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NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S807 Airfoil (s807-nr)
Reynolds number: 50,000
Max Cl/Cd: 20.34 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s807-nr-50000.txt
Download as CSV file: xf-s807-nr-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S807 Airfoil                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.7168   0.09513   0.08739  -0.0500   1.0000   0.1238
 -13.250  -0.7503   0.08725   0.07942  -0.0529   1.0000   0.1226
 -13.000  -0.7833   0.08036   0.07239  -0.0551   1.0000   0.1214
 -12.750  -0.8135   0.07450   0.06636  -0.0564   1.0000   0.1207
 -12.500  -0.8377   0.06963   0.06129  -0.0569   1.0000   0.1205
 -12.250  -0.8558   0.06552   0.05697  -0.0567   1.0000   0.1208
 -12.000  -0.8695   0.06193   0.05314  -0.0559   1.0000   0.1217
 -11.750  -0.8802   0.05873   0.04967  -0.0546   1.0000   0.1230
 -11.500  -0.8437   0.05656   0.04753  -0.0534   1.0000   0.1298
 -11.250  -0.8345   0.05432   0.04513  -0.0519   1.0000   0.1361
 -11.000  -0.7985   0.05317   0.04407  -0.0499   1.0000   0.1489
 -10.750  -0.7729   0.05205   0.04306  -0.0474   1.0000   0.1647
 -10.500  -0.7643   0.05034   0.04149  -0.0451   1.0000   0.1835
 -10.250  -0.7561   0.04914   0.04085  -0.0419   1.0000   0.2128
  -9.000  -0.4111   0.09227   0.08388  -0.0090   1.0000   0.4652
  -8.750  -0.3283   0.09489   0.08624  -0.0051   1.0000   0.5564
  -8.500  -0.3196   0.09304   0.08433  -0.0040   1.0000   0.5785
  -8.250  -0.3141   0.09132   0.08255  -0.0028   1.0000   0.5978
  -8.000  -0.3060   0.08943   0.08059  -0.0017   1.0000   0.6157
  -7.750  -0.2979   0.08763   0.07874  -0.0005   1.0000   0.6334
  -7.500  -0.2853   0.08550   0.07654   0.0002   1.0000   0.6504
  -7.250  -0.2719   0.08339   0.07437   0.0008   1.0000   0.6673
  -7.000  -0.2553   0.08105   0.07196   0.0011   1.0000   0.6836
  -6.750  -0.2387   0.07881   0.06966   0.0014   1.0000   0.6995
  -6.500  -0.2222   0.07662   0.06742   0.0017   1.0000   0.7150
  -6.250  -0.2067   0.07462   0.06538   0.0021   1.0000   0.7304
  -6.000  -0.1916   0.07274   0.06347   0.0026   1.0000   0.7461
  -5.750  -0.1764   0.07096   0.06165   0.0031   1.0000   0.7623
  -5.500  -0.1607   0.06921   0.05988   0.0035   1.0000   0.7787
  -5.250  -0.1444   0.06755   0.05820   0.0039   1.0000   0.7963
  -5.000  -0.1284   0.06602   0.05665   0.0044   1.0000   0.8146
  -4.750  -0.1205   0.06534   0.05599   0.0062   1.0000   0.8346
  -4.250  -0.0657   0.06065   0.05130   0.0032   1.0000   0.8720
  -4.000  -0.0459   0.05960   0.05025   0.0031   1.0000   0.8988
  -3.750  -0.0060   0.05665   0.04731  -0.0010   1.0000   0.9212
  -3.500   0.0357   0.05427   0.04492  -0.0058   1.0000   0.9518
  -3.000   0.1377   0.04896   0.03962  -0.0208   1.0000   1.0000
  -2.750   0.1464   0.04839   0.03918  -0.0196   1.0000   1.0000
  -2.500   0.1535   0.04798   0.03893  -0.0183   1.0000   1.0000
  -2.250   0.1569   0.04791   0.03908  -0.0167   1.0000   1.0000
  -2.000   0.2078   0.04662   0.03811  -0.0267   0.9765   1.0000
  -1.750   0.3371   0.04050   0.03200  -0.0492   0.8774   1.0000
  -1.500   0.4636   0.03589   0.02677  -0.0707   0.7908   1.0000
  -1.250   0.5084   0.03494   0.02526  -0.0755   0.7344   1.0000
  -1.000   0.5348   0.03464   0.02467  -0.0767   0.7012   1.0000
  -0.750   0.5586   0.03444   0.02427  -0.0775   0.6772   1.0000
  -0.500   0.5818   0.03430   0.02400  -0.0783   0.6578   1.0000
  -0.250   0.6038   0.03421   0.02385  -0.0788   0.6411   1.0000
   0.000   0.6239   0.03420   0.02383  -0.0790   0.6265   1.0000
   0.250   0.6432   0.03426   0.02389  -0.0790   0.6140   1.0000
   0.500   0.6634   0.03434   0.02391  -0.0791   0.6039   1.0000
   0.750   0.6798   0.03455   0.02423  -0.0786   0.5937   1.0000
   1.000   0.6985   0.03476   0.02440  -0.0784   0.5855   1.0000
   1.250   0.7136   0.03508   0.02484  -0.0777   0.5766   1.0000
   1.500   0.5382   0.04123   0.03096  -0.0440   0.5868   0.8656
   1.750   0.5268   0.04163   0.03153  -0.0397   0.5803   0.8469
   2.000   0.5096   0.04209   0.03205  -0.0343   0.5753   0.8330
   2.250   0.5233   0.04208   0.03201  -0.0333   0.5688   0.8291
   2.500   0.4806   0.04283   0.03290  -0.0240   0.5659   0.8172
   2.750   0.4779   0.04316   0.03335  -0.0208   0.5597   0.8135
   3.000   0.4794   0.04338   0.03361  -0.0182   0.5549   0.8114
   3.250   0.4816   0.04373   0.03399  -0.0157   0.5510   0.8107
   3.500   0.4585   0.04463   0.03508  -0.0102   0.5470   0.8093
   3.750   0.4444   0.04548   0.03607  -0.0062   0.5425   0.8089
   4.000   0.4500   0.04603   0.03666  -0.0048   0.5377   0.8096
   4.250   0.4635   0.04659   0.03725  -0.0043   0.5332   0.8111
   4.500   0.4260   0.04892   0.03979   0.0006   0.5298   0.8116
   4.750   0.3871   0.05207   0.04308   0.0042   0.5274   0.8127
   5.000   0.3313   0.05671   0.04783   0.0068   0.5275   0.8135
   5.250   0.3040   0.06139   0.05256   0.0052   0.5284   0.8154
   5.500   0.3003   0.06489   0.05610   0.0024   0.5292   0.8180
   5.750   0.3070   0.06760   0.05887   0.0005   0.5321   0.8207
   6.000   0.3244   0.06993   0.06126  -0.0016   0.5342   0.8240
   7.000   0.2120   0.08727   0.07891  -0.0144   0.6817   0.8316
   7.250   0.2346   0.08954   0.08122  -0.0165   0.6703   0.8363
   7.500   0.2631   0.09200   0.08376  -0.0184   0.6587   0.8420
   7.750   0.2726   0.09333   0.08514  -0.0190   0.6442   0.8465
   8.000   0.2897   0.09544   0.08730  -0.0208   0.6307   0.8513
   8.250   0.3276   0.09924   0.09118  -0.0234   0.6219   0.8580
   8.500   0.3339   0.10024   0.09225  -0.0237   0.6068   0.8633
   8.750   0.3421   0.10190   0.09397  -0.0243   0.5926   0.8689
   9.000   0.3545   0.10404   0.09618  -0.0248   0.5807   0.8756
   9.250   0.3911   0.10781   0.10007  -0.0273   0.5701   0.8853
   9.500   0.3895   0.10871   0.10103  -0.0269   0.5556   0.8918
   9.750   0.3982   0.11084   0.10324  -0.0278   0.5424   0.8997
  10.000   0.4355   0.11525   0.10779  -0.0298   0.5339   0.9133
  10.250   0.4327   0.11592   0.10855  -0.0295   0.5194   0.9230
  10.500   0.4360   0.11777   0.11050  -0.0301   0.5065   0.9360
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