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NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S818 Airfoil (s818-nr)
Reynolds number: 200,000
Max Cl/Cd: 58.83 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s818-nr-200000-n5.txt
Download as CSV file: xf-s818-nr-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S818 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5607   0.10009   0.09530  -0.0378   1.0000   0.2688
 -12.750  -0.5397   0.10087   0.09606  -0.0368   1.0000   0.2729
 -12.500  -0.5466   0.09842   0.09356  -0.0367   1.0000   0.2817
 -12.250  -0.5189   0.09996   0.09507  -0.0353   1.0000   0.2839
 -11.750  -0.5140   0.09750   0.09255  -0.0341   1.0000   0.2951
 -11.500  -0.4754   0.09852   0.09353  -0.0347   0.9988   0.2965
 -11.250  -0.4332   0.09871   0.09365  -0.0373   0.9963   0.2989
 -11.000  -0.4329   0.09530   0.09015  -0.0412   0.9935   0.3075
 -10.750  -0.3907   0.09551   0.09031  -0.0432   0.9911   0.3098
 -10.500  -0.3518   0.09525   0.09000  -0.0452   0.9880   0.3113
 -10.250  -0.3207   0.09403   0.08871  -0.0478   0.9850   0.3128
  -9.750  -0.3202   0.08745   0.08198  -0.0547   0.9784   0.3228
  -9.500  -0.2947   0.08580   0.08029  -0.0564   0.9743   0.3231
  -9.250  -0.2660   0.08414   0.07857  -0.0589   0.9711   0.3234
  -9.000  -0.2366   0.08241   0.07679  -0.0618   0.9686   0.3238
  -8.750  -0.2172   0.08093   0.07528  -0.0625   0.9632   0.3241
  -8.500  -0.1938   0.07941   0.07373  -0.0639   0.9582   0.3245
  -8.000  -0.1485   0.07694   0.07122  -0.0657   0.9462   0.3258
  -7.750  -0.1289   0.07505   0.06929  -0.0675   0.9405   0.3261
  -7.500  -0.1233   0.07370   0.06794  -0.0659   0.9273   0.3264
  -7.250  -0.1168   0.07238   0.06661  -0.0644   0.9115   0.3269
  -4.750  -0.1363   0.02307   0.01527  -0.1087   0.7084   0.3530
  -4.500  -0.1106   0.02271   0.01478  -0.1092   0.6894   0.3535
  -4.250  -0.0859   0.02239   0.01434  -0.1093   0.6717   0.3540
  -4.000  -0.0617   0.02211   0.01395  -0.1094   0.6554   0.3545
  -3.750  -0.0377   0.02183   0.01356  -0.1094   0.6402   0.3551
  -3.250   0.0105   0.02121   0.01273  -0.1096   0.6120   0.3562
  -3.000   0.0352   0.02091   0.01234  -0.1097   0.5992   0.3568
  -2.750   0.0601   0.02063   0.01194  -0.1100   0.5874   0.3574
  -2.500   0.0855   0.02037   0.01158  -0.1102   0.5759   0.3580
  -2.250   0.1116   0.02010   0.01123  -0.1106   0.5655   0.3587
  -2.000   0.1379   0.01987   0.01089  -0.1110   0.5564   0.3595
  -1.750   0.1649   0.01962   0.01058  -0.1115   0.5473   0.3603
  -1.250   0.2200   0.01919   0.00998  -0.1126   0.5315   0.3620
  -1.000   0.2478   0.01901   0.00971  -0.1132   0.5243   0.3630
  -0.750   0.2764   0.01883   0.00946  -0.1139   0.5178   0.3639
  -0.500   0.3051   0.01867   0.00922  -0.1146   0.5112   0.3649
  -0.250   0.3339   0.01855   0.00899  -0.1154   0.5056   0.3659
   0.000   0.3631   0.01841   0.00880  -0.1161   0.4997   0.3669
   0.250   0.3923   0.01831   0.00863  -0.1169   0.4940   0.3677
   0.500   0.4206   0.01827   0.00853  -0.1173   0.4890   0.3686
   0.750   0.4486   0.01823   0.00852  -0.1176   0.4844   0.3694
   1.000   0.4767   0.01822   0.00853  -0.1180   0.4799   0.3702
   1.250   0.5048   0.01824   0.00857  -0.1183   0.4758   0.3710
   1.500   0.5332   0.01829   0.00860  -0.1186   0.4723   0.3719
   1.750   0.5620   0.01834   0.00866  -0.1191   0.4689   0.3729
   2.000   0.5907   0.01837   0.00874  -0.1195   0.4653   0.3740
   2.250   0.6194   0.01841   0.00880  -0.1199   0.4619   0.3751
   2.500   0.6483   0.01847   0.00887  -0.1204   0.4588   0.3764
   2.750   0.6777   0.01855   0.00894  -0.1210   0.4560   0.3778
   3.000   0.7076   0.01866   0.00901  -0.1217   0.4533   0.3794
   3.250   0.7364   0.01871   0.00911  -0.1221   0.4502   0.3810
   3.500   0.7654   0.01878   0.00919  -0.1226   0.4471   0.3826
   3.750   0.7947   0.01887   0.00929  -0.1232   0.4444   0.3840
   4.000   0.8232   0.01895   0.00944  -0.1236   0.4420   0.3852
   4.250   0.8521   0.01908   0.00962  -0.1240   0.4398   0.3864
   4.500   0.8816   0.01924   0.00982  -0.1245   0.4378   0.3877
   4.750   0.9111   0.01942   0.01005  -0.1250   0.4359   0.3892
   5.000   0.9390   0.01956   0.01030  -0.1252   0.4337   0.3907
   5.250   0.9670   0.01972   0.01056  -0.1255   0.4316   0.3923
   5.500   0.9949   0.01988   0.01079  -0.1257   0.4292   0.3940
   5.750   1.0228   0.02005   0.01102  -0.1260   0.4268   0.3959
   6.000   1.0512   0.02023   0.01126  -0.1263   0.4247   0.3977
   6.250   1.0804   0.02044   0.01149  -0.1268   0.4229   0.3996
   6.500   1.1101   0.02066   0.01177  -0.1274   0.4212   0.4013
   6.750   1.1404   0.02092   0.01211  -0.1281   0.4196   0.4030
   7.000   1.1652   0.02114   0.01250  -0.1277   0.4174   0.4048
   7.250   1.1900   0.02137   0.01288  -0.1274   0.4148   0.4069
   7.500   1.2146   0.02160   0.01323  -0.1270   0.4119   0.4092
   7.750   1.2390   0.02180   0.01351  -0.1265   0.4085   0.4118
   8.000   1.2641   0.02193   0.01359  -0.1262   0.4030   0.4143
   8.250   1.2724   0.02198   0.01379  -0.1227   0.3953   0.4163
   8.500   1.2869   0.02203   0.01387  -0.1205   0.3879   0.4182
   8.750   1.3035   0.02226   0.01425  -0.1187   0.3822   0.4202
   9.000   1.3206   0.02251   0.01466  -0.1170   0.3768   0.4223
   9.250   1.3390   0.02276   0.01496  -0.1156   0.3715   0.4246
   9.500   1.3554   0.02308   0.01539  -0.1139   0.3656   0.4271
   9.750   1.3705   0.02341   0.01585  -0.1120   0.3586   0.4297
  10.000   1.3857   0.02376   0.01623  -0.1102   0.3521   0.4322
  10.250   1.3996   0.02418   0.01683  -0.1083   0.3438   0.4346
  10.500   1.4120   0.02464   0.01739  -0.1062   0.3355   0.4371
  10.750   1.4239   0.02518   0.01808  -0.1042   0.3244   0.4398
  11.000   1.4337   0.02583   0.01883  -0.1019   0.3105   0.4428
  11.250   1.4387   0.02671   0.01973  -0.0992   0.2910   0.4458
  11.500   1.4356   0.02807   0.02099  -0.0958   0.2632   0.4484
  11.750   1.4236   0.03015   0.02293  -0.0919   0.2362   0.4504
  12.000   1.4098   0.03272   0.02543  -0.0885   0.2136   0.4521
  12.250   1.3965   0.03560   0.02828  -0.0859   0.1931   0.4538
  12.500   1.3831   0.03883   0.03151  -0.0838   0.1754   0.4557
  12.750   1.3702   0.04236   0.03504  -0.0824   0.1604   0.4576
  13.000   1.3579   0.04614   0.03884  -0.0814   0.1475   0.4596
  13.250   1.3451   0.05024   0.04297  -0.0810   0.1360   0.4617
  13.500   1.3340   0.05439   0.04715  -0.0809   0.1257   0.4639
  13.750   1.3248   0.05854   0.05134  -0.0810   0.1169   0.4662
  14.000   1.3139   0.06301   0.05587  -0.0814   0.1092   0.4681
  14.250   1.3074   0.06711   0.06005  -0.0820   0.1017   0.4703
  14.500   1.2988   0.07158   0.06457  -0.0827   0.0955   0.4726
  14.750   1.2947   0.07557   0.06864  -0.0835   0.0892   0.4756
  15.250   1.2865   0.08375   0.07694  -0.0853   0.0789   0.4820
  15.500   1.2829   0.08789   0.08113  -0.0863   0.0741   0.4851
  15.750   1.2812   0.09183   0.08516  -0.0874   0.0700   0.4883
  16.000   1.2814   0.09553   0.08893  -0.0885   0.0658   0.4922
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