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NREL's S815 Airfoil (s815-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S815 Airfoil (s815-nr)
Reynolds number: 500,000
Max Cl/Cd: 79.52 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s815-nr-500000.txt
Download as CSV file: xf-s815-nr-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.0076   0.09940   0.09570  -0.0705   0.9691   0.2691
  -8.000   0.0224   0.09753   0.09383  -0.0739   0.9672   0.2707
  -6.250  -0.4329   0.02170   0.01674  -0.1015   0.8640   0.3028
  -6.000  -0.3733   0.02043   0.01533  -0.1102   0.8511   0.3037
  -5.750  -0.3169   0.01947   0.01420  -0.1178   0.8307   0.3045
  -5.500  -0.2828   0.01878   0.01332  -0.1208   0.8028   0.3052
  -5.250  -0.2575   0.01828   0.01262  -0.1218   0.7759   0.3058
  -5.000  -0.2364   0.01787   0.01203  -0.1218   0.7512   0.3063
  -4.750  -0.2157   0.01752   0.01153  -0.1215   0.7284   0.3068
  -4.500  -0.1944   0.01724   0.01110  -0.1211   0.7076   0.3073
  -4.250  -0.1722   0.01702   0.01075  -0.1208   0.6888   0.3078
  -4.000  -0.1491   0.01685   0.01046  -0.1205   0.6718   0.3083
  -3.500  -0.1011   0.01645   0.00985  -0.1203   0.6413   0.3090
  -3.250  -0.0777   0.01575   0.00904  -0.1205   0.6284   0.3101
  -3.000  -0.0532   0.01543   0.00863  -0.1204   0.6159   0.3110
  -2.750  -0.0273   0.01519   0.00836  -0.1205   0.6044   0.3118
  -2.500  -0.0013   0.01505   0.00816  -0.1205   0.5939   0.3125
  -2.250   0.0254   0.01491   0.00800  -0.1206   0.5839   0.3131
  -2.000   0.0522   0.01484   0.00787  -0.1207   0.5750   0.3138
  -1.750   0.0798   0.01472   0.00775  -0.1209   0.5665   0.3145
  -1.500   0.1071   0.01467   0.00763  -0.1210   0.5583   0.3152
  -1.250   0.1353   0.01457   0.00753  -0.1214   0.5512   0.3160
  -1.000   0.1634   0.01449   0.00742  -0.1216   0.5440   0.3168
  -0.750   0.1919   0.01446   0.00732  -0.1220   0.5375   0.3176
  -0.500   0.2209   0.01436   0.00723  -0.1225   0.5322   0.3185
  -0.250   0.2500   0.01428   0.00713  -0.1229   0.5268   0.3193
   0.000   0.2792   0.01424   0.00705  -0.1234   0.5217   0.3202
   0.250   0.3095   0.01425   0.00699  -0.1240   0.5168   0.3211
   0.500   0.3389   0.01416   0.00692  -0.1245   0.5130   0.3220
   0.750   0.3687   0.01411   0.00686  -0.1250   0.5089   0.3228
   1.000   0.3985   0.01409   0.00682  -0.1255   0.5050   0.3235
   1.250   0.4289   0.01412   0.00680  -0.1262   0.5012   0.3242
   1.500   0.4604   0.01420   0.00683  -0.1270   0.4973   0.3247
   1.750   0.4898   0.01395   0.00664  -0.1275   0.4943   0.3264
   2.000   0.5195   0.01386   0.00660  -0.1280   0.4912   0.3279
   2.250   0.5493   0.01385   0.00662  -0.1284   0.4882   0.3291
   2.500   0.5794   0.01388   0.00668  -0.1289   0.4854   0.3305
   2.750   0.6100   0.01396   0.00676  -0.1295   0.4826   0.3319
   3.000   0.6425   0.01410   0.00689  -0.1304   0.4796   0.3334
   3.250   0.6736   0.01418   0.00700  -0.1311   0.4773   0.3349
   3.500   0.7028   0.01420   0.00707  -0.1314   0.4751   0.3363
   3.750   0.7323   0.01423   0.00713  -0.1317   0.4726   0.3377
   4.000   0.7622   0.01428   0.00721  -0.1320   0.4701   0.3391
   4.250   0.7920   0.01435   0.00728  -0.1324   0.4675   0.3402
   4.500   0.8212   0.01442   0.00735  -0.1326   0.4644   0.3412
   4.750   0.8535   0.01446   0.00740  -0.1336   0.4607   0.3438
   5.000   0.8835   0.01453   0.00755  -0.1340   0.4580   0.3458
   5.250   0.9098   0.01454   0.00764  -0.1337   0.4550   0.3476
   5.500   0.9360   0.01457   0.00773  -0.1333   0.4512   0.3495
   5.750   0.9621   0.01461   0.00780  -0.1328   0.4472   0.3515
   6.000   0.9898   0.01473   0.00790  -0.1328   0.4427   0.3536
   6.250   1.0171   0.01485   0.00805  -0.1326   0.4384   0.3556
   6.500   1.0381   0.01484   0.00810  -0.1312   0.4342   0.3572
   6.750   1.0602   0.01481   0.00811  -0.1300   0.4294   0.3595
   7.000   1.0846   0.01485   0.00820  -0.1293   0.4247   0.3624
   7.250   1.1105   0.01500   0.00839  -0.1289   0.4200   0.3650
   7.500   1.1314   0.01504   0.00853  -0.1275   0.4155   0.3676
   7.750   1.1534   0.01514   0.00868  -0.1263   0.4104   0.3703
   8.000   1.1755   0.01533   0.00885  -0.1252   0.4046   0.3730
   8.250   1.1972   0.01547   0.00905  -0.1240   0.3988   0.3751
   8.500   1.2195   0.01552   0.00919  -0.1230   0.3919   0.3787
   8.750   1.2396   0.01574   0.00942  -0.1216   0.3849   0.3817
   9.000   1.2617   0.01587   0.00966  -0.1205   0.3772   0.3847
   9.250   1.2802   0.01612   0.00991  -0.1189   0.3676   0.3877
   9.500   1.3001   0.01635   0.01019  -0.1175   0.3548   0.3906
   9.750   1.3162   0.01672   0.01052  -0.1156   0.3380   0.3929
  10.000   1.3277   0.01727   0.01100  -0.1131   0.3136   0.3962
  10.250   1.3316   0.01824   0.01182  -0.1097   0.2807   0.3990
  10.500   1.3335   0.01943   0.01287  -0.1063   0.2512   0.4014
  10.750   1.3348   0.02073   0.01405  -0.1029   0.2262   0.4039
  11.000   1.3366   0.02207   0.01530  -0.0998   0.2032   0.4065
  11.250   1.3372   0.02355   0.01669  -0.0968   0.1832   0.4089
  11.500   1.3375   0.02514   0.01819  -0.0940   0.1659   0.4109
  11.750   1.3379   0.02684   0.01985  -0.0916   0.1503   0.4135
  12.000   1.3388   0.02863   0.02163  -0.0895   0.1369   0.4165
  12.250   1.3395   0.03056   0.02357  -0.0876   0.1253   0.4192
  12.500   1.3391   0.03270   0.02571  -0.0860   0.1150   0.4220
  12.750   1.3375   0.03509   0.02810  -0.0845   0.1060   0.4248
  13.000   1.3362   0.03759   0.03060  -0.0833   0.0975   0.4274
  13.250   1.3361   0.04014   0.03316  -0.0824   0.0904   0.4297
  13.500   1.3337   0.04306   0.03611  -0.0818   0.0839   0.4327
  13.750   1.3331   0.04591   0.03902  -0.0814   0.0780   0.4358
  14.000   1.3318   0.04895   0.04210  -0.0811   0.0729   0.4386
  14.250   1.3296   0.05216   0.04535  -0.0809   0.0681   0.4414
  14.500   1.3286   0.05532   0.04856  -0.0809   0.0640   0.4443
  14.750   1.3263   0.05871   0.05197  -0.0810   0.0602   0.4469
  15.000   1.3251   0.06207   0.05537  -0.0812   0.0568   0.4492
  15.250   1.3244   0.06549   0.05887  -0.0817   0.0534   0.4528
  15.500   1.3230   0.06903   0.06247  -0.0822   0.0505   0.4560
  15.750   1.3237   0.07238   0.06588  -0.0827   0.0477   0.4594
  16.000   1.3198   0.07635   0.06989  -0.0834   0.0453   0.4624
  16.250   1.3227   0.07950   0.07310  -0.0839   0.0429   0.4659
  16.500   1.3216   0.08322   0.07685  -0.0847   0.0408   0.4688
  16.750   1.3217   0.08692   0.08064  -0.0857   0.0388   0.4729
  17.000   1.3238   0.09035   0.08415  -0.0865   0.0370   0.4770
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