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


Details Polar file
Airfoil: S9032 (9%) (s9032-il)
Reynolds number: 100,000
Max Cl/Cd: 32.74 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9032-il-100000.txt
Download as CSV file: xf-s9032-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.7379   0.08392   0.07899  -0.0071   1.0000   0.0901
  -9.750  -0.7529   0.07538   0.07045  -0.0125   1.0000   0.0842
  -9.500  -0.8555   0.06105   0.05541  -0.0199   1.0000   0.0748
  -9.250  -0.8579   0.05567   0.04983  -0.0196   1.0000   0.0742
  -9.000  -0.8591   0.05062   0.04445  -0.0190   1.0000   0.0736
  -8.750  -0.8575   0.04590   0.03928  -0.0180   1.0000   0.0734
  -8.500  -0.8514   0.04166   0.03450  -0.0167   1.0000   0.0738
  -8.250  -0.8410   0.03816   0.03039  -0.0152   1.0000   0.0747
  -8.000  -0.8256   0.03489   0.02696  -0.0144   1.0000   0.0779
  -7.750  -0.8055   0.03308   0.02504  -0.0136   1.0000   0.0821
  -7.500  -0.7867   0.03060   0.02208  -0.0123   1.0000   0.0858
  -7.250  -0.7662   0.02806   0.01914  -0.0112   1.0000   0.0899
  -7.000  -0.7437   0.02648   0.01751  -0.0104   1.0000   0.0967
  -6.750  -0.7215   0.02488   0.01578  -0.0095   1.0000   0.1058
  -6.500  -0.6985   0.02349   0.01415  -0.0085   1.0000   0.1163
  -6.250  -0.6756   0.02239   0.01299  -0.0076   1.0000   0.1294
  -6.000  -0.6525   0.02120   0.01183  -0.0068   1.0000   0.1437
  -5.750  -0.6296   0.02013   0.01086  -0.0060   1.0000   0.1602
  -5.500  -0.6067   0.01917   0.00999  -0.0051   1.0000   0.1792
  -5.250  -0.5840   0.01825   0.00913  -0.0041   1.0000   0.2025
  -5.000  -0.5613   0.01738   0.00835  -0.0031   1.0000   0.2292
  -4.750  -0.5392   0.01655   0.00772  -0.0020   1.0000   0.2600
  -4.500  -0.5173   0.01583   0.00716  -0.0009   1.0000   0.2971
  -4.250  -0.4957   0.01515   0.00670   0.0003   1.0000   0.3378
  -4.000  -0.4742   0.01455   0.00632   0.0016   1.0000   0.3829
  -3.750  -0.4529   0.01401   0.00600   0.0030   1.0000   0.4319
  -3.500  -0.4319   0.01352   0.00575   0.0046   1.0000   0.4812
  -3.250  -0.4110   0.01310   0.00554   0.0063   1.0000   0.5328
  -3.000  -0.3903   0.01272   0.00540   0.0081   1.0000   0.5824
  -2.750  -0.3697   0.01240   0.00527   0.0100   1.0000   0.6334
  -2.500  -0.3495   0.01212   0.00518   0.0122   1.0000   0.6823
  -2.250  -0.3298   0.01189   0.00514   0.0146   1.0000   0.7320
  -2.000  -0.3100   0.01171   0.00512   0.0172   1.0000   0.7819
  -1.750  -0.2881   0.01162   0.00517   0.0195   1.0000   0.8315
  -1.500  -0.2593   0.01165   0.00526   0.0205   1.0000   0.8814
  -1.250  -0.2108   0.01186   0.00543   0.0175   1.0000   0.9251
  -1.000  -0.1442   0.01210   0.00556   0.0106   1.0000   0.9568
  -0.750  -0.0690   0.01215   0.00550   0.0015   1.0000   0.9810
  -0.500   0.0037   0.01193   0.00520  -0.0078   1.0000   1.0000
  -0.250   0.0028   0.01167   0.00498  -0.0042   1.0000   1.0000
   0.000   0.0000   0.01158   0.00490   0.0000   1.0000   1.0000
   0.250  -0.0028   0.01167   0.00498   0.0042   1.0000   1.0000
   0.500  -0.0037   0.01193   0.00520   0.0078   1.0000   1.0000
   0.750   0.0690   0.01215   0.00550  -0.0015   0.9810   1.0000
   1.000   0.1443   0.01210   0.00556  -0.0106   0.9567   1.0000
   1.250   0.2109   0.01186   0.00543  -0.0175   0.9249   1.0000
   1.500   0.2595   0.01165   0.00526  -0.0205   0.8814   1.0000
   1.750   0.2883   0.01162   0.00517  -0.0195   0.8314   1.0000
   2.000   0.3103   0.01171   0.00513  -0.0172   0.7818   1.0000
   2.250   0.3301   0.01189   0.00514  -0.0147   0.7320   1.0000
   2.500   0.3498   0.01212   0.00518  -0.0123   0.6822   1.0000
   2.750   0.3700   0.01240   0.00527  -0.0101   0.6331   1.0000
   3.000   0.3906   0.01272   0.00540  -0.0082   0.5822   1.0000
   3.250   0.4114   0.01310   0.00554  -0.0063   0.5327   1.0000
   3.500   0.4323   0.01352   0.00575  -0.0047   0.4810   1.0000
   3.750   0.4533   0.01401   0.00601  -0.0031   0.4316   1.0000
   4.000   0.4745   0.01455   0.00632  -0.0017   0.3827   1.0000
   4.250   0.4960   0.01515   0.00671  -0.0004   0.3375   1.0000
   4.500   0.5176   0.01583   0.00717   0.0008   0.2969   1.0000
   4.750   0.5395   0.01655   0.00772   0.0020   0.2599   1.0000
   5.000   0.5615   0.01738   0.00836   0.0030   0.2291   1.0000
   5.250   0.5842   0.01826   0.00914   0.0041   0.2024   1.0000
   5.500   0.6069   0.01917   0.00999   0.0050   0.1792   1.0000
   5.750   0.6297   0.02013   0.01086   0.0059   0.1602   1.0000
   6.000   0.6525   0.02121   0.01184   0.0068   0.1437   1.0000
   6.250   0.6756   0.02240   0.01300   0.0076   0.1294   1.0000
   6.500   0.6984   0.02348   0.01414   0.0085   0.1163   1.0000
   6.750   0.7214   0.02487   0.01577   0.0095   0.1058   1.0000
   7.000   0.7436   0.02649   0.01752   0.0104   0.0967   1.0000
   7.250   0.7661   0.02805   0.01914   0.0112   0.0899   1.0000
   7.500   0.7865   0.03059   0.02207   0.0124   0.0858   1.0000
   7.750   0.8052   0.03308   0.02504   0.0137   0.0822   1.0000
   8.000   0.8252   0.03490   0.02697   0.0145   0.0779   1.0000
   8.250   0.8407   0.03815   0.03037   0.0153   0.0748   1.0000
   8.500   0.8510   0.04161   0.03446   0.0168   0.0738   1.0000
   8.750   0.8569   0.04586   0.03924   0.0181   0.0734   1.0000
   9.000   0.8587   0.05055   0.04437   0.0191   0.0736   1.0000
   9.250   0.8569   0.05562   0.04978   0.0198   0.0741   1.0000
   9.500   0.8553   0.06097   0.05532   0.0200   0.0748   1.0000
   9.750   0.6296   0.07871   0.07396   0.0047   0.0930   1.0000
  10.000   0.6419   0.08048   0.07577   0.0061   0.0902   1.0000
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