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NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NREL's S814 Airfoil (s814-nr)
Reynolds number: 200,000
Max Cl/Cd: 58.82 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s814-nr-200000-n5.txt
Download as CSV file: xf-s814-nr-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4422   0.12484   0.11932  -0.0332   1.0000   0.2313
 -12.750  -0.4308   0.12381   0.11829  -0.0327   1.0000   0.2325
 -12.250  -0.4532   0.11612   0.11052  -0.0340   1.0000   0.2419
 -12.000  -0.4381   0.11559   0.10999  -0.0332   1.0000   0.2424
 -11.750  -0.4243   0.11490   0.10930  -0.0325   1.0000   0.2429
 -11.500  -0.4113   0.11416   0.10857  -0.0317   1.0000   0.2436
 -11.250  -0.3952   0.11295   0.10735  -0.0321   0.9994   0.2443
 -11.000  -0.3690   0.11113   0.10550  -0.0351   0.9972   0.2454
 -10.500  -0.3683   0.10177   0.09599  -0.0433   0.9925   0.2554
 -10.250  -0.3413   0.10047   0.09468  -0.0452   0.9897   0.2558
 -10.000  -0.3144   0.09906   0.09325  -0.0475   0.9867   0.2563
  -9.750  -0.2865   0.09768   0.09184  -0.0499   0.9841   0.2569
  -9.500  -0.2584   0.09616   0.09031  -0.0526   0.9818   0.2576
  -9.250  -0.2310   0.09457   0.08869  -0.0554   0.9795   0.2585
  -9.000  -0.2118   0.09302   0.08714  -0.0565   0.9749   0.2594
  -8.500  -0.2192   0.08340   0.07738  -0.0643   0.9674   0.2693
  -8.250  -0.1987   0.08231   0.07629  -0.0647   0.9614   0.2697
  -8.000  -0.1735   0.08108   0.07508  -0.0661   0.9563   0.2701
  -7.750  -0.1444   0.07971   0.07370  -0.0685   0.9527   0.2706
  -7.500  -0.1302   0.07879   0.07280  -0.0676   0.9421   0.2712
  -7.250  -0.1154   0.07767   0.07170  -0.0671   0.9302   0.2718
  -7.000  -0.1033   0.07666   0.07071  -0.0661   0.9147   0.2726
  -6.750  -0.0863   0.07543   0.06948  -0.0662   0.8998   0.2735
  -6.500  -0.0626   0.07390   0.06793  -0.0679   0.8861   0.2749
  -6.250  -0.0349   0.07164   0.06563  -0.0715   0.8736   0.2765
  -5.750  -0.0093   0.06053   0.05422  -0.0864   0.8454   0.2844
  -5.500   0.0591   0.05840   0.05196  -0.0970   0.8270   0.2849
  -5.000   0.1556   0.05544   0.04861  -0.1096   0.7680   0.2861
  -4.500  -0.1555   0.02367   0.01590  -0.1134   0.7277   0.3115
  -4.250  -0.1363   0.02180   0.01366  -0.1164   0.7106   0.3133
  -4.000  -0.1105   0.02148   0.01326  -0.1167   0.6948   0.3141
  -3.750  -0.0848   0.02130   0.01303  -0.1167   0.6799   0.3148
  -3.500  -0.0592   0.02116   0.01282  -0.1167   0.6660   0.3155
  -3.000  -0.0081   0.02080   0.01235  -0.1168   0.6412   0.3169
  -2.750   0.0178   0.02057   0.01206  -0.1170   0.6306   0.3177
  -2.500   0.0439   0.02035   0.01177  -0.1173   0.6203   0.3185
  -2.250   0.0704   0.02011   0.01147  -0.1177   0.6108   0.3194
  -2.000   0.0974   0.01988   0.01116  -0.1181   0.6020   0.3204
  -1.750   0.1246   0.01962   0.01085  -0.1186   0.5935   0.3214
  -1.500   0.1523   0.01939   0.01053  -0.1192   0.5856   0.3225
  -1.250   0.1803   0.01914   0.01022  -0.1198   0.5780   0.3236
  -1.000   0.2086   0.01890   0.00990  -0.1205   0.5704   0.3248
  -0.750   0.2375   0.01869   0.00959  -0.1212   0.5640   0.3261
  -0.500   0.2667   0.01846   0.00931  -0.1220   0.5574   0.3272
  -0.250   0.2962   0.01829   0.00903  -0.1228   0.5517   0.3283
   0.000   0.3248   0.01819   0.00892  -0.1232   0.5467   0.3293
   0.250   0.3529   0.01813   0.00891  -0.1235   0.5414   0.3302
   0.500   0.3813   0.01811   0.00891  -0.1237   0.5365   0.3312
   0.750   0.4100   0.01812   0.00891  -0.1241   0.5323   0.3322
   1.000   0.4388   0.01811   0.00893  -0.1244   0.5279   0.3333
   1.250   0.4673   0.01810   0.00896  -0.1247   0.5232   0.3346
   1.500   0.4962   0.01810   0.00897  -0.1251   0.5189   0.3360
   1.750   0.5258   0.01813   0.00897  -0.1256   0.5153   0.3376
   2.000   0.5555   0.01814   0.00898  -0.1262   0.5119   0.3394
   2.250   0.5851   0.01812   0.00898  -0.1267   0.5082   0.3412
   2.500   0.6149   0.01811   0.00897  -0.1273   0.5048   0.3428
   2.750   0.6450   0.01812   0.00896  -0.1279   0.5016   0.3443
   3.000   0.6742   0.01818   0.00906  -0.1283   0.4987   0.3456
   3.250   0.7035   0.01826   0.00920  -0.1286   0.4956   0.3469
   3.500   0.7315   0.01833   0.00937  -0.1287   0.4922   0.3483
   3.750   0.7602   0.01841   0.00953  -0.1290   0.4892   0.3499
   4.000   0.7892   0.01851   0.00969  -0.1293   0.4863   0.3516
   4.250   0.8185   0.01860   0.00982  -0.1296   0.4836   0.3535
   4.500   0.8486   0.01872   0.00994  -0.1301   0.4808   0.3555
   4.750   0.8779   0.01884   0.01009  -0.1305   0.4779   0.3576
   5.000   0.9053   0.01892   0.01024  -0.1305   0.4741   0.3596
   5.250   0.9321   0.01900   0.01042  -0.1304   0.4699   0.3613
   5.500   0.9593   0.01912   0.01062  -0.1303   0.4661   0.3631
   5.750   0.9884   0.01929   0.01081  -0.1305   0.4624   0.3652
   6.000   1.0120   0.01941   0.01107  -0.1298   0.4574   0.3675
   6.250   1.0362   0.01950   0.01126  -0.1291   0.4517   0.3700
   6.500   1.0623   0.01962   0.01136  -0.1287   0.4461   0.3727
   6.750   1.0846   0.01973   0.01156  -0.1278   0.4396   0.3751
   7.000   1.1068   0.01981   0.01170  -0.1267   0.4326   0.3772
   7.250   1.1290   0.01993   0.01190  -0.1257   0.4259   0.3791
   7.500   1.1482   0.02004   0.01216  -0.1241   0.4182   0.3812
   7.750   1.1684   0.02019   0.01232  -0.1227   0.4115   0.3834
   8.000   1.1859   0.02033   0.01261  -0.1208   0.4036   0.3858
   8.250   1.2035   0.02052   0.01282  -0.1190   0.3953   0.3884
   8.500   1.2206   0.02075   0.01316  -0.1172   0.3852   0.3909
   8.750   1.2367   0.02103   0.01347  -0.1153   0.3741   0.3933
   9.000   1.2509   0.02135   0.01388  -0.1131   0.3600   0.3956
   9.250   1.2642   0.02175   0.01435  -0.1108   0.3418   0.3980
   9.500   1.2729   0.02234   0.01491  -0.1080   0.3172   0.4005
   9.750   1.2752   0.02325   0.01569  -0.1045   0.2885   0.4029
  10.000   1.2738   0.02449   0.01680  -0.1008   0.2618   0.4054
  10.250   1.2722   0.02592   0.01811  -0.0973   0.2371   0.4077
  10.500   1.2698   0.02753   0.01962  -0.0942   0.2153   0.4098
  10.750   1.2679   0.02926   0.02133  -0.0914   0.1953   0.4116
  11.000   1.2655   0.03117   0.02322  -0.0889   0.1775   0.4135
  11.250   1.2634   0.03322   0.02526  -0.0868   0.1621   0.4154
  11.500   1.2609   0.03546   0.02750  -0.0850   0.1481   0.4175
  11.750   1.2585   0.03788   0.02991  -0.0835   0.1358   0.4197
  12.000   1.2555   0.04051   0.03255  -0.0824   0.1250   0.4220
  12.250   1.2546   0.04311   0.03516  -0.0815   0.1147   0.4244
  12.750   1.2509   0.04890   0.04102  -0.0805   0.0983   0.4288
  13.000   1.2514   0.05172   0.04392  -0.0802   0.0912   0.4313
  13.250   1.2489   0.05496   0.04720  -0.0802   0.0851   0.4337
  13.500   1.2505   0.05786   0.05017  -0.0802   0.0793   0.4367
  13.750   1.2490   0.06118   0.05352  -0.0804   0.0742   0.4396
  14.000   1.2504   0.06425   0.05665  -0.0806   0.0697   0.4426
  14.250   1.2509   0.06750   0.05997  -0.0810   0.0654   0.4452
  14.500   1.2504   0.07094   0.06347  -0.0815   0.0618   0.4477
  14.750   1.2533   0.07401   0.06664  -0.0820   0.0582   0.4508
  15.000   1.2538   0.07744   0.07013  -0.0827   0.0550   0.4540
  15.250   1.2540   0.08098   0.07373  -0.0834   0.0523   0.4574
  15.500   1.2575   0.08412   0.07696  -0.0841   0.0496   0.4611
  15.750   1.2591   0.08759   0.08052  -0.0849   0.0472   0.4643
  16.000   1.2588   0.09135   0.08434  -0.0859   0.0451   0.4677
  16.250   1.2620   0.09465   0.08774  -0.0868   0.0432   0.4718
  16.500   1.2650   0.09804   0.09121  -0.0878   0.0412   0.4760
  16.750   1.2667   0.10163   0.09488  -0.0890   0.0395   0.4796
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