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=50,000 Ncrit=5


Details Polar file
Airfoil: S9032 (9%) (s9032-il)
Reynolds number: 50,000
Max Cl/Cd: 25.02 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9032-il-50000-n5.txt
Download as CSV file: xf-s9032-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7607   0.08641   0.07916  -0.0075   1.0000   0.0621
 -10.500  -0.7829   0.07824   0.07097  -0.0136   1.0000   0.0618
 -10.250  -0.8069   0.07158   0.06426  -0.0180   1.0000   0.0614
 -10.000  -0.8306   0.06635   0.05894  -0.0194   1.0000   0.0612
  -9.750  -0.8491   0.06130   0.05363  -0.0200   1.0000   0.0614
  -9.500  -0.8613   0.05639   0.04832  -0.0199   1.0000   0.0618
  -9.250  -0.8660   0.05180   0.04326  -0.0193   1.0000   0.0626
  -9.000  -0.8562   0.04876   0.04004  -0.0186   1.0000   0.0641
  -8.750  -0.8451   0.04596   0.03701  -0.0178   1.0000   0.0661
  -8.500  -0.8331   0.04333   0.03408  -0.0169   1.0000   0.0696
  -8.250  -0.8211   0.04034   0.03051  -0.0160   1.0000   0.0741
  -8.000  -0.8039   0.03818   0.02823  -0.0151   1.0000   0.0782
  -7.750  -0.7852   0.03605   0.02587  -0.0143   1.0000   0.0828
  -7.500  -0.7660   0.03391   0.02335  -0.0133   1.0000   0.0895
  -7.250  -0.7460   0.03248   0.02182  -0.0125   1.0000   0.0975
  -7.000  -0.7247   0.03076   0.01993  -0.0116   1.0000   0.1054
  -6.750  -0.7034   0.02937   0.01836  -0.0108   1.0000   0.1167
  -6.500  -0.6816   0.02809   0.01695  -0.0099   1.0000   0.1288
  -6.250  -0.6597   0.02692   0.01572  -0.0091   1.0000   0.1429
  -6.000  -0.6377   0.02579   0.01461  -0.0082   1.0000   0.1583
  -5.750  -0.6154   0.02469   0.01350  -0.0073   1.0000   0.1748
  -5.500  -0.5932   0.02374   0.01256  -0.0065   1.0000   0.1970
  -5.250  -0.5709   0.02282   0.01170  -0.0056   1.0000   0.2204
  -5.000  -0.5485   0.02198   0.01093  -0.0047   1.0000   0.2488
  -4.750  -0.5260   0.02121   0.01025  -0.0039   1.0000   0.2817
  -4.500  -0.5035   0.02050   0.00961  -0.0030   1.0000   0.3173
  -4.250  -0.4811   0.01985   0.00907  -0.0020   1.0000   0.3568
  -4.000  -0.4592   0.01925   0.00862  -0.0008   1.0000   0.3970
  -3.750  -0.4378   0.01871   0.00823   0.0005   1.0000   0.4396
  -3.500  -0.4165   0.01822   0.00787   0.0021   1.0000   0.4843
  -3.250  -0.3955   0.01779   0.00760   0.0037   1.0000   0.5309
  -3.000  -0.3747   0.01741   0.00738   0.0056   1.0000   0.5775
  -2.750  -0.3538   0.01707   0.00720   0.0075   1.0000   0.6236
  -2.500  -0.3328   0.01677   0.00702   0.0095   1.0000   0.6694
  -2.250  -0.3112   0.01651   0.00689   0.0116   1.0000   0.7153
  -2.000  -0.2882   0.01631   0.00680   0.0134   1.0000   0.7619
  -1.750  -0.2615   0.01617   0.00674   0.0145   1.0000   0.8094
  -1.500  -0.2261   0.01611   0.00669   0.0140   1.0000   0.8558
  -1.250  -0.1817   0.01609   0.00664   0.0114   1.0000   0.8990
  -1.000  -0.1305   0.01607   0.00653   0.0071   1.0000   0.9366
  -0.750  -0.0750   0.01601   0.00639   0.0016   1.0000   0.9700
  -0.500  -0.0167   0.01584   0.00615  -0.0050   1.0000   1.0000
  -0.250  -0.0087   0.01571   0.00602  -0.0025   1.0000   1.0000
   0.000   0.0000   0.01566   0.00598   0.0000   1.0000   1.0000
   0.250   0.0087   0.01571   0.00602   0.0025   1.0000   1.0000
   0.500   0.0167   0.01584   0.00615   0.0050   1.0000   1.0000
   0.750   0.0750   0.01601   0.00639  -0.0016   0.9700   1.0000
   1.000   0.1305   0.01607   0.00653  -0.0071   0.9365   1.0000
   1.250   0.1817   0.01609   0.00664  -0.0114   0.8989   1.0000
   1.500   0.2262   0.01611   0.00669  -0.0140   0.8558   1.0000
   1.750   0.2616   0.01617   0.00674  -0.0146   0.8095   1.0000
   2.000   0.2884   0.01631   0.00680  -0.0134   0.7618   1.0000
   2.250   0.3114   0.01651   0.00689  -0.0116   0.7152   1.0000
   2.500   0.3330   0.01677   0.00702  -0.0096   0.6693   1.0000
   2.750   0.3540   0.01707   0.00720  -0.0076   0.6235   1.0000
   3.000   0.3749   0.01741   0.00738  -0.0056   0.5774   1.0000
   3.250   0.3957   0.01779   0.00760  -0.0038   0.5308   1.0000
   3.500   0.4167   0.01822   0.00787  -0.0021   0.4842   1.0000
   3.750   0.4380   0.01871   0.00823  -0.0006   0.4394   1.0000
   4.000   0.4594   0.01925   0.00862   0.0008   0.3969   1.0000
   4.250   0.4812   0.01985   0.00907   0.0020   0.3566   1.0000
   4.500   0.5036   0.02050   0.00961   0.0030   0.3174   1.0000
   4.750   0.5261   0.02122   0.01025   0.0039   0.2816   1.0000
   5.000   0.5486   0.02198   0.01093   0.0047   0.2488   1.0000
   5.250   0.5709   0.02282   0.01171   0.0056   0.2204   1.0000
   5.500   0.5932   0.02374   0.01256   0.0065   0.1970   1.0000
   5.750   0.6154   0.02469   0.01350   0.0073   0.1748   1.0000
   6.000   0.6376   0.02578   0.01461   0.0082   0.1584   1.0000
   6.250   0.6596   0.02691   0.01572   0.0091   0.1429   1.0000
   6.500   0.6814   0.02809   0.01694   0.0099   0.1288   1.0000
   6.750   0.7032   0.02937   0.01835   0.0108   0.1167   1.0000
   7.000   0.7245   0.03075   0.01993   0.0117   0.1054   1.0000
   7.250   0.7457   0.03247   0.02180   0.0126   0.0976   1.0000
   7.500   0.7657   0.03391   0.02335   0.0134   0.0896   1.0000
   7.750   0.7848   0.03603   0.02585   0.0143   0.0828   1.0000
   8.000   0.8035   0.03816   0.02821   0.0152   0.0782   1.0000
   8.250   0.8207   0.04032   0.03048   0.0160   0.0742   1.0000
   8.500   0.8326   0.04329   0.03404   0.0170   0.0696   1.0000
   8.750   0.8446   0.04592   0.03697   0.0179   0.0661   1.0000
   9.000   0.8555   0.04874   0.04001   0.0187   0.0642   1.0000
   9.250   0.8654   0.05176   0.04321   0.0194   0.0626   1.0000
   9.500   0.8609   0.05631   0.04823   0.0200   0.0618   1.0000
   9.750   0.8489   0.06120   0.05352   0.0201   0.0614   1.0000
  10.000   0.8307   0.06623   0.05881   0.0196   0.0613   1.0000
  10.250   0.8073   0.07141   0.06408   0.0182   0.0614   1.0000
  10.500   0.7831   0.07807   0.07080   0.0139   0.0618   1.0000
  10.750   0.7604   0.08634   0.07909   0.0076   0.0621   1.0000
<< Back to S9032 (9%) (s9032-il)

Polar data table (+)

Polar graphs


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