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NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NREL's S815 Airfoil (s815-nr)
Reynolds number: 100,000
Max Cl/Cd: 35.97 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s815-nr-100000-n5.txt
Download as CSV file: xf-s815-nr-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S815 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1107   0.11892   0.11102  -0.0421   0.9791   0.2885
  -8.250  -0.0947   0.11617   0.10825  -0.0448   0.9729   0.2899
  -8.000  -0.0900   0.11309   0.10512  -0.0483   0.9672   0.2942
  -7.750  -0.0565   0.11128   0.10334  -0.0506   0.9614   0.2954
  -7.500  -0.0287   0.10947   0.10156  -0.0526   0.9534   0.2968
  -7.250  -0.0077   0.10740   0.09951  -0.0542   0.9445   0.2979
  -7.000   0.0120   0.10512   0.09723  -0.0562   0.9352   0.2986
  -6.750   0.0243   0.10321   0.09535  -0.0564   0.9202   0.2994
  -6.500   0.0364   0.10129   0.09344  -0.0567   0.9040   0.3001
  -6.000   0.0685   0.09715   0.08930  -0.0590   0.8743   0.3025
  -5.750   0.0875   0.09472   0.08684  -0.0616   0.8614   0.3049
  -5.500   0.1094   0.09180   0.08385  -0.0654   0.8496   0.3062
  -5.250   0.1319   0.08877   0.08073  -0.0695   0.8350   0.3070
  -5.000   0.1512   0.08534   0.07718  -0.0748   0.8201   0.3081
  -4.750   0.1902   0.08226   0.07398  -0.0816   0.8034   0.3096
  -4.500   0.2473   0.08009   0.07169  -0.0882   0.7829   0.3108
  -4.250   0.2904   0.07817   0.06963  -0.0932   0.7611   0.3120
  -4.000   0.3231   0.07654   0.06786  -0.0966   0.7403   0.3132
  -3.750   0.3463   0.07491   0.06611  -0.0987   0.7216   0.3138
  -3.500   0.3649   0.07333   0.06443  -0.1002   0.7051   0.3141
  -3.250   0.3826   0.07184   0.06285  -0.1014   0.6906   0.3145
  -3.000   0.3986   0.07045   0.06137  -0.1022   0.6772   0.3150
  -2.750   0.4116   0.06916   0.06003  -0.1023   0.6648   0.3155
  -2.500   0.4253   0.06785   0.05863  -0.1027   0.6541   0.3161
  -2.250   0.4366   0.06672   0.05749  -0.1024   0.6434   0.3173
  -2.000   0.4477   0.06553   0.05623  -0.1023   0.6347   0.3187
  -1.750   0.4536   0.06427   0.05497  -0.1016   0.6258   0.3200
  -1.500   0.4609   0.06285   0.05350  -0.1013   0.6185   0.3205
  -1.250   0.4661   0.06136   0.05199  -0.1007   0.6119   0.3212
   1.250   0.3738   0.03690   0.02726  -0.0913   0.5636   0.3414
   1.500   0.3981   0.03689   0.02728  -0.0908   0.5592   0.3421
   1.750   0.4225   0.03677   0.02718  -0.0908   0.5556   0.3428
   2.000   0.4400   0.03661   0.02712  -0.0898   0.5511   0.3438
   2.250   0.4592   0.03622   0.02680  -0.0896   0.5470   0.3452
   2.500   0.4804   0.03547   0.02608  -0.0904   0.5434   0.3471
   2.750   0.5047   0.03380   0.02431  -0.0936   0.5401   0.3502
   3.250   0.5709   0.02956   0.01964  -0.1050   0.5326   0.3585
   3.500   0.5936   0.02962   0.01983  -0.1044   0.5286   0.3595
   3.750   0.6190   0.02969   0.02000  -0.1043   0.5252   0.3607
   4.000   0.6467   0.02973   0.02011  -0.1046   0.5222   0.3620
   4.250   0.6767   0.02975   0.02017  -0.1054   0.5195   0.3636
   4.500   0.7073   0.02976   0.02021  -0.1064   0.5167   0.3655
   4.750   0.7283   0.02978   0.02036  -0.1060   0.5127   0.3678
   5.000   0.7548   0.02969   0.02033  -0.1068   0.5090   0.3708
   5.250   0.7882   0.02944   0.02001  -0.1091   0.5056   0.3746
   5.500   0.8170   0.02950   0.02015  -0.1096   0.5023   0.3766
   5.750   0.8470   0.02966   0.02039  -0.1100   0.4993   0.3782
   6.000   0.8692   0.02993   0.02081  -0.1093   0.4956   0.3799
   6.250   0.8859   0.03023   0.02129  -0.1078   0.4910   0.3817
   6.500   0.9089   0.03043   0.02160  -0.1074   0.4867   0.3840
   6.750   0.9389   0.03048   0.02169  -0.1081   0.4828   0.3868
   7.000   0.9775   0.03039   0.02153  -0.1103   0.4791   0.3905
   7.250   0.9932   0.03066   0.02192  -0.1090   0.4737   0.3934
   7.500   1.0080   0.03096   0.02242  -0.1070   0.4681   0.3951
   7.750   1.0346   0.03102   0.02257  -0.1067   0.4629   0.3974
   8.000   1.0607   0.03111   0.02274  -0.1063   0.4574   0.4002
   8.250   1.0657   0.03154   0.02338  -0.1030   0.4506   0.4028
   8.500   1.0914   0.03146   0.02331  -0.1027   0.4439   0.4067
   8.750   1.1127   0.03148   0.02333  -0.1019   0.4372   0.4109
   9.000   1.1149   0.03189   0.02394  -0.0981   0.4298   0.4130
   9.250   1.1411   0.03172   0.02382  -0.0975   0.4225   0.4158
   9.500   1.1407   0.03244   0.02476  -0.0937   0.4148   0.4180
   9.750   1.1542   0.03271   0.02512  -0.0917   0.4065   0.4211
  10.000   1.1642   0.03317   0.02567  -0.0895   0.3984   0.4243
  10.250   1.1693   0.03386   0.02646  -0.0869   0.3890   0.4277
  10.500   1.1765   0.03453   0.02722  -0.0847   0.3796   0.4308
  10.750   1.1768   0.03552   0.02839  -0.0818   0.3692   0.4329
  11.000   1.1719   0.03702   0.03008  -0.0789   0.3581   0.4350
  11.250   1.1718   0.03834   0.03151  -0.0767   0.3460   0.4379
  11.500   1.1652   0.04032   0.03360  -0.0745   0.3322   0.4406
  11.750   1.1555   0.04287   0.03624  -0.0727   0.3169   0.4433
  12.000   1.1505   0.04530   0.03866  -0.0716   0.2994   0.4467
  12.250   1.1484   0.04761   0.04089  -0.0707   0.2805   0.4498
  12.500   1.1418   0.05044   0.04369  -0.0698   0.2618   0.4519
  12.750   1.1328   0.05377   0.04698  -0.0693   0.2441   0.4541
  13.000   1.1235   0.05738   0.05055  -0.0691   0.2273   0.4564
  13.250   1.1148   0.06112   0.05425  -0.0691   0.2115   0.4590
  13.500   1.1072   0.06494   0.05803  -0.0695   0.1965   0.4617
  13.750   1.1011   0.06878   0.06184  -0.0701   0.1824   0.4647
  14.000   1.0969   0.07257   0.06557  -0.0708   0.1693   0.4681
  14.250   1.0931   0.07625   0.06928  -0.0714   0.1576   0.4704
  14.500   1.0898   0.07993   0.07296  -0.0721   0.1469   0.4731
  14.750   1.0883   0.08354   0.07659  -0.0729   0.1366   0.4762
  15.000   1.0884   0.08706   0.08013  -0.0738   0.1273   0.4798
  15.250   1.0885   0.09063   0.08365  -0.0749   0.1191   0.4838
  15.500   1.0904   0.09411   0.08715  -0.0760   0.1110   0.4879
  15.750   1.0921   0.09746   0.09055  -0.0770   0.1040   0.4909
  16.000   1.0936   0.10092   0.09405  -0.0781   0.0977   0.4945
  16.250   1.0971   0.10419   0.09737  -0.0792   0.0917   0.4988
  16.500   1.0996   0.10765   0.10083  -0.0805   0.0864   0.5035
  16.750   1.1040   0.11088   0.10410  -0.0818   0.0814   0.5080
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