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NREL's S830 Airfoil (s830-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S830 Airfoil (s830-nr)
Reynolds number: 100,000
Max Cl/Cd: 34.19 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s830-nr-100000-n5.txt
Download as CSV file: xf-s830-nr-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1216   0.11794   0.11320  -0.0974   0.9483   0.0267
 -12.500  -0.2570   0.12355   0.11862  -0.0889   0.9733   0.0275
 -12.250  -0.2442   0.12112   0.11617  -0.0895   0.9694   0.0266
 -11.750  -0.2597   0.10272   0.09773  -0.1018   0.9617   0.0220
 -11.500  -0.2593   0.09792   0.09291  -0.1050   0.9575   0.0217
 -11.250  -0.2677   0.09254   0.08749  -0.1080   0.9512   0.0214
 -11.000  -0.2746   0.08681   0.08167  -0.1124   0.9474   0.0211
 -10.750  -0.2894   0.08228   0.07707  -0.1138   0.9389   0.0208
 -10.500  -0.3000   0.07706   0.07171  -0.1172   0.9339   0.0205
 -10.250  -0.3164   0.07333   0.06786  -0.1173   0.9242   0.0203
 -10.000  -0.3251   0.06866   0.06298  -0.1200   0.9193   0.0199
  -9.750  -0.3407   0.06572   0.05991  -0.1187   0.9084   0.0197
  -9.500  -0.3547   0.06281   0.05683  -0.1174   0.8986   0.0195
  -9.250  -0.3604   0.05939   0.05316  -0.1177   0.8924   0.0192
  -9.000  -0.3739   0.05711   0.05070  -0.1149   0.8813   0.0190
  -8.750  -0.3666   0.05307   0.04627  -0.1161   0.8771   0.0186
  -8.500  -0.3708   0.05067   0.04363  -0.1133   0.8665   0.0185
  -8.250  -0.3530   0.04725   0.03983  -0.1138   0.8631   0.0184
  -8.000  -0.3472   0.04523   0.03756  -0.1114   0.8543   0.0184
  -7.750  -0.3243   0.04279   0.03485  -0.1114   0.8505   0.0186
  -7.500  -0.2935   0.04051   0.03231  -0.1120   0.8482   0.0190
  -7.250  -0.2728   0.03909   0.03071  -0.1101   0.8423   0.0194
  -7.000  -0.2452   0.03787   0.02929  -0.1089   0.8378   0.0207
  -6.750  -0.2048   0.03670   0.02793  -0.1089   0.8358   0.0232
  -6.500  -0.1457   0.03595   0.02711  -0.1110   0.8354   0.0256
  -6.250  -0.0862   0.03591   0.02701  -0.1121   0.8348   0.0291
  -6.000  -0.0270   0.03695   0.02811  -0.1132   0.8336   0.0362
  -5.750   0.0020   0.03719   0.02830  -0.1124   0.8283   0.0431
  -5.500   0.0129   0.03694   0.02809  -0.1101   0.8205   0.0492
  -5.000   0.0203   0.03552   0.02661  -0.1049   0.8051   0.0630
  -4.750   0.0179   0.03439   0.02547  -0.1021   0.7982   0.0711
  -4.500   0.0047   0.03354   0.02459  -0.0970   0.7884   0.0775
  -4.250  -0.0043   0.03222   0.02329  -0.0936   0.7797   0.0868
  -4.000  -0.0009   0.03260   0.02548  -0.0898   0.7726   0.3651
  -3.500   0.0411   0.03121   0.02355  -0.0951   0.7588   0.5093
  -3.250   0.0860   0.03435   0.02651  -0.0931   0.7558   0.5304
  -3.000   0.1311   0.03649   0.02849  -0.0924   0.7526   0.5471
  -2.750   0.1318   0.03624   0.02818  -0.0888   0.7436   0.5511
  -2.500   0.1681   0.03572   0.02746  -0.0910   0.7400   0.5521
  -2.250   0.1833   0.03504   0.02667  -0.0904   0.7336   0.5525
  -2.000   0.2021   0.03435   0.02586  -0.0904   0.7273   0.5531
  -1.750   0.2403   0.03348   0.02479  -0.0939   0.7238   0.5535
  -1.500   0.2514   0.03299   0.02423  -0.0925   0.7166   0.5544
  -1.250   0.2767   0.03238   0.02350  -0.0935   0.7113   0.5552
  -1.000   0.3159   0.03171   0.02268  -0.0970   0.7080   0.5564
  -0.750   0.3306   0.03130   0.02220  -0.0962   0.7015   0.5580
  -0.500   0.3566   0.03069   0.02150  -0.0978   0.6961   0.5595
  -0.250   0.3987   0.02989   0.02054  -0.1023   0.6926   0.5610
   0.000   0.4288   0.02903   0.01955  -0.1055   0.6872   0.5636
   0.250   0.4549   0.02849   0.01893  -0.1072   0.6814   0.5655
   0.500   0.4893   0.02824   0.01861  -0.1090   0.6777   0.5662
   0.750   0.5249   0.02802   0.01831  -0.1112   0.6744   0.5669
   1.000   0.5312   0.02817   0.01850  -0.1081   0.6676   0.5679
   1.250   0.5606   0.02805   0.01835  -0.1091   0.6635   0.5691
   1.500   0.5989   0.02784   0.01808  -0.1117   0.6605   0.5704
   1.750   0.6130   0.02793   0.01819  -0.1102   0.6547   0.5721
   2.000   0.6367   0.02788   0.01814  -0.1105   0.6497   0.5741
   2.250   0.6751   0.02759   0.01780  -0.1137   0.6464   0.5762
   2.500   0.7222   0.02720   0.01731  -0.1187   0.6439   0.5787
   2.750   0.7325   0.02738   0.01753  -0.1172   0.6377   0.5811
   3.000   0.7546   0.02753   0.01773  -0.1168   0.6336   0.5821
   3.250   0.7867   0.02752   0.01773  -0.1181   0.6306   0.5832
   3.500   0.8257   0.02743   0.01764  -0.1207   0.6282   0.5845
   3.750   0.8230   0.02808   0.01841  -0.1162   0.6216   0.5858
   4.000   0.8466   0.02827   0.01866  -0.1162   0.6176   0.5876
   4.250   0.8799   0.02828   0.01870  -0.1180   0.6149   0.5898
   4.500   0.9208   0.02818   0.01860  -0.1212   0.6128   0.5924
   4.750   0.9241   0.02897   0.01949  -0.1185   0.6071   0.5952
   5.000   0.9449   0.02936   0.01995  -0.1184   0.6028   0.5972
   5.250   0.9729   0.02949   0.02016  -0.1189   0.5999   0.5985
   5.500   1.0076   0.02947   0.02022  -0.1206   0.5977   0.5999
   5.750   1.0086   0.03056   0.02145  -0.1172   0.5926   0.6013
   6.000   1.0161   0.03152   0.02253  -0.1149   0.5878   0.6030
   6.250   1.0434   0.03175   0.02286  -0.1156   0.5848   0.6049
   6.500   1.0790   0.03172   0.02292  -0.1176   0.5826   0.6075
   6.750   1.0976   0.03242   0.02371  -0.1173   0.5790   0.6102
   7.000   1.0810   0.03463   0.02604  -0.1123   0.5717   0.6126
   7.250   1.1066   0.03488   0.02643  -0.1124   0.5688   0.6140
   7.500   1.1402   0.03479   0.02649  -0.1136   0.5668   0.6159
   8.000   1.1232   0.03881   0.03079  -0.1060   0.5534   0.6189
   8.250   1.1622   0.03834   0.03046  -0.1078   0.5515   0.6213
   8.500   1.2082   0.03759   0.02984  -0.1106   0.5499   0.6240
   9.000   1.1594   0.04423   0.03671  -0.1011   0.5309   0.6273
   9.500   1.1211   0.05167   0.04439  -0.0948   0.5090   0.6298
   9.750   1.1591   0.05025   0.04315  -0.0953   0.5065   0.6320
  10.000   1.2177   0.04695   0.04006  -0.0971   0.5047   0.6351
  10.250   1.1850   0.05187   0.04510  -0.0933   0.4912   0.6362
  10.500   1.2748   0.04537   0.03875  -0.0969   0.4881   0.6407
  10.750   1.2372   0.05069   0.04419  -0.0929   0.4749   0.6418
  11.000   1.2236   0.05423   0.04783  -0.0909   0.4621   0.6433
  11.250   1.2583   0.05251   0.04630  -0.0908   0.4533   0.6456
  11.500   1.2737   0.05282   0.04676  -0.0898   0.4414   0.6476
  11.750   1.2578   0.05669   0.05077  -0.0878   0.4266   0.6489
  12.000   1.2502   0.05987   0.05409  -0.0865   0.4110   0.6506
  12.250   1.2393   0.06369   0.05804  -0.0855   0.3931   0.6523
  12.500   1.2282   0.06780   0.06227  -0.0848   0.3728   0.6540
  12.750   1.2449   0.06829   0.06280  -0.0843   0.3485   0.6568
  13.000   1.2735   0.06704   0.06137  -0.0837   0.3094   0.6600
  13.250   1.2810   0.06827   0.06230  -0.0824   0.2676   0.6617
  13.500   1.2742   0.07166   0.06548  -0.0815   0.2337   0.6631
  13.750   1.2652   0.07561   0.06927  -0.0809   0.2046   0.6645
  14.000   1.2567   0.07969   0.07323  -0.0806   0.1786   0.6660
  14.250   1.2490   0.08380   0.07723  -0.0806   0.1556   0.6676
  14.500   1.2440   0.08770   0.08105  -0.0807   0.1349   0.6695
  14.750   1.2399   0.09159   0.08486  -0.0810   0.1172   0.6715
  15.000   1.2374   0.09535   0.08855  -0.0814   0.1022   0.6736
  15.500   1.2372   0.10217   0.09539  -0.0823   0.0788   0.6774
  15.750   1.2386   0.10536   0.09863  -0.0827   0.0698   0.6793
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