Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S833 Airfoil (s833-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S833 Airfoil (s833-nr)
Reynolds number: 100,000
Max Cl/Cd: 39.4 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s833-nr-100000.txt
Download as CSV file: xf-s833-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S833 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.500  -0.4809   0.17142   0.16543  -0.0320   1.0000   0.1889
 -15.250  -0.4833   0.16906   0.16306  -0.0325   1.0000   0.1957
 -15.000  -0.9921   0.07139   0.06534  -0.0783   1.0000   0.1388
 -14.500  -0.9158   0.07582   0.06998  -0.0738   1.0000   0.1512
 -14.250  -0.9982   0.06532   0.05924  -0.0752   1.0000   0.1500
 -14.000  -1.0499   0.05954   0.05323  -0.0739   1.0000   0.1504
 -13.750  -1.0911   0.05548   0.04896  -0.0712   1.0000   0.1514
 -13.500  -1.1292   0.05234   0.04559  -0.0674   1.0000   0.1524
 -13.250  -1.0875   0.05289   0.04642  -0.0673   1.0000   0.1596
 -13.000  -1.1107   0.05066   0.04407  -0.0639   1.0000   0.1621
 -12.750  -1.1413   0.04850   0.04175  -0.0592   1.0000   0.1640
 -12.500  -1.1740   0.04671   0.03979  -0.0536   1.0000   0.1656
 -12.250  -1.2011   0.04467   0.03744  -0.0488   1.0000   0.1678
 -12.000  -1.1697   0.04448   0.03757  -0.0486   1.0000   0.1746
 -11.750  -1.1798   0.04297   0.03589  -0.0451   1.0000   0.1791
 -11.500  -1.1952   0.04102   0.03358  -0.0414   1.0000   0.1831
 -11.250  -1.1708   0.04070   0.03353  -0.0406   1.0000   0.1897
 -11.000  -1.1719   0.03932   0.03194  -0.0381   1.0000   0.1956
 -10.750  -1.1629   0.03820   0.03078  -0.0363   1.0000   0.2018
 -10.500  -1.1510   0.03748   0.03006  -0.0347   1.0000   0.2085
 -10.250  -1.1459   0.03606   0.02837  -0.0330   1.0000   0.2155
 -10.000  -1.1281   0.03564   0.02809  -0.0317   1.0000   0.2226
  -9.750  -1.1201   0.03433   0.02646  -0.0304   1.0000   0.2306
  -9.500  -1.1009   0.03396   0.02630  -0.0292   1.0000   0.2379
  -9.250  -1.0889   0.03286   0.02492  -0.0283   1.0000   0.2470
  -9.000  -1.0699   0.03250   0.02473  -0.0272   1.0000   0.2546
  -8.750  -1.0545   0.03157   0.02359  -0.0265   1.0000   0.2641
  -8.500  -1.0358   0.03121   0.02331  -0.0255   1.0000   0.2726
  -8.250  -1.0181   0.03048   0.02249  -0.0248   1.0000   0.2820
  -8.000  -0.9992   0.03002   0.02197  -0.0241   1.0000   0.2918
  -7.750  -0.9800   0.02955   0.02153  -0.0234   1.0000   0.3010
  -7.500  -0.9604   0.02892   0.02070  -0.0232   1.0000   0.3122
  -7.250  -0.9405   0.02871   0.02064  -0.0222   1.0000   0.3213
  -7.000  -0.9202   0.02824   0.02009  -0.0218   1.0000   0.3321
  -6.750  -0.8994   0.02786   0.01962  -0.0215   1.0000   0.3435
  -6.500  -0.8791   0.02766   0.01953  -0.0207   1.0000   0.3531
  -6.250  -0.8579   0.02730   0.01910  -0.0205   1.0000   0.3648
  -6.000  -0.8365   0.02706   0.01881  -0.0201   1.0000   0.3766
  -5.750  -0.8160   0.02694   0.01878  -0.0193   1.0000   0.3868
  -5.500  -0.7943   0.02669   0.01849  -0.0191   1.0000   0.3988
  -5.250  -0.7722   0.02651   0.01822  -0.0190   1.0000   0.4118
  -5.000  -0.7521   0.02652   0.01836  -0.0180   1.0000   0.4219
  -4.750  -0.7306   0.02642   0.01826  -0.0177   1.0000   0.4340
  -4.500  -0.7083   0.02631   0.01808  -0.0176   1.0000   0.4473
  -4.250  -0.6881   0.02639   0.01826  -0.0167   1.0000   0.4584
  -4.000  -0.6674   0.02645   0.01837  -0.0161   1.0000   0.4700
  -3.750  -0.6458   0.02648   0.01838  -0.0158   1.0000   0.4831
  -3.500  -0.6238   0.02656   0.01843  -0.0156   1.0000   0.4968
  -3.250  -0.6053   0.02684   0.01885  -0.0142   1.0000   0.5067
  -3.000  -0.5848   0.02704   0.01908  -0.0136   1.0000   0.5189
  -2.750  -0.5635   0.02722   0.01924  -0.0133   1.0000   0.5322
  -2.500  -0.5449   0.02760   0.01970  -0.0120   1.0000   0.5428
  -2.250  -0.5259   0.02797   0.02013  -0.0110   1.0000   0.5540
  -2.000  -0.5033   0.02838   0.02054  -0.0109   0.9993   0.5669
  -1.750  -0.4104   0.03156   0.02372  -0.0222   0.9618   0.5846
  -1.500  -0.3716   0.03229   0.02443  -0.0245   0.9501   0.5986
  -1.250  -0.3359   0.03356   0.02579  -0.0254   0.9419   0.6073
  -1.000  -0.3108   0.03379   0.02602  -0.0253   0.9326   0.6185
  -0.750  -0.2783   0.03429   0.02649  -0.0267   0.9243   0.6319
  -0.500  -0.2516   0.03511   0.02740  -0.0259   0.9168   0.6388
  -0.250  -0.2252   0.03541   0.02769  -0.0262   0.9082   0.6508
   0.000  -0.1930   0.03620   0.02852  -0.0265   0.9015   0.6597
   0.250  -0.1721   0.03644   0.02878  -0.0257   0.8922   0.6699
   0.500  -0.1312   0.03696   0.02927  -0.0284   0.8862   0.6832
   0.750  -0.1189   0.03731   0.02971  -0.0252   0.8761   0.6892
   1.000  -0.0767   0.03777   0.03016  -0.0279   0.8705   0.7019
   1.250  -0.0660   0.03804   0.03050  -0.0248   0.8600   0.7087
   1.500  -0.0226   0.03839   0.03086  -0.0274   0.8545   0.7206
   1.750  -0.0116   0.03858   0.03111  -0.0246   0.8434   0.7289
   2.000   0.0315   0.03881   0.03136  -0.0268   0.8382   0.7395
   2.250   0.0459   0.03892   0.03151  -0.0251   0.8265   0.7498
   2.500   0.0755   0.03903   0.03167  -0.0249   0.8190   0.7584
   2.750   0.1039   0.03906   0.03172  -0.0255   0.8092   0.7699
   3.000   0.1231   0.03912   0.03186  -0.0234   0.7997   0.7777
   3.250   0.1589   0.03894   0.03172  -0.0247   0.7918   0.7884
   3.500   0.1770   0.03897   0.03181  -0.0229   0.7808   0.7974
   3.750   0.2161   0.03853   0.03143  -0.0240   0.7743   0.8071
   4.000   0.2366   0.03851   0.03147  -0.0231   0.7621   0.8172
   4.250   0.2767   0.03774   0.03078  -0.0237   0.7569   0.8260
   4.500   0.2981   0.03767   0.03077  -0.0231   0.7438   0.8360
   4.750   0.3413   0.03651   0.02971  -0.0237   0.7395   0.8447
   5.000   0.3601   0.03630   0.02957  -0.0223   0.7258   0.8540
   5.250   0.4097   0.03477   0.02814  -0.0239   0.7225   0.8632
   5.500   0.4263   0.03438   0.02784  -0.0218   0.7083   0.8720
   5.750   0.4524   0.03380   0.02735  -0.0211   0.6957   0.8815
   6.000   0.4977   0.03176   0.02543  -0.0213   0.6913   0.8899
   6.250   0.5246   0.03082   0.02459  -0.0203   0.6789   0.8989
   6.500   0.5773   0.02837   0.02226  -0.0215   0.6745   0.9076
   6.750   0.6076   0.02715   0.02116  -0.0206   0.6609   0.9163
   7.000   0.6499   0.02548   0.01959  -0.0212   0.6478   0.9251
   7.250   0.6928   0.02384   0.01805  -0.0219   0.6309   0.9334
   7.500   0.7377   0.02245   0.01669  -0.0232   0.6083   0.9419
   7.750   0.7679   0.02177   0.01602  -0.0228   0.5783   0.9510
   8.000   0.8005   0.02133   0.01552  -0.0230   0.5415   0.9600
   8.250   0.8284   0.02134   0.01540  -0.0230   0.4985   0.9696
   8.500   0.8562   0.02173   0.01557  -0.0234   0.4504   0.9795
   8.750   0.8767   0.02235   0.01596  -0.0231   0.4043   0.9967
   9.000   0.8848   0.02308   0.01645  -0.0209   0.3680   1.0000
   9.250   0.8940   0.02403   0.01722  -0.0191   0.3320   1.0000
   9.500   0.9044   0.02514   0.01814  -0.0177   0.2973   1.0000
   9.750   0.9157   0.02639   0.01918  -0.0166   0.2649   1.0000
  10.000   0.9274   0.02775   0.02035  -0.0157   0.2351   1.0000
  10.250   0.9393   0.02917   0.02167  -0.0149   0.2070   1.0000
  10.500   0.9524   0.03072   0.02303  -0.0143   0.1825   1.0000
  10.750   0.9658   0.03228   0.02450  -0.0138   0.1606   1.0000
  11.000   0.9800   0.03392   0.02600  -0.0134   0.1421   1.0000
  11.250   0.9963   0.03562   0.02754  -0.0133   0.1258   1.0000
  11.500   1.0124   0.03731   0.02919  -0.0131   0.1121   1.0000
  11.750   1.0292   0.03904   0.03094  -0.0130   0.1004   1.0000
  12.000   1.0492   0.04089   0.03281  -0.0131   0.0904   1.0000
  12.250   1.0709   0.04280   0.03467  -0.0134   0.0820   1.0000
  12.500   1.0916   0.04459   0.03641  -0.0136   0.0751   1.0000
  12.750   1.1095   0.04681   0.03883  -0.0135   0.0693   1.0000
  13.000   1.1444   0.04905   0.04082  -0.0151   0.0635   1.0000
  13.250   1.1465   0.05142   0.04361  -0.0136   0.0607   1.0000
  13.500   1.1571   0.05369   0.04604  -0.0131   0.0575   1.0000
  13.750   1.1855   0.05644   0.04868  -0.0142   0.0542   1.0000
  14.000   1.1795   0.05960   0.05229  -0.0125   0.0531   1.0000
  14.250   1.1729   0.06305   0.05609  -0.0111   0.0520   1.0000
  14.500   1.1653   0.06661   0.05996  -0.0101   0.0508   1.0000
  14.750   1.1590   0.07018   0.06376  -0.0095   0.0497   1.0000
  15.000   1.1659   0.07283   0.06644  -0.0095   0.0481   1.0000
  15.250   1.1783   0.07649   0.07004  -0.0100   0.0466   1.0000
  15.500   1.1558   0.08121   0.07510  -0.0098   0.0464   1.0000
  15.750   1.1335   0.08643   0.08061  -0.0103   0.0464   1.0000
  16.000   1.1101   0.09219   0.08666  -0.0116   0.0464   1.0000
  16.250   1.0883   0.09834   0.09304  -0.0137   0.0465   1.0000
  16.500   1.0646   0.10512   0.10008  -0.0167   0.0466   1.0000
<< Back to NREL's S833 Airfoil (s833-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S833 Airfoil (s833-nr)