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NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NREL's S832 Airfoil (s832-nr)
Reynolds number: 200,000
Max Cl/Cd: 54.66 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s832-nr-200000.txt
Download as CSV file: xf-s832-nr-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S832 Airfoil                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.0002   0.10994   0.10597  -0.1281   0.9037   0.0246
 -11.250  -0.0002   0.10792   0.10396  -0.1301   0.8975   0.0250
 -11.000   0.0010   0.10565   0.10166  -0.1322   0.8927   0.0252
 -10.750   0.0056   0.10311   0.09912  -0.1333   0.8873   0.0253
 -10.500   0.0062   0.10060   0.09661  -0.1352   0.8818   0.0254
 -10.250   0.0098   0.09790   0.09387  -0.1367   0.8778   0.0254
 -10.000   0.0165   0.09340   0.08940  -0.1365   0.8738   0.0259
  -9.750   0.0286   0.09015   0.08614  -0.1355   0.8702   0.0265
  -9.500   0.0362   0.08743   0.08340  -0.1357   0.8665   0.0272
  -9.250   0.0417   0.08480   0.08073  -0.1364   0.8631   0.0278
  -9.000   0.0452   0.08226   0.07822  -0.1372   0.8580   0.0287
  -8.750   0.0483   0.07968   0.07564  -0.1381   0.8535   0.0292
  -8.500   0.0511   0.07698   0.07293  -0.1393   0.8500   0.0298
  -8.250   0.0513   0.07423   0.07021  -0.1408   0.8455   0.0309
  -8.000   0.0506   0.07150   0.06751  -0.1425   0.8407   0.0312
  -7.750   0.0467   0.06850   0.06450  -0.1446   0.8364   0.0316
  -7.500   0.0365   0.06629   0.06227  -0.1451   0.8317   0.0323
  -7.250   0.0311   0.06422   0.06014  -0.1456   0.8261   0.0330
  -7.000   0.0303   0.06260   0.05832  -0.1459   0.8222   0.0338
  -6.750   0.0339   0.06091   0.05640  -0.1452   0.8194   0.0340
  -6.500   0.0344   0.05963   0.05500  -0.1434   0.8140   0.0342
  -6.250   0.0346   0.05415   0.04958  -0.1428   0.8106   0.0351
  -6.000   0.0442   0.05133   0.04676  -0.1422   0.8080   0.0362
  -5.750   0.0563   0.04899   0.04432  -0.1416   0.8059   0.0375
  -5.500   0.0595   0.04768   0.04296  -0.1393   0.8008   0.0389
  -5.250   0.0691   0.04596   0.04109  -0.1377   0.7970   0.0412
  -5.000   0.0902   0.04679   0.04133  -0.1355   0.7942   0.0455
  -4.750   0.0988   0.04167   0.03609  -0.1348   0.7922   0.0470
  -4.500   0.1034   0.04003   0.03455  -0.1326   0.7875   0.0492
  -4.250   0.1125   0.03915   0.03360  -0.1303   0.7830   0.0545
  -4.000   0.1297   0.03747   0.03150  -0.1286   0.7805   0.0616
  -3.750   0.1507   0.03538   0.02937  -0.1285   0.7789   0.0660
  -3.500   0.1747   0.03393   0.02749  -0.1278   0.7774   0.0765
  -2.500   0.2537   0.02792   0.02019  -0.1186   0.7644   0.0338
  -2.250   0.2255   0.02973   0.02205  -0.1100   0.7548   0.0337
  -2.000   0.2513   0.02804   0.02019  -0.1094   0.7528   0.0323
  -1.750   0.2825   0.02673   0.01869  -0.1096   0.7515   0.0322
  -1.500   0.3138   0.02540   0.01726  -0.1098   0.7506   0.0359
  -1.250   0.3451   0.02460   0.01646  -0.1103   0.7497   0.0468
  -1.000   0.3744   0.02365   0.01558  -0.1107   0.7489   0.0692
   0.500   0.6080   0.02433   0.01834  -0.1212   0.7366   0.9910
   0.750   0.6425   0.02425   0.01817  -0.1231   0.7357   0.9931
   1.000   0.6759   0.02416   0.01800  -0.1246   0.7349   0.9946
   1.250   0.7117   0.02404   0.01779  -0.1267   0.7342   0.9958
   2.750   0.4750   0.03666   0.03057  -0.0703   0.6826   1.0000
   3.000   0.5038   0.03690   0.03074  -0.0710   0.6807   1.0000
   3.250   0.5363   0.03697   0.03074  -0.0720   0.6793   1.0000
   3.500   0.5346   0.03876   0.03252  -0.0694   0.6722   1.0000
   3.750   0.5541   0.03944   0.03317  -0.0691   0.6682   1.0000
   4.000   0.5847   0.03957   0.03327  -0.0699   0.6663   1.0000
   4.250   0.6185   0.03954   0.03320  -0.0709   0.6649   1.0000
   4.500   0.6547   0.03936   0.03301  -0.0722   0.6640   1.0000
   4.750   0.6911   0.03920   0.03285  -0.0736   0.6632   1.0000
   5.000   0.6746   0.04163   0.03529  -0.0694   0.6515   1.0000
   5.250   0.7099   0.04143   0.03509  -0.0706   0.6504   1.0000
   5.500   0.7038   0.04339   0.03707  -0.0676   0.6399   1.0000
   5.750   0.7367   0.04324   0.03694  -0.0684   0.6380   1.0000
   6.000   0.7726   0.04288   0.03662  -0.0695   0.6367   1.0000
   6.250   0.8025   0.04282   0.03659  -0.0700   0.6339   1.0000
   6.500   0.8055   0.04419   0.03800  -0.0679   0.6243   1.0000
   6.750   0.8441   0.04345   0.03730  -0.0691   0.6230   1.0000
   7.000   0.8473   0.04485   0.03874  -0.0670   0.6130   1.0000
   7.250   0.8848   0.04400   0.03797  -0.0679   0.6108   1.0000
   7.500   0.9274   0.04263   0.03667  -0.0692   0.6094   1.0000
   7.750   0.9762   0.04059   0.03474  -0.0709   0.6087   1.0000
   8.000   1.0270   0.03827   0.03251  -0.0728   0.6082   1.0000
   8.250   1.0767   0.03590   0.03028  -0.0745   0.6079   1.0000
   8.500   1.1275   0.03340   0.02792  -0.0764   0.6080   1.0000
   8.750   1.1842   0.03056   0.02522  -0.0790   0.6080   1.0000
   9.000   1.2588   0.02662   0.02147  -0.0837   0.6078   1.0000
   9.250   1.2476   0.02821   0.02313  -0.0790   0.5955   1.0000
   9.500   1.2521   0.02894   0.02397  -0.0763   0.5845   1.0000
   9.750   1.3332   0.02439   0.01958  -0.0814   0.5788   1.0000
  10.000   1.3294   0.02550   0.02078  -0.0775   0.5641   1.0000
  10.250   1.3151   0.02755   0.02292  -0.0729   0.5460   1.0000
  10.500   1.3322   0.02744   0.02285  -0.0714   0.5235   1.0000
  10.750   1.3357   0.02841   0.02380  -0.0687   0.4910   1.0000
  11.000   1.3517   0.02823   0.02328  -0.0666   0.4298   1.0000
  11.250   1.3404   0.03032   0.02493  -0.0624   0.3728   1.0000
  11.500   1.3244   0.03313   0.02744  -0.0584   0.3274   1.0000
  11.750   1.3106   0.03602   0.03010  -0.0550   0.2884   1.0000
  12.250   1.2900   0.04186   0.03553  -0.0497   0.2219   1.0000
  12.500   1.2840   0.04462   0.03815  -0.0477   0.1944   1.0000
  12.750   1.2800   0.04732   0.04071  -0.0459   0.1700   1.0000
  13.000   1.2789   0.04985   0.04316  -0.0445   0.1481   1.0000
  13.250   1.2771   0.05250   0.04570  -0.0432   0.1295   1.0000
  13.500   1.2779   0.05497   0.04813  -0.0421   0.1110   1.0000
  13.750   1.2783   0.05756   0.05067  -0.0411   0.0950   1.0000
  14.000   1.2782   0.06025   0.05331  -0.0401   0.0810   1.0000
  14.250   1.2784   0.06298   0.05600  -0.0393   0.0690   1.0000
  14.500   1.2790   0.06572   0.05878  -0.0385   0.0589   1.0000
  14.750   1.2791   0.06858   0.06166  -0.0377   0.0509   1.0000
  15.000   1.2772   0.07170   0.06477  -0.0370   0.0438   1.0000
  15.250   1.2792   0.07447   0.06762  -0.0366   0.0377   1.0000
  15.500   1.2793   0.07748   0.07070  -0.0360   0.0324   1.0000
  15.750   1.2777   0.08073   0.07395  -0.0358   0.0280   1.0000
  16.000   1.2799   0.08371   0.07707  -0.0357   0.0235   1.0000
  16.250   1.2759   0.08735   0.08072  -0.0356   0.0198   1.0000
  16.500   1.2763   0.09072   0.08422  -0.0360   0.0163   1.0000
  16.750   1.2722   0.09444   0.08800  -0.0357   0.0142   1.0000
  17.000   1.2735   0.09775   0.09148  -0.0362   0.0125   1.0000
  17.250   1.2674   0.10190   0.09560  -0.0368   0.0105   1.0000
  17.500   1.2698   0.10502   0.09893  -0.0372   0.0100   1.0000
  17.750   1.2690   0.10874   0.10286  -0.0380   0.0089   1.0000
  18.000   1.2653   0.11291   0.10710  -0.0393   0.0079   1.0000
  18.250   1.2645   0.11631   0.11057  -0.0398   0.0075   1.0000
  18.500   1.2608   0.12061   0.11513  -0.0407   0.0070   1.0000
  18.750   1.2592   0.12457   0.11928  -0.0418   0.0069   1.0000
  19.000   1.2547   0.12911   0.12405  -0.0434   0.0067   1.0000
  19.250   1.2484   0.13414   0.12931  -0.0453   0.0066   1.0000
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