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NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NREL's S814 Airfoil (s814-nr)
Reynolds number: 500,000
Max Cl/Cd: 84.38 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s814-nr-500000.txt
Download as CSV file: xf-s814-nr-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S814 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2491   0.10064   0.09705  -0.0483   0.9868   0.2588
  -9.500  -0.2199   0.09931   0.09571  -0.0510   0.9848   0.2598
  -9.250  -0.2540   0.09133   0.08763  -0.0577   0.9825   0.2684
  -9.000  -0.2101   0.09099   0.08730  -0.0599   0.9815   0.2677
  -8.750  -0.1603   0.09119   0.08751  -0.0618   0.9807   0.2660
  -8.500  -0.1347   0.09066   0.08700  -0.0630   0.9771   0.2720
  -8.250  -0.6151   0.02894   0.02457  -0.0898   0.9397   0.3014
  -8.000  -0.6095   0.02557   0.02108  -0.0942   0.9279   0.3028
  -7.750  -0.5777   0.02383   0.01924  -0.0986   0.9243   0.3037
  -7.500  -0.5625   0.02243   0.01776  -0.0990   0.9136   0.3044
  -7.250  -0.5309   0.02128   0.01653  -0.1017   0.9092   0.3051
  -7.000  -0.5112   0.02031   0.01548  -0.1017   0.8979   0.3057
  -6.750  -0.4751   0.01939   0.01449  -0.1046   0.8928   0.3065
  -6.500  -0.4444   0.01862   0.01364  -0.1063   0.8820   0.3072
  -6.250  -0.3982   0.01780   0.01273  -0.1108   0.8755   0.3079
  -6.000  -0.3498   0.01712   0.01196  -0.1158   0.8640   0.3087
  -5.750  -0.2924   0.01654   0.01125  -0.1225   0.8499   0.3096
  -5.500  -0.2449   0.01607   0.01062  -0.1271   0.8284   0.3103
  -5.250  -0.2106   0.01574   0.01011  -0.1291   0.8031   0.3110
  -5.000  -0.1819   0.01549   0.00969  -0.1298   0.7784   0.3116
  -4.750  -0.1556   0.01530   0.00934  -0.1300   0.7558   0.3121
  -4.500  -0.1302   0.01513   0.00902  -0.1300   0.7345   0.3126
  -4.250  -0.1048   0.01499   0.00875  -0.1300   0.7149   0.3130
  -4.000  -0.0791   0.01487   0.00850  -0.1299   0.6969   0.3134
  -3.750  -0.0542   0.01435   0.00786  -0.1301   0.6803   0.3145
  -3.500  -0.0286   0.01410   0.00753  -0.1301   0.6650   0.3154
  -3.250  -0.0026   0.01397   0.00733  -0.1300   0.6506   0.3162
  -3.000   0.0237   0.01388   0.00718  -0.1299   0.6368   0.3169
  -2.750   0.0505   0.01380   0.00705  -0.1299   0.6240   0.3176
  -2.500   0.0776   0.01375   0.00696  -0.1299   0.6124   0.3184
  -2.000   0.1326   0.01369   0.00682  -0.1302   0.5917   0.3202
  -1.750   0.1603   0.01369   0.00675  -0.1303   0.5828   0.3212
  -1.500   0.1887   0.01362   0.00666  -0.1306   0.5743   0.3222
  -1.250   0.2169   0.01360   0.00656  -0.1308   0.5666   0.3231
  -1.000   0.2459   0.01352   0.00647  -0.1312   0.5594   0.3241
  -0.750   0.2746   0.01349   0.00638  -0.1316   0.5526   0.3251
  -0.500   0.3038   0.01347   0.00630  -0.1320   0.5467   0.3260
  -0.250   0.3331   0.01341   0.00623  -0.1324   0.5406   0.3269
   0.000   0.3621   0.01341   0.00618  -0.1328   0.5349   0.3277
   0.250   0.3917   0.01344   0.00616  -0.1332   0.5298   0.3283
   0.500   0.4213   0.01328   0.00600  -0.1337   0.5251   0.3295
   0.750   0.4505   0.01317   0.00591  -0.1342   0.5206   0.3310
   1.000   0.4799   0.01318   0.00591  -0.1346   0.5165   0.3322
   1.250   0.5098   0.01322   0.00596  -0.1350   0.5127   0.3334
   1.500   0.5391   0.01322   0.00601  -0.1353   0.5091   0.3346
   1.750   0.5685   0.01324   0.00606  -0.1357   0.5056   0.3358
   2.000   0.5980   0.01329   0.00611  -0.1360   0.5022   0.3372
   2.250   0.6282   0.01338   0.00617  -0.1365   0.4987   0.3386
   2.500   0.6587   0.01346   0.00625  -0.1371   0.4955   0.3400
   2.750   0.6881   0.01348   0.00631  -0.1374   0.4928   0.3414
   3.000   0.7178   0.01353   0.00638  -0.1377   0.4900   0.3428
   3.250   0.7476   0.01361   0.00645  -0.1381   0.4872   0.3438
   3.500   0.7776   0.01358   0.00645  -0.1386   0.4845   0.3459
   3.750   0.8081   0.01366   0.00656  -0.1392   0.4815   0.3479
   4.000   0.8383   0.01379   0.00673  -0.1396   0.4783   0.3497
   4.250   0.8657   0.01382   0.00684  -0.1395   0.4751   0.3515
   4.500   0.8937   0.01388   0.00695  -0.1394   0.4715   0.3533
   4.750   0.9217   0.01394   0.00704  -0.1394   0.4679   0.3552
   5.000   0.9511   0.01409   0.00715  -0.1397   0.4637   0.3572
   5.250   0.9781   0.01417   0.00727  -0.1395   0.4596   0.3589
   5.500   1.0036   0.01420   0.00734  -0.1389   0.4549   0.3603
   5.750   1.0299   0.01414   0.00735  -0.1386   0.4501   0.3631
   6.000   1.0578   0.01430   0.00751  -0.1386   0.4447   0.3652
   6.250   1.0811   0.01430   0.00762  -0.1376   0.4399   0.3673
   6.500   1.1057   0.01435   0.00773  -0.1369   0.4351   0.3696
   6.750   1.1309   0.01448   0.00786  -0.1363   0.4301   0.3719
   7.000   1.1540   0.01457   0.00800  -0.1354   0.4249   0.3741
   7.250   1.1745   0.01461   0.00809  -0.1338   0.4188   0.3759
   7.500   1.1962   0.01469   0.00817  -0.1326   0.4120   0.3787
   7.750   1.2181   0.01473   0.00834  -0.1315   0.4056   0.3814
   8.000   1.2395   0.01487   0.00854  -0.1302   0.3984   0.3840
   8.250   1.2608   0.01505   0.00877  -0.1290   0.3909   0.3867
   8.500   1.2816   0.01523   0.00898  -0.1276   0.3812   0.3894
   8.750   1.3020   0.01543   0.00921  -0.1262   0.3694   0.3918
   9.000   1.3206   0.01569   0.00946  -0.1246   0.3540   0.3942
   9.250   1.3353   0.01609   0.00982  -0.1225   0.3301   0.3970
   9.500   1.3433   0.01684   0.01043  -0.1194   0.2958   0.3993
   9.750   1.3470   0.01792   0.01132  -0.1159   0.2615   0.4014
  10.000   1.3498   0.01910   0.01234  -0.1124   0.2315   0.4036
  10.250   1.3536   0.02029   0.01340  -0.1092   0.2048   0.4058
  10.500   1.3567   0.02156   0.01455  -0.1060   0.1820   0.4079
  10.750   1.3602   0.02286   0.01576  -0.1031   0.1622   0.4096
  11.000   1.3637   0.02421   0.01707  -0.1005   0.1451   0.4124
  11.250   1.3664   0.02569   0.01853  -0.0980   0.1302   0.4148
  11.500   1.3689   0.02729   0.02011  -0.0957   0.1175   0.4171
  11.750   1.3708   0.02902   0.02183  -0.0936   0.1064   0.4196
  12.000   1.3711   0.03099   0.02378  -0.0916   0.0966   0.4220
  12.250   1.3729   0.03299   0.02578  -0.0900   0.0881   0.4245
  12.500   1.3744   0.03512   0.02792  -0.0886   0.0811   0.4266
  12.750   1.3743   0.03757   0.03041  -0.0875   0.0745   0.4296
  13.000   1.3768   0.03991   0.03281  -0.0866   0.0690   0.4323
  13.250   1.3750   0.04274   0.03567  -0.0859   0.0640   0.4348
  13.500   1.3766   0.04536   0.03835  -0.0853   0.0597   0.4375
  13.750   1.3759   0.04832   0.04135  -0.0850   0.0559   0.4400
  14.000   1.3734   0.05156   0.04463  -0.0847   0.0524   0.4423
  14.250   1.3757   0.05439   0.04753  -0.0847   0.0494   0.4452
  14.500   1.3740   0.05776   0.05097  -0.0848   0.0467   0.4480
  14.750   1.3714   0.06131   0.05458  -0.0850   0.0442   0.4508
  15.000   1.3740   0.06429   0.05766  -0.0852   0.0422   0.4541
  15.250   1.3735   0.06771   0.06112  -0.0856   0.0402   0.4573
  15.500   1.3696   0.07163   0.06507  -0.0861   0.0384   0.4602
  15.750   1.3702   0.07510   0.06864  -0.0867   0.0368   0.4639
  16.000   1.3729   0.07832   0.07196  -0.0873   0.0353   0.4679
  16.250   1.3735   0.08183   0.07555  -0.0880   0.0339   0.4720
  16.500   1.3714   0.08578   0.07952  -0.0889   0.0326   0.4757
  16.750   1.3675   0.09005   0.08386  -0.0899   0.0314   0.4792
  17.000   1.3722   0.09318   0.08712  -0.0907   0.0303   0.4841
  17.250   1.3745   0.09665   0.09068  -0.0917   0.0293   0.4891
  17.500   1.3759   0.10024   0.09432  -0.0927   0.0283   0.4942
  17.750   1.3752   0.10426   0.09842  -0.0941   0.0274   0.4992
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