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NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NREL's S830 Airfoil (s830-nr)
Reynolds number: 50,000
Max Cl/Cd: 4.17 at α=12.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s830-nr-50000.txt
Download as CSV file: xf-s830-nr-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S830 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3666   0.13441   0.12939  -0.0048   1.0000   0.4517
  -7.500  -0.4548   0.12481   0.11998  -0.0100   1.0000   0.3501
  -7.250  -0.5115   0.11635   0.11167  -0.0137   1.0000   0.3080
  -7.000  -0.5626   0.10925   0.10473  -0.0157   1.0000   0.2904
  -6.750  -0.6197   0.10263   0.09829  -0.0163   1.0000   0.2845
  -6.500  -0.6701   0.09713   0.09291  -0.0152   1.0000   0.2843
  -6.250  -0.7178   0.08999   0.08586  -0.0166   1.0000   0.2820
  -6.000  -0.7879   0.07741   0.07312  -0.0263   1.0000   0.2884
  -5.750  -0.7771   0.06757   0.06184  -0.0423   1.0000   0.2359
  -5.500  -0.7402   0.06579   0.05907  -0.0454   1.0000   0.1866
  -5.250  -0.7100   0.06391   0.05651  -0.0458   1.0000   0.1537
  -5.000  -0.6854   0.06163   0.05379  -0.0454   1.0000   0.1344
  -4.750  -0.6608   0.05999   0.05164  -0.0451   1.0000   0.1207
  -4.500  -0.6333   0.05932   0.05019  -0.0450   1.0000   0.1091
  -4.250  -0.6167   0.05688   0.04779  -0.0435   1.0000   0.1061
  -4.000  -0.5982   0.05536   0.04614  -0.0422   1.0000   0.1037
  -3.750  -0.5796   0.05423   0.04485  -0.0409   1.0000   0.1041
  -3.500  -0.5632   0.05353   0.04405  -0.0385   1.0000   0.1045
  -3.250  -0.5490   0.05318   0.04367  -0.0352   1.0000   0.1051
  -3.000  -0.5375   0.05321   0.04371  -0.0305   1.0000   0.1056
  -2.750  -0.5279   0.05363   0.04409  -0.0251   1.0000   0.1071
  -2.500  -0.5184   0.05427   0.04473  -0.0196   0.9997   0.1104
  -2.250  -0.5089   0.05555   0.04625  -0.0135   0.9969   0.1170
  -2.000  -0.4920   0.05699   0.04768  -0.0099   0.9939   0.1232
  -1.750  -0.3244   0.08030   0.07326   0.0228   0.9965   0.8761
  -1.250  -0.3973   0.05872   0.05136  -0.0193   0.9838   0.5378
  -1.000  -0.4206   0.06539   0.05809   0.0007   0.9788   0.5990
  -0.750  -0.4381   0.07091   0.06360   0.0201   0.9744   0.6607
  -0.500  -0.4390   0.07619   0.06882   0.0430   0.9726   0.7630
   0.000  -0.0111   0.08517   0.07610  -0.0192   0.9788   1.0000
   0.250   0.0040   0.08569   0.07653  -0.0200   0.9743   1.0000
   0.500   0.0151   0.08637   0.07713  -0.0200   0.9720   1.0000
   0.750   0.0209   0.08615   0.07686  -0.0189   0.9676   1.0000
   1.000   0.0367   0.08671   0.07736  -0.0197   0.9619   1.0000
   1.250   0.0477   0.08739   0.07798  -0.0197   0.9586   1.0000
   1.500   0.0540   0.08719   0.07776  -0.0186   0.9529   1.0000
   1.750   0.0705   0.08806   0.07856  -0.0196   0.9477   1.0000
   2.000   0.0762   0.08825   0.07873  -0.0184   0.9437   1.0000
   2.250  -0.2164   0.07933   0.07012   0.0412   0.9274   0.8976
   2.500  -0.2698   0.07751   0.06828   0.0515   0.9195   0.8707
   2.750  -0.2753   0.07600   0.06671   0.0534   0.9133   0.8608
   3.000  -0.2534   0.07658   0.06716   0.0506   0.9075   0.8542
   3.250  -0.2378   0.07672   0.06721   0.0488   0.9033   0.8480
   3.500  -0.2152   0.07709   0.06747   0.0454   0.8959   0.8426
   3.750  -0.1824   0.07884   0.06911   0.0411   0.8915   0.8392
   4.000  -0.1711   0.07810   0.06834   0.0404   0.8850   0.8359
   4.250  -0.1391   0.07947   0.06962   0.0359   0.8790   0.8332
   4.500  -0.1155   0.08035   0.07045   0.0327   0.8744   0.8310
   4.750  -0.0889   0.08118   0.07122   0.0290   0.8667   0.8293
   5.000  -0.0510   0.08372   0.07370   0.0237   0.8621   0.8283
   5.250  -0.0415   0.08306   0.07305   0.0236   0.8547   0.8272
   5.500  -0.0085   0.08488   0.07484   0.0193   0.8485   0.8263
   5.750   0.0095   0.08558   0.07553   0.0175   0.8429   0.8252
   6.000   0.0371   0.08685   0.07681   0.0141   0.8349   0.8244
   6.250   0.0677   0.08907   0.07903   0.0101   0.8304   0.8237
   6.500   0.0841   0.08935   0.07933   0.0085   0.8212   0.8233
   6.750   0.1232   0.09250   0.08250   0.0032   0.8162   0.8237
   7.000   0.1311   0.09223   0.08228   0.0030   0.8073   0.8239
   7.250   0.1680   0.09512   0.08521  -0.0019   0.8013   0.8250
   7.500   0.1782   0.09546   0.08560  -0.0026   0.7927   0.8255
   7.750   0.2151   0.09842   0.08861  -0.0075   0.7859   0.8269
   8.000   0.2256   0.09903   0.08928  -0.0085   0.7771   0.8275
   8.250   0.2637   0.10226   0.09260  -0.0136   0.7702   0.8287
   8.500   0.2722   0.10283   0.09325  -0.0143   0.7607   0.8292
   8.750   0.3091   0.10623   0.09674  -0.0187   0.7541   0.8306
   9.000   0.3146   0.10656   0.09715  -0.0189   0.7437   0.8312
   9.250   0.3519   0.11044   0.10114  -0.0234   0.7378   0.8335
   9.500   0.3570   0.11064   0.10145  -0.0235   0.7261   0.8348
   9.750   0.3752   0.11289   0.10380  -0.0257   0.7186   0.8368
  10.000   0.4038   0.11559   0.10662  -0.0290   0.7082   0.8394
  10.250   0.4133   0.11706   0.10821  -0.0303   0.6979   0.8410
  10.500   0.4497   0.12121   0.11250  -0.0351   0.6902   0.8438
  10.750   0.4586   0.12220   0.11361  -0.0358   0.6780   0.8454
  11.000   0.4688   0.12404   0.11558  -0.0370   0.6675   0.8471
  11.250   0.5032   0.12813   0.11985  -0.0408   0.6590   0.8500
  11.500   0.5136   0.12954   0.12139  -0.0421   0.6458   0.8521
  11.750   0.5228   0.13152   0.12350  -0.0436   0.6340   0.8541
  12.000   0.5411   0.13445   0.12657  -0.0462   0.6233   0.8570
  12.250   0.5746   0.13854   0.13087  -0.0496   0.6120   0.8610
  12.500   0.5846   0.14017   0.13265  -0.0507   0.5979   0.8638
  12.750   0.5919   0.14212   0.13474  -0.0520   0.5845   0.8663
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