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S9032 (9%) (s9032-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S9032 (9%) (s9032-il)
Reynolds number: 50,000
Max Cl/Cd: 23.49 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9032-il-50000.txt
Download as CSV file: xf-s9032-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.7417   0.07647   0.06948  -0.0083   1.0000   0.1561
  -8.500  -0.7470   0.07074   0.06369  -0.0099   1.0000   0.1544
  -8.250  -0.7561   0.06463   0.05744  -0.0117   1.0000   0.1524
  -8.000  -0.7637   0.05855   0.05108  -0.0130   1.0000   0.1512
  -7.750  -0.7657   0.05295   0.04508  -0.0136   1.0000   0.1512
  -7.500  -0.7620   0.04781   0.03944  -0.0134   1.0000   0.1523
  -7.250  -0.7542   0.04319   0.03416  -0.0128   1.0000   0.1552
  -7.000  -0.7362   0.04062   0.03150  -0.0118   1.0000   0.1649
  -6.750  -0.7206   0.03745   0.02788  -0.0108   1.0000   0.1744
  -6.500  -0.7023   0.03468   0.02457  -0.0097   1.0000   0.1854
  -6.250  -0.6812   0.03274   0.02264  -0.0087   1.0000   0.2017
  -6.000  -0.6591   0.03073   0.02053  -0.0076   1.0000   0.2177
  -5.750  -0.6374   0.02914   0.01883  -0.0065   1.0000   0.2395
  -5.500  -0.6145   0.02734   0.01698  -0.0054   1.0000   0.2609
  -5.250  -0.5925   0.02597   0.01564  -0.0041   1.0000   0.2894
  -5.000  -0.5701   0.02466   0.01443  -0.0027   1.0000   0.3210
  -4.750  -0.5485   0.02350   0.01335  -0.0012   1.0000   0.3596
  -4.500  -0.5273   0.02247   0.01249   0.0005   1.0000   0.4027
  -4.250  -0.5064   0.02157   0.01184   0.0026   1.0000   0.4494
  -4.000  -0.4862   0.02077   0.01126   0.0049   1.0000   0.5011
  -3.750  -0.4662   0.02011   0.01086   0.0075   1.0000   0.5538
  -3.500  -0.4467   0.01955   0.01049   0.0105   1.0000   0.6087
  -3.250  -0.4287   0.01910   0.01023   0.0140   1.0000   0.6644
  -3.000  -0.4109   0.01876   0.01006   0.0179   1.0000   0.7192
  -2.750  -0.3916   0.01854   0.00997   0.0220   1.0000   0.7739
  -2.500  -0.3637   0.01850   0.00995   0.0247   1.0000   0.8304
  -2.250  -0.3021   0.01885   0.01010   0.0214   1.0000   0.8896
  -2.000  -0.1824   0.01912   0.00985   0.0059   1.0000   0.9460
  -1.750  -0.0670   0.01815   0.00850  -0.0117   1.0000   0.9960
  -1.500  -0.0492   0.01739   0.00770  -0.0126   1.0000   1.0000
  -1.250  -0.0407   0.01684   0.00714  -0.0113   1.0000   1.0000
  -1.000  -0.0324   0.01640   0.00670  -0.0096   1.0000   1.0000
  -0.750  -0.0245   0.01607   0.00638  -0.0074   1.0000   1.0000
  -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   0.0245   0.01607   0.00638   0.0074   1.0000   1.0000
   1.000   0.0324   0.01640   0.00670   0.0096   1.0000   1.0000
   1.250   0.0407   0.01684   0.00713   0.0113   1.0000   1.0000
   1.500   0.0492   0.01739   0.00770   0.0126   1.0000   1.0000
   1.750   0.0670   0.01815   0.00850   0.0117   0.9960   1.0000
   2.000   0.1822   0.01912   0.00985  -0.0059   0.9460   1.0000
   2.250   0.3021   0.01886   0.01010  -0.0214   0.8895   1.0000
   2.500   0.3638   0.01850   0.00995  -0.0247   0.8303   1.0000
   2.750   0.3918   0.01854   0.00998  -0.0220   0.7737   1.0000
   3.000   0.4111   0.01876   0.01006  -0.0179   0.7190   1.0000
   3.250   0.4290   0.01910   0.01023  -0.0140   0.6643   1.0000
   3.500   0.4470   0.01954   0.01049  -0.0105   0.6085   1.0000
   3.750   0.4664   0.02011   0.01086  -0.0076   0.5535   1.0000
   4.000   0.4864   0.02078   0.01127  -0.0049   0.5009   1.0000
   4.250   0.5066   0.02157   0.01184  -0.0026   0.4492   1.0000
   4.500   0.5276   0.02248   0.01249  -0.0006   0.4026   1.0000
   4.750   0.5487   0.02349   0.01335   0.0012   0.3595   1.0000
   5.000   0.5703   0.02466   0.01443   0.0027   0.3209   1.0000
   5.250   0.5926   0.02597   0.01564   0.0041   0.2893   1.0000
   5.500   0.6147   0.02734   0.01698   0.0053   0.2609   1.0000
   5.750   0.6375   0.02914   0.01883   0.0065   0.2395   1.0000
   6.000   0.6591   0.03072   0.02053   0.0076   0.2176   1.0000
   6.250   0.6812   0.03274   0.02265   0.0087   0.2016   1.0000
   6.500   0.7023   0.03467   0.02457   0.0097   0.1854   1.0000
   6.750   0.7205   0.03744   0.02787   0.0109   0.1743   1.0000
   7.000   0.7360   0.04061   0.03149   0.0119   0.1649   1.0000
   7.250   0.7540   0.04316   0.03413   0.0128   0.1552   1.0000
   7.500   0.7617   0.04779   0.03941   0.0135   0.1523   1.0000
   7.750   0.7654   0.05290   0.04503   0.0137   0.1513   1.0000
   8.000   0.7633   0.05848   0.05101   0.0132   0.1511   1.0000
   8.250   0.7558   0.06458   0.05738   0.0119   0.1525   1.0000
   8.500   0.7465   0.07068   0.06363   0.0101   0.1544   1.0000
   8.750   0.7405   0.07647   0.06948   0.0083   0.1560   1.0000
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