1504   0.01131   0.00431  -0.0119   0.8223   0.9811
   1.000   0.1934   0.01133   0.00420  -0.0144   0.7733   0.9949
   1.250   0.2224   0.01141   0.00412  -0.0143   0.7280   1.0000
   1.500   0.2439   0.01154   0.00409  -0.0128   0.6863   1.0000
   1.750   0.2659   0.01170   0.00411  -0.0114   0.6449   1.0000
   2.000   0.2879   0.01190   0.00414  -0.0101   0.6018   1.0000
   2.250   0.3099   0.01213   0.00419  -0.0087   0.5580   1.0000
   2.500   0.3320   0.01240   0.00428  -0.0074   0.5143   1.0000
   2.750   0.3543   0.01269   0.00441  -0.0062   0.4723   1.0000
   3.000   0.3768   0.01301   0.00457  -0.0051   0.4324   1.0000
   3.250   0.3994   0.01334   0.00477  -0.0040   0.3935   1.0000
   3.500   0.4219   0.01372   0.00499  -0.0030   0.3555   1.0000
   3.750   0.4446   0.01412   0.00527  -0.0020   0.3180   1.0000
   4.000   0.4673   0.01455   0.00556  -0.0010   0.2823   1.0000
   4.250   0.4902   0.01500   0.00589  -0.0001   0.2500   1.0000
   4.500   0.5132   0.01547   0.00627   0.0007   0.2212   1.0000
   4.750   0.5361   0.01598   0.00672   0.0015   0.1953   1.0000
   5.000   0.5590   0.01653   0.00718   0.0024   0.1722   1.0000
   5.250   0.5821   0.01710   0.00772   0.0032   0.1536   1.0000
   5.500   0.6051   0.01771   0.00831   0.0040   0.1361   1.0000
   5.750   0.6278   0.01835   0.00893   0.0048   0.1202   1.0000
   6.000   0.6505   0.01904   0.00964   0.0056   0.1069   1.0000
   6.250   0.6730   0.01977   0.01038   0.0065   0.0950   1.0000
   6.500   0.6951   0.02057   0.01118   0.0073   0.0853   1.0000
   6.750   0.7171   0.02136   0.01200   0.0081   0.0761   1.0000
   7.000   0.7392   0.02229   0.01304   0.0090   0.0690   1.0000
   7.250   0.7600   0.02328   0.01403   0.0099   0.0627   1.0000
   7.500   0.7819   0.02427   0.01521   0.0108   0.0569   1.0000
   7.750   0.8028   0.02538   0.01640   0.0117   0.0529   1.0000
   8.000   0.8222   0.02688   0.01791   0.0126   0.0500   1.0000
   8.250   0.8429   0.02838   0.01970   0.0137   0.0473   1.0000
   8.500   0.8626   0.02981   0.02136   0.0146   0.0443   1.0000
   8.750   0.8815   0.03106   0.02275   0.0154   0.0416   1.0000
   9.000   0.8986   0.03281   0.02457   0.0163   0.0398   1.0000
   9.250   0.9141   0.03511   0.02718   0.0174   0.0385   1.0000
   9.500   0.9271   0.03765   0.03014   0.0186   0.0374   1.0000
   9.750   0.9362   0.04055   0.03346   0.0199   0.0364   1.0000
  10.000   0.9411   0.04362   0.03692   0.0211   0.0354   1.0000
  10.250   0.9424   0.04667   0.04032   0.0223   0.0343   1.0000
  10.500   0.9406   0.04954   0.04346   0.0234   0.0332   1.0000
  10.750   0.9332   0.05248   0.04661   0.0245   0.0325   1.0000
  11.000   0.9169   0.05603   0.05037   0.0251   0.0323   1.0000
  11.250   0.8884   0.06197   0.05656   0.0222   0.0325   1.0000
  11.500   0.8011   0.08325   0.07816   0.0043   0.0359   1.0000
<< Back to S9032 (9%) (s9032-il)

Polar data table (+)

Polar graphs


<< Back to S9032 (9%) (s9032-il)