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S9027 (8%) (s9027-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 100,000
Max Cl/Cd: 32.76 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9027-il-100000-n5.txt
Download as CSV file: xf-s9027-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9027 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7907   0.08269   0.07764  -0.0008   1.0000   0.0325
 -10.750  -0.8215   0.07083   0.06575  -0.0106   1.0000   0.0319
 -10.500  -0.8506   0.06245   0.05723  -0.0180   1.0000   0.0315
 -10.250  -0.8761   0.05712   0.05175  -0.0200   1.0000   0.0314
 -10.000  -0.8946   0.05240   0.04673  -0.0199   1.0000   0.0314
  -9.750  -0.9049   0.04772   0.04162  -0.0195   1.0000   0.0318
  -9.500  -0.9070   0.04348   0.03688  -0.0186   1.0000   0.0323
  -9.250  -0.9019   0.03998   0.03275  -0.0175   1.0000   0.0332
  -9.000  -0.8896   0.03752   0.03020  -0.0168   1.0000   0.0348
  -8.750  -0.8735   0.03587   0.02840  -0.0160   1.0000   0.0366
  -8.500  -0.8575   0.03367   0.02588  -0.0151   1.0000   0.0383
  -8.250  -0.8400   0.03136   0.02322  -0.0141   1.0000   0.0399
  -8.000  -0.8207   0.02928   0.02078  -0.0131   1.0000   0.0418
  -7.750  -0.8001   0.02750   0.01868  -0.0122   1.0000   0.0440
  -7.500  -0.7797   0.02618   0.01732  -0.0115   1.0000   0.0473
  -7.250  -0.7578   0.02499   0.01598  -0.0107   1.0000   0.0512
  -7.000  -0.7352   0.02367   0.01439  -0.0098   1.0000   0.0549
  -6.750  -0.7139   0.02239   0.01313  -0.0090   1.0000   0.0590
  -6.500  -0.6910   0.02151   0.01213  -0.0082   1.0000   0.0658
  -6.250  -0.6685   0.02058   0.01119  -0.0074   1.0000   0.0731
  -6.000  -0.6453   0.01974   0.01020  -0.0066   1.0000   0.0815
  -5.750  -0.6221   0.01902   0.00945  -0.0059   1.0000   0.0924
  -5.500  -0.5989   0.01829   0.00873  -0.0052   1.0000   0.1041
  -5.250  -0.5755   0.01762   0.00807  -0.0044   1.0000   0.1185
  -5.000  -0.5519   0.01699   0.00745  -0.0037   1.0000   0.1337
  -4.750  -0.5284   0.01638   0.00688  -0.0030   1.0000   0.1523
  -4.500  -0.5047   0.01582   0.00638  -0.0022   1.0000   0.1736
  -4.250  -0.4810   0.01530   0.00592  -0.0015   1.0000   0.1964
  -4.000  -0.4573   0.01481   0.00553  -0.0007   1.0000   0.2249
  -3.750  -0.4338   0.01433   0.00515   0.0000   1.0000   0.2570
  -3.500  -0.4103   0.01388   0.00484   0.0009   1.0000   0.2937
  -3.250  -0.3871   0.01344   0.00457   0.0017   1.0000   0.3361
  -3.000  -0.3641   0.01302   0.00434   0.0027   1.0000   0.3815
  -2.750  -0.3412   0.01262   0.00412   0.0037   1.0000   0.4300
  -2.500  -0.3185   0.01224   0.00395   0.0049   1.0000   0.4812
  -2.250  -0.2959   0.01189   0.00383   0.0061   1.0000   0.5366
  -2.000  -0.2734   0.01156   0.00374   0.0074   1.0000   0.5954
  -1.750  -0.2510   0.01127   0.00369   0.0089   1.0000   0.6570
  -1.500  -0.2288   0.01103   0.00368   0.0106   1.0000   0.7183
  -1.250  -0.2056   0.01085   0.00370   0.0122   1.0000   0.7792
  -0.750  -0.1382   0.01074   0.00383   0.0111   1.0000   0.8977
  -0.500  -0.0895   0.01077   0.00388   0.0072   1.0000   0.9445
  -0.250  -0.0415   0.01079   0.00388   0.0031   1.0000   0.9802
   0.000   0.0000   0.01078   0.00387   0.0000   1.0000   1.0000
   0.250   0.0415   0.01079   0.00388  -0.0031   0.9803   1.0000
   0.500   0.0895   0.01077   0.00387  -0.0072   0.9445   1.0000
   0.750   0.1382   0.01074   0.00383  -0.0111   0.8977   1.0000
   1.000   0.1777   0.01075   0.00376  -0.0128   0.8397   1.0000
   1.250   0.2055   0.01085   0.00370  -0.0121   0.7796   1.0000
   1.500   0.2287   0.01103   0.00368  -0.0106   0.7185   1.0000
   1.750   0.2508   0.01127   0.00368  -0.0089   0.6569   1.0000
   2.000   0.2732   0.01156   0.00374  -0.0074   0.5954   1.0000
   2.250   0.2957   0.01189   0.00383  -0.0060   0.5368   1.0000
   2.500   0.3182   0.01224   0.00395  -0.0048   0.4813   1.0000
   2.750   0.3410   0.01262   0.00412  -0.0037   0.4302   1.0000
   3.000   0.3639   0.01301   0.00433  -0.0026   0.3816   1.0000
   3.250   0.3869   0.01344   0.00457  -0.0017   0.3364   1.0000
   3.500   0.4101   0.01388   0.00484  -0.0008   0.2939   1.0000
   3.750   0.4335   0.01433   0.00515   0.0000   0.2572   1.0000
   4.000   0.4571   0.01480   0.00553   0.0008   0.2250   1.0000
   4.250   0.4808   0.01530   0.00592   0.0015   0.1965   1.0000
   4.500   0.5045   0.01582   0.00638   0.0023   0.1736   1.0000
   4.750   0.5282   0.01638   0.00688   0.0030   0.1523   1.0000
   5.000   0.5518   0.01699   0.00744   0.0037   0.1339   1.0000
   5.250   0.5754   0.01762   0.00807   0.0045   0.1184   1.0000
   5.500   0.5989   0.01828   0.00873   0.0052   0.1041   1.0000
   5.750   0.6221   0.01902   0.00945   0.0059   0.0924   1.0000
   6.000   0.6453   0.01975   0.01020   0.0066   0.0815   1.0000
   6.250   0.6686   0.02059   0.01118   0.0074   0.0730   1.0000
   6.500   0.6911   0.02151   0.01212   0.0082   0.0657   1.0000
   6.750   0.7141   0.02240   0.01313   0.0089   0.0589   1.0000
   7.000   0.7354   0.02367   0.01440   0.0098   0.0549   1.0000
   7.250   0.7580   0.02499   0.01598   0.0107   0.0512   1.0000
   7.500   0.7800   0.02619   0.01733   0.0115   0.0473   1.0000
   7.750   0.8005   0.02750   0.01868   0.0121   0.0440   1.0000
   8.000   0.8210   0.02930   0.02079   0.0131   0.0418   1.0000
   8.250   0.8404   0.03139   0.02325   0.0140   0.0399   1.0000
   8.500   0.8579   0.03369   0.02591   0.0150   0.0383   1.0000
   8.750   0.8740   0.03589   0.02842   0.0159   0.0366   1.0000
   9.000   0.8902   0.03753   0.03021   0.0167   0.0348   1.0000
   9.250   0.9025   0.04001   0.03279   0.0174   0.0332   1.0000
   9.500   0.9077   0.04353   0.03693   0.0185   0.0323   1.0000
   9.750   0.9055   0.04779   0.04169   0.0193   0.0318   1.0000
  10.000   0.8954   0.05247   0.04680   0.0197   0.0314   1.0000
  10.250   0.8765   0.05725   0.05189   0.0198   0.0314   1.0000
  10.500   0.8514   0.06258   0.05737   0.0177   0.0315   1.0000
  10.750   0.8229   0.07088   0.06580   0.0104   0.0320   1.0000
  11.000   0.7904   0.08321   0.07816   0.0002   0.0325   1.0000
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