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NREL's S808 Airfoil (s808-nr) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NREL's S808 Airfoil (s808-nr)
Reynolds number: 100,000
Max Cl/Cd: 36.55 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s808-nr-100000.txt
Download as CSV file: xf-s808-nr-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S808 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2423   0.10409   0.09743  -0.0165   1.0000   0.3642
  -8.250  -0.2277   0.10250   0.09587  -0.0154   1.0000   0.3680
  -8.000  -0.3004   0.10469   0.09817  -0.0123   1.0000   0.3790
  -7.750  -0.2678   0.10098   0.09446  -0.0118   1.0000   0.3800
  -7.500  -0.2426   0.09848   0.09199  -0.0109   1.0000   0.3817
  -7.250  -0.2259   0.09691   0.09047  -0.0094   1.0000   0.3845
  -7.000  -0.2207   0.09597   0.08959  -0.0073   1.0000   0.3887
  -6.750  -0.3114   0.09868   0.09247  -0.0009   1.0000   0.3983
  -6.500  -0.2912   0.09633   0.09017   0.0007   1.0000   0.3993
  -6.250  -0.2667   0.09436   0.08824   0.0007   0.9984   0.4008
  -6.000  -0.2138   0.09145   0.08531  -0.0049   0.9923   0.4046
  -5.750  -0.2270   0.09044   0.08424  -0.0124   0.9788   0.4178
  -5.500  -0.1707   0.08643   0.08022  -0.0166   0.9716   0.4192
  -5.250  -0.1148   0.08314   0.07691  -0.0219   0.9658   0.4217
  -5.000  -0.0713   0.08064   0.07441  -0.0261   0.9554   0.4264
  -4.750  -0.0834   0.07925   0.07299  -0.0306   0.9380   0.4381
  -4.500  -0.0216   0.07547   0.06920  -0.0359   0.9336   0.4400
  -4.250   0.0218   0.07281   0.06655  -0.0391   0.9211   0.4430
  -4.000   0.0600   0.07041   0.06414  -0.0428   0.9096   0.4483
  -3.750  -0.0656   0.05754   0.05093  -0.0533   0.8823   0.3976
  -3.500  -0.0006   0.05997   0.05346  -0.0523   0.8719   0.4179
  -3.250   0.0591   0.05721   0.05067  -0.0577   0.8657   0.4190
  -3.000   0.1012   0.05445   0.04786  -0.0615   0.8520   0.4131
  -2.750   0.1202   0.05138   0.04471  -0.0645   0.8365   0.4112
  -2.500   0.1291   0.04780   0.04102  -0.0679   0.8203   0.4092
  -2.250   0.1280   0.04324   0.03628  -0.0724   0.8042   0.4092
  -2.000   0.1014   0.03426   0.02680  -0.0823   0.7869   0.4189
  -1.750   0.1300   0.03440   0.02698  -0.0810   0.7705   0.4208
  -1.500   0.1581   0.03420   0.02676  -0.0805   0.7551   0.4235
  -1.250   0.1859   0.03309   0.02552  -0.0818   0.7410   0.4277
  -1.000   0.2092   0.02982   0.02182  -0.0872   0.7268   0.4376
  -0.750   0.2323   0.02994   0.02202  -0.0854   0.7116   0.4400
  -0.500   0.2590   0.03003   0.02211  -0.0844   0.6979   0.4430
  -0.250   0.2880   0.02965   0.02163  -0.0846   0.6851   0.4473
   0.000   0.3119   0.02857   0.02041  -0.0860   0.6707   0.4536
   0.250   0.3406   0.02777   0.01944  -0.0873   0.6582   0.4591
   0.500   0.3662   0.02787   0.01956  -0.0862   0.6457   0.4625
   0.750   0.3893   0.02789   0.01961  -0.0852   0.6327   0.4669
   1.000   0.4225   0.02732   0.01881  -0.0870   0.6218   0.4741
   1.250   0.4466   0.02689   0.01835  -0.0871   0.6085   0.4793
   1.500   0.4724   0.02695   0.01842  -0.0863   0.5975   0.4830
   1.750   0.4980   0.02695   0.01842  -0.0858   0.5859   0.4879
   2.000   0.5263   0.02672   0.01808  -0.0866   0.5743   0.4955
   2.250   0.5550   0.02656   0.01785  -0.0867   0.5639   0.5008
   2.500   0.5770   0.02673   0.01812  -0.0855   0.5525   0.5053
   2.750   0.6076   0.02665   0.01793  -0.0859   0.5428   0.5115
   3.000   0.6339   0.02656   0.01781  -0.0864   0.5312   0.5191
   3.250   0.6619   0.02664   0.01786  -0.0858   0.5223   0.5240
   3.500   0.6828   0.02686   0.01820  -0.0847   0.5111   0.5301
   3.750   0.7182   0.02675   0.01784  -0.0864   0.5021   0.5392
   4.000   0.7367   0.02698   0.01829  -0.0846   0.4915   0.5436
   4.250   0.7663   0.02706   0.01829  -0.0846   0.4829   0.5505
   4.500   0.7913   0.02728   0.01853  -0.0847   0.4724   0.5597
   4.750   0.8176   0.02738   0.01865  -0.0839   0.4641   0.5656
   5.000   0.8396   0.02772   0.01910  -0.0830   0.4545   0.5733
   5.250   0.8691   0.02780   0.01910  -0.0834   0.4457   0.5821
   5.500   0.8913   0.02815   0.01956  -0.0822   0.4371   0.5888
   5.750   0.9178   0.02837   0.01977  -0.0822   0.4280   0.5990
   6.000   0.9441   0.02865   0.02005  -0.0816   0.4204   0.6068
   6.250   0.9640   0.02904   0.02059  -0.0804   0.4111   0.6163
   6.500   0.9964   0.02918   0.02058  -0.0809   0.4039   0.6258
   6.750   1.0114   0.02974   0.02139  -0.0790   0.3949   0.6348
   7.000   1.0392   0.02992   0.02153  -0.0789   0.3873   0.6453
   7.250   1.0601   0.03046   0.02216  -0.0778   0.3795   0.6562
   7.500   1.0802   0.03082   0.02264  -0.0765   0.3714   0.6665
   7.750   1.1139   0.03113   0.02277  -0.0773   0.3645   0.6803
   8.000   1.1224   0.03178   0.02376  -0.0743   0.3565   0.6893
   8.250   1.1506   0.03198   0.02390  -0.0742   0.3493   0.7031
   8.500   1.1686   0.03265   0.02470  -0.0727   0.3423   0.7160
   8.750   1.1836   0.03317   0.02538  -0.0707   0.3348   0.7285
   9.000   1.2177   0.03332   0.02535  -0.0713   0.3284   0.7447
   9.250   1.2230   0.03430   0.02666  -0.0683   0.3212   0.7594
   9.500   1.2414   0.03466   0.02708  -0.0667   0.3145   0.7758
   9.750   1.2690   0.03501   0.02734  -0.0663   0.3084   0.7946
  10.000   1.2682   0.03598   0.02864  -0.0624   0.3019   0.8121
  10.250   1.2856   0.03624   0.02894  -0.0606   0.2958   0.8348
  10.500   1.3066   0.03649   0.02914  -0.0589   0.2904   0.8620
  10.750   1.2931   0.03738   0.03042  -0.0530   0.2852   0.8962
  11.000   1.3055   0.03772   0.03089  -0.0512   0.2793   1.0000
  11.250   1.3513   0.03846   0.03140  -0.0550   0.2722   1.0000
  11.500   1.3480   0.04020   0.03338  -0.0525   0.2662   1.0000
  11.750   1.3769   0.04077   0.03383  -0.0532   0.2599   1.0000
  12.000   1.3987   0.04189   0.03489  -0.0532   0.2541   1.0000
  12.250   1.3822   0.04395   0.03719  -0.0490   0.2495   1.0000
  12.500   1.3940   0.04500   0.03824  -0.0477   0.2442   1.0000
  12.750   0.7651   0.12661   0.12166  -0.0664   0.2300   1.0000
  13.000   0.8075   0.12498   0.11994  -0.0660   0.2256   1.0000
  13.250   0.8834   0.11654   0.11139  -0.0614   0.2235   1.0000
  13.500   1.4371   0.05025   0.04350  -0.0431   0.2244   1.0000
  13.750   1.4225   0.05322   0.04664  -0.0409   0.2208   1.0000
  14.000   1.3602   0.05963   0.05346  -0.0381   0.2186   1.0000
  14.750   1.3762   0.06610   0.05999  -0.0371   0.2057   1.0000
  15.000   0.7848   0.18076   0.17588  -0.0936   0.2390   1.0000
  15.250   0.7471   0.18285   0.17796  -0.0996   0.2307   1.0000
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