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S9033 (7.5%) (s9033-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S9033 (7.5%) (s9033-il)
Reynolds number: 200,000
Max Cl/Cd: 39.61 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9033-il-200000.txt
Download as CSV file: xf-s9033-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9033 (7.5%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.7674   0.08052   0.07710  -0.0007   1.0000   0.0502
  -9.750  -0.7579   0.07862   0.07518   0.0009   1.0000   0.0472
  -9.500  -0.8754   0.05343   0.04929  -0.0163   1.0000   0.0383
  -9.250  -0.8770   0.04920   0.04470  -0.0161   1.0000   0.0380
  -9.000  -0.8768   0.04432   0.03942  -0.0157   1.0000   0.0379
  -8.750  -0.8756   0.03871   0.03332  -0.0151   1.0000   0.0384
  -8.500  -0.8645   0.03501   0.02939  -0.0146   1.0000   0.0399
  -8.250  -0.8478   0.03263   0.02675  -0.0139   1.0000   0.0412
  -8.000  -0.8305   0.02980   0.02353  -0.0130   1.0000   0.0420
  -7.750  -0.8109   0.02742   0.02081  -0.0121   1.0000   0.0430
  -7.500  -0.7897   0.02533   0.01840  -0.0112   1.0000   0.0444
  -7.250  -0.7670   0.02376   0.01655  -0.0104   1.0000   0.0465
  -7.000  -0.7430   0.02264   0.01514  -0.0096   1.0000   0.0486
  -6.750  -0.7210   0.02016   0.01248  -0.0088   1.0000   0.0512
  -6.500  -0.6971   0.01896   0.01125  -0.0081   1.0000   0.0547
  -6.250  -0.6725   0.01797   0.01010  -0.0074   1.0000   0.0594
  -6.000  -0.6493   0.01665   0.00878  -0.0066   1.0000   0.0657
  -5.750  -0.6244   0.01596   0.00801  -0.0059   1.0000   0.0751
  -5.500  -0.5998   0.01529   0.00733  -0.0053   1.0000   0.0865
  -5.250  -0.5756   0.01452   0.00661  -0.0047   1.0000   0.0985
  -5.000  -0.5508   0.01393   0.00601  -0.0041   1.0000   0.1125
  -4.750  -0.5260   0.01335   0.00546  -0.0035   1.0000   0.1289
  -4.500  -0.5016   0.01274   0.00498  -0.0029   1.0000   0.1485
  -4.250  -0.4769   0.01220   0.00454  -0.0022   1.0000   0.1733
  -4.000  -0.4523   0.01167   0.00415  -0.0016   1.0000   0.2022
  -3.750  -0.4277   0.01118   0.00379  -0.0010   1.0000   0.2354
  -3.500  -0.4032   0.01072   0.00350  -0.0004   1.0000   0.2740
  -3.250  -0.3789   0.01028   0.00326   0.0003   1.0000   0.3196
  -3.000  -0.3548   0.00987   0.00305   0.0011   1.0000   0.3696
  -2.750  -0.3310   0.00947   0.00287   0.0019   1.0000   0.4250
  -2.500  -0.3077   0.00907   0.00274   0.0029   1.0000   0.4858
  -2.250  -0.2849   0.00869   0.00265   0.0041   1.0000   0.5519
  -2.000  -0.2627   0.00833   0.00259   0.0055   1.0000   0.6193
  -1.750  -0.2409   0.00801   0.00253   0.0071   1.0000   0.6851
  -1.500  -0.2198   0.00771   0.00251   0.0091   1.0000   0.7516
  -1.250  -0.1990   0.00746   0.00254   0.0113   1.0000   0.8241
  -1.000  -0.1645   0.00739   0.00265   0.0109   1.0000   0.9061
  -0.750  -0.1054   0.00746   0.00272   0.0051   1.0000   0.9660
  -0.500  -0.0458   0.00748   0.00269  -0.0014   1.0000   0.9949
  -0.250  -0.0174   0.00743   0.00261  -0.0018   1.0000   1.0000
   0.000   0.0000   0.00741   0.00259   0.0000   1.0000   1.0000
   0.250   0.0174   0.00743   0.00261   0.0018   1.0000   1.0000
   0.500   0.0457   0.00748   0.00269   0.0014   0.9950   1.0000
   0.750   0.1054   0.00746   0.00272  -0.0051   0.9660   1.0000
   1.000   0.1646   0.00739   0.00265  -0.0109   0.9058   1.0000
   1.250   0.1991   0.00746   0.00254  -0.0113   0.8242   1.0000
   1.500   0.2199   0.00771   0.00251  -0.0091   0.7516   1.0000
   1.750   0.2410   0.00801   0.00253  -0.0071   0.6850   1.0000
   2.000   0.2628   0.00833   0.00259  -0.0055   0.6191   1.0000
   2.250   0.2850   0.00869   0.00265  -0.0041   0.5517   1.0000
   2.500   0.3078   0.00907   0.00274  -0.0029   0.4856   1.0000
   2.750   0.3311   0.00947   0.00287  -0.0019   0.4249   1.0000
   3.000   0.3549   0.00987   0.00305  -0.0011   0.3695   1.0000
   3.250   0.3790   0.01028   0.00326  -0.0003   0.3194   1.0000
   3.500   0.4033   0.01072   0.00350   0.0003   0.2740   1.0000
   3.750   0.4278   0.01118   0.00379   0.0010   0.2353   1.0000
   4.000   0.4524   0.01167   0.00415   0.0016   0.2021   1.0000
   4.250   0.4770   0.01220   0.00454   0.0022   0.1733   1.0000
   4.500   0.5017   0.01274   0.00498   0.0028   0.1485   1.0000
   4.750   0.5261   0.01335   0.00546   0.0034   0.1288   1.0000
   5.000   0.5508   0.01393   0.00601   0.0041   0.1125   1.0000
   5.250   0.5756   0.01453   0.00661   0.0047   0.0985   1.0000
   5.500   0.5998   0.01528   0.00733   0.0053   0.0864   1.0000
   5.750   0.6244   0.01596   0.00801   0.0059   0.0752   1.0000
   6.000   0.6492   0.01665   0.00878   0.0066   0.0657   1.0000
   6.250   0.6725   0.01797   0.01010   0.0074   0.0595   1.0000
   6.500   0.6971   0.01896   0.01126   0.0082   0.0547   1.0000
   6.750   0.7209   0.02015   0.01247   0.0088   0.0513   1.0000
   7.000   0.7429   0.02264   0.01515   0.0097   0.0487   1.0000
   7.250   0.7669   0.02375   0.01654   0.0105   0.0465   1.0000
   7.500   0.7896   0.02532   0.01840   0.0113   0.0444   1.0000
   7.750   0.8108   0.02739   0.02078   0.0121   0.0430   1.0000
   8.000   0.8304   0.02979   0.02351   0.0130   0.0420   1.0000
   8.250   0.8477   0.03262   0.02674   0.0139   0.0412   1.0000
   8.500   0.8641   0.03509   0.02947   0.0146   0.0399   1.0000
   8.750   0.8752   0.03875   0.03336   0.0152   0.0383   1.0000
   9.000   0.8766   0.04431   0.03941   0.0158   0.0379   1.0000
   9.250   0.8774   0.04906   0.04456   0.0162   0.0380   1.0000
   9.500   0.8751   0.05345   0.04931   0.0164   0.0383   1.0000
   9.750   0.7596   0.07808   0.07463  -0.0003   0.0473   1.0000
  10.000   0.7697   0.07983   0.07641   0.0014   0.0501   1.0000
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