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NREL's S831 Airfoil (s831-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S831 Airfoil (s831-nr)
Reynolds number: 100,000
Max Cl/Cd: 21.23 at α=12.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s831-nr-100000-n5.txt
Download as CSV file: xf-s831-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S831 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000   0.0309   0.11326   0.10759  -0.1502   0.8874   0.0408
 -11.750   0.0370   0.10999   0.10430  -0.1523   0.8835   0.0418
 -11.500   0.0436   0.10658   0.10088  -0.1551   0.8804   0.0430
 -11.250   0.0438   0.10363   0.09794  -0.1576   0.8757   0.0441
 -11.000   0.0399   0.10062   0.09494  -0.1604   0.8703   0.0448
 -10.750   0.0410   0.09704   0.09136  -0.1639   0.8665   0.0451
 -10.500   0.0403   0.09350   0.08781  -0.1664   0.8619   0.0452
 -10.250   0.0353   0.09003   0.08435  -0.1684   0.8563   0.0452
 -10.000   0.0316   0.08624   0.08051  -0.1713   0.8523   0.0453
  -9.750   0.0224   0.08313   0.07737  -0.1724   0.8474   0.0453
  -9.250   0.0917   0.06186   0.05634  -0.1622   0.8288   0.0255
  -8.750   0.0274   0.06707   0.06120  -0.1718   0.8320   0.0253
  -8.500   0.0137   0.06496   0.05908  -0.1699   0.8264   0.0248
  -8.250   0.0018   0.06247   0.05651  -0.1688   0.8225   0.0242
  -8.000  -0.0243   0.06192   0.05597  -0.1634   0.8156   0.0240
  -7.750  -0.0386   0.06017   0.05413  -0.1603   0.8109   0.0234
  -7.500  -0.0570   0.05632   0.04977  -0.1569   0.8074   0.0201
  -7.250  -0.0833   0.05666   0.05014  -0.1490   0.7994   0.0200
  -7.000  -0.0826   0.05459   0.04797  -0.1469   0.7961   0.0197
  -6.750  -0.0758   0.05200   0.04519  -0.1460   0.7939   0.0194
  -6.500  -0.1065   0.05275   0.04596  -0.1369   0.7856   0.0194
  -6.250  -0.1077   0.05109   0.04414  -0.1337   0.7821   0.0191
  -6.000  -0.0970   0.04863   0.04142  -0.1325   0.7801   0.0188
  -5.750  -0.1295   0.04964   0.04245  -0.1231   0.7713   0.0188
  -5.500  -0.1219   0.04774   0.04030  -0.1210   0.7680   0.0185
  -5.250  -0.1047   0.04529   0.03752  -0.1203   0.7663   0.0182
  -5.000  -0.0826   0.04279   0.03463  -0.1200   0.7650   0.0180
  -4.750  -0.1098   0.04420   0.03604  -0.1121   0.7564   0.0180
  -4.500  -0.0904   0.04237   0.03386  -0.1113   0.7540   0.0178
  -4.250  -0.0651   0.04041   0.03154  -0.1111   0.7525   0.0180
  -4.000  -0.0372   0.03870   0.02943  -0.1111   0.7514   0.0190
  -3.750  -0.0095   0.03735   0.02783  -0.1113   0.7504   0.0215
  -3.500  -0.0217   0.03853   0.02895  -0.1059   0.7438   0.0215
  -3.250  -0.0060   0.03825   0.02856  -0.1045   0.7410   0.0232
  -3.000   0.0174   0.03730   0.02744  -0.1036   0.7392   0.0245
  -2.750   0.0428   0.03641   0.02637  -0.1030   0.7378   0.0258
  -2.500   0.0688   0.03570   0.02568  -0.1031   0.7367   0.0308
  -2.250   0.0959   0.03500   0.02489  -0.1030   0.7357   0.0351
  -2.000   0.0860   0.03633   0.02630  -0.0984   0.7296   0.0371
  -1.750   0.1013   0.03655   0.02647  -0.0971   0.7267   0.0444
  -1.500   0.1254   0.03623   0.02608  -0.0972   0.7247   0.0562
  -1.000   0.1873   0.03376   0.02541  -0.1016   0.7225   0.5295
  -0.500   0.1970   0.03649   0.02835  -0.0936   0.7155   0.6993
  -0.250   0.2067   0.03753   0.02930  -0.0904   0.7120   0.7258
   0.000   0.2181   0.03824   0.03001  -0.0866   0.7098   0.7463
   0.250   0.2320   0.03884   0.03055  -0.0834   0.7082   0.7664
   0.500   0.2553   0.03917   0.03075  -0.0827   0.7070   0.7754
   0.750   0.2849   0.03933   0.03075  -0.0837   0.7061   0.7774
   1.000   0.2746   0.04122   0.03264  -0.0799   0.6984   0.7805
   1.250   0.2983   0.04172   0.03303  -0.0804   0.6963   0.7832
   1.500   0.3265   0.04206   0.03325  -0.0815   0.6946   0.7863
   1.750   0.3542   0.04226   0.03335  -0.0820   0.6932   0.7885
   2.000   0.3826   0.04246   0.03347  -0.0826   0.6921   0.7908
   2.500   0.3983   0.04481   0.03578  -0.0795   0.6821   0.7967
   2.750   0.4251   0.04524   0.03615  -0.0803   0.6803   0.7998
   3.000   0.4535   0.04552   0.03638  -0.0812   0.6788   0.8027
   3.250   0.4823   0.04568   0.03652  -0.0818   0.6776   0.8054
   3.500   0.4752   0.04757   0.03846  -0.0785   0.6695   0.8090
   3.750   0.4999   0.04803   0.03890  -0.0789   0.6669   0.8124
   4.000   0.5288   0.04836   0.03921  -0.0800   0.6650   0.8158
   4.250   0.5577   0.04857   0.03943  -0.0807   0.6637   0.8186
   4.750   0.5787   0.05076   0.04169  -0.0782   0.6527   0.8260
   5.000   0.6075   0.05106   0.04199  -0.0792   0.6507   0.8301
   5.250   0.6370   0.05118   0.04215  -0.0799   0.6492   0.8338
   5.750   0.6608   0.05326   0.04435  -0.0779   0.6375   0.8418
   6.000   0.6910   0.05341   0.04454  -0.0788   0.6357   0.8461
   6.250   0.7205   0.05342   0.04462  -0.0794   0.6341   0.8504
   6.500   0.7173   0.05522   0.04650  -0.0769   0.6239   0.8554
   6.750   0.7471   0.05529   0.04668  -0.0777   0.6217   0.8606
   7.000   0.7773   0.05517   0.04664  -0.0783   0.6201   0.8657
   7.250   0.7762   0.05690   0.04848  -0.0761   0.6096   0.8713
   7.500   0.8058   0.05678   0.04848  -0.0766   0.6072   0.8772
   8.000   0.8365   0.05808   0.05002  -0.0751   0.5944   0.8913
   8.250   0.8675   0.05763   0.04970  -0.0755   0.5923   0.9005
   8.500   0.8698   0.05901   0.05124  -0.0736   0.5813   0.9108
   8.750   0.9008   0.05840   0.05081  -0.0740   0.5786   0.9263
   9.250   0.9413   0.05861   0.05132  -0.0736   0.5643   1.0000
   9.750   0.9874   0.05880   0.05178  -0.0739   0.5484   1.0000
  10.750   1.0553   0.06058   0.05413  -0.0720   0.5010   1.0000
  11.000   1.0749   0.06074   0.05445  -0.0716   0.4877   1.0000
  11.500   1.1163   0.06098   0.05498  -0.0708   0.4544   1.0000
  12.000   1.1820   0.05812   0.05214  -0.0705   0.3955   1.0000
  12.250   1.2100   0.05700   0.05070  -0.0696   0.3395   1.0000
  12.500   1.2167   0.05845   0.05180  -0.0681   0.2887   1.0000
  12.750   1.2172   0.06079   0.05387  -0.0666   0.2454   1.0000
  13.000   1.2172   0.06335   0.05622  -0.0653   0.2077   1.0000
  13.250   1.2177   0.06596   0.05864  -0.0643   0.1759   1.0000
  13.500   1.2196   0.06853   0.06109  -0.0634   0.1493   1.0000
  13.750   1.2221   0.07109   0.06355  -0.0626   0.1265   1.0000
  14.000   1.2252   0.07364   0.06604  -0.0620   0.1078   1.0000
  14.500   1.2314   0.07891   0.07126  -0.0609   0.0779   1.0000
  14.750   1.2343   0.08164   0.07398  -0.0605   0.0665   1.0000
  15.000   1.2371   0.08442   0.07679  -0.0602   0.0567   1.0000
  15.250   1.2407   0.08715   0.07961  -0.0599   0.0484   1.0000
  15.500   1.2425   0.09013   0.08265  -0.0597   0.0422   1.0000
  15.750   1.2435   0.09327   0.08584  -0.0596   0.0370   1.0000
  16.000   1.2459   0.09625   0.08894  -0.0595   0.0325   1.0000
  16.250   1.2465   0.09953   0.09229  -0.0596   0.0289   1.0000
  16.500   1.2479   0.10267   0.09557  -0.0597   0.0258   1.0000
  16.750   1.2494   0.10589   0.09891  -0.0601   0.0229   1.0000
  17.000   1.2477   0.10952   0.10260  -0.0606   0.0210   1.0000
  17.250   1.2509   0.11255   0.10587  -0.0609   0.0188   1.0000
  17.500   1.2513   0.11602   0.10947  -0.0617   0.0171   1.0000
  17.750   1.2495   0.11979   0.11330  -0.0627   0.0159   1.0000
  18.000   1.2516   0.12300   0.11673  -0.0633   0.0147   1.0000
  18.250   1.2518   0.12664   0.12059  -0.0643   0.0135   1.0000
  18.500   1.2499   0.13065   0.12475  -0.0658   0.0126   1.0000
  18.750   1.2479   0.13464   0.12884  -0.0675   0.0120   1.0000
  19.000   1.2448   0.13891   0.13323  -0.0693   0.0114   1.0000
  19.250   1.2412   0.14353   0.13815  -0.0713   0.0108   1.0000
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