Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NREL's S814 Airfoil (s814-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NREL's S814 Airfoil (s814-nr)
Reynolds number: 1,000,000
Max Cl/Cd: 97.14 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s814-nr-1000000-n5.txt
Download as CSV file: xf-s814-nr-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.8019   0.10809   0.10476  -0.0571   0.9938   0.1295
 -17.500  -0.8584   0.09782   0.09475  -0.0606   0.9936   0.1654
 -17.250  -0.8842   0.09163   0.08865  -0.0629   0.9933   0.1821
 -17.000  -0.8804   0.08915   0.08640  -0.0642   0.9931   0.2040
 -16.750  -0.8622   0.08831   0.08561  -0.0650   0.9929   0.2128
 -16.500  -0.8464   0.08717   0.08447  -0.0659   0.9927   0.2172
 -16.250  -0.9289   0.07470   0.07190  -0.0698   0.9923   0.2268
 -16.000  -0.9365   0.07166   0.06884  -0.0700   0.9916   0.2306
 -15.750  -0.9634   0.06648   0.06363  -0.0709   0.9908   0.2357
 -15.500  -1.0423   0.05600   0.05297  -0.0733   0.9892   0.2391
 -15.250  -1.0646   0.05132   0.04819  -0.0747   0.9880   0.2406
 -15.000  -1.0789   0.04748   0.04431  -0.0760   0.9869   0.2439
 -14.750  -1.0889   0.04401   0.04081  -0.0773   0.9858   0.2470
 -14.500  -1.0996   0.04037   0.03710  -0.0790   0.9846   0.2497
 -14.250  -1.1060   0.03687   0.03351  -0.0813   0.9833   0.2524
 -14.000  -1.1083   0.03371   0.03025  -0.0837   0.9822   0.2543
 -13.750  -1.0973   0.03134   0.02780  -0.0868   0.9811   0.2555
 -13.500  -1.0977   0.02881   0.02525  -0.0882   0.9773   0.2585
 -13.250  -1.0879   0.02639   0.02281  -0.0909   0.9724   0.2618
 -13.000  -1.0638   0.02442   0.02078  -0.0952   0.9699   0.2647
 -12.750  -1.0366   0.02260   0.01888  -0.0998   0.9682   0.2670
 -12.500  -1.0075   0.02100   0.01719  -0.1043   0.9671   0.2683
 -12.250  -1.0310   0.01959   0.01573  -0.0991   0.9580   0.2686
 -12.000  -1.0081   0.01850   0.01457  -0.1011   0.9556   0.2689
 -11.750  -0.9759   0.01755   0.01356  -0.1044   0.9542   0.2690
 -11.500  -0.9402   0.01672   0.01268  -0.1080   0.9530   0.2695
 -11.250  -0.9481   0.01569   0.01160  -0.1044   0.9431   0.2700
 -11.000  -0.9176   0.01489   0.01076  -0.1070   0.9404   0.2707
 -10.750  -0.8830   0.01418   0.01000  -0.1102   0.9384   0.2713
 -10.500  -0.8803   0.01365   0.00943  -0.1071   0.9275   0.2718
 -10.000  -0.8312   0.01283   0.00853  -0.1078   0.9142   0.2727
  -9.750  -0.7941   0.01242   0.00808  -0.1104   0.9083   0.2732
  -9.500  -0.7500   0.01204   0.00766  -0.1142   0.8989   0.2736
  -9.250  -0.6891   0.01170   0.00724  -0.1214   0.8874   0.2742
  -9.000  -0.6410   0.01145   0.00683  -0.1259   0.8606   0.2747
  -8.750  -0.6117   0.01133   0.00654  -0.1268   0.8271   0.2751
  -8.500  -0.5874   0.01126   0.00631  -0.1266   0.7964   0.2755
  -8.250  -0.5636   0.01118   0.00611  -0.1263   0.7705   0.2759
  -8.000  -0.5392   0.01111   0.00591  -0.1262   0.7471   0.2764
  -7.750  -0.5143   0.01103   0.00573  -0.1260   0.7261   0.2768
  -7.500  -0.4888   0.01097   0.00556  -0.1260   0.7064   0.2773
  -7.250  -0.4628   0.01090   0.00540  -0.1260   0.6878   0.2777
  -7.000  -0.4363   0.01084   0.00524  -0.1262   0.6700   0.2781
  -6.750  -0.4093   0.01078   0.00509  -0.1263   0.6533   0.2786
  -6.500  -0.3816   0.01071   0.00495  -0.1267   0.6387   0.2790
  -6.250  -0.3535   0.01064   0.00481  -0.1270   0.6259   0.2795
  -6.000  -0.3254   0.01058   0.00468  -0.1274   0.6138   0.2799
  -5.750  -0.2972   0.01053   0.00456  -0.1277   0.6019   0.2804
  -5.500  -0.2684   0.01046   0.00444  -0.1282   0.5912   0.2808
  -5.250  -0.2398   0.01042   0.00434  -0.1285   0.5810   0.2812
  -5.000  -0.2108   0.01037   0.00423  -0.1290   0.5711   0.2816
  -4.750  -0.1819   0.01033   0.00414  -0.1294   0.5622   0.2820
  -4.500  -0.1528   0.01029   0.00405  -0.1299   0.5532   0.2824
  -4.250  -0.1237   0.01025   0.00396  -0.1303   0.5451   0.2827
  -4.000  -0.0944   0.01022   0.00388  -0.1307   0.5366   0.2830
  -3.750  -0.0653   0.01020   0.00382  -0.1311   0.5289   0.2833
  -3.500  -0.0359   0.01017   0.00375  -0.1316   0.5213   0.2837
  -3.000   0.0235   0.01005   0.00359  -0.1327   0.5090   0.2858
  -2.750   0.0533   0.01001   0.00352  -0.1332   0.5030   0.2868
  -2.500   0.0827   0.00999   0.00347  -0.1337   0.4973   0.2876
  -2.250   0.1127   0.00995   0.00342  -0.1342   0.4928   0.2884
  -2.000   0.1426   0.00992   0.00338  -0.1347   0.4880   0.2892
  -1.750   0.1721   0.00991   0.00336  -0.1351   0.4830   0.2899
  -1.500   0.2016   0.00991   0.00333  -0.1355   0.4787   0.2907
  -1.250   0.2316   0.00989   0.00331  -0.1360   0.4751   0.2915
  -1.000   0.2613   0.00988   0.00330  -0.1364   0.4710   0.2923
  -0.750   0.2908   0.00988   0.00329  -0.1368   0.4666   0.2931
  -0.250   0.3498   0.00990   0.00329  -0.1375   0.4596   0.2947
   0.000   0.3795   0.00990   0.00329  -0.1379   0.4566   0.2955
   0.250   0.4091   0.00991   0.00330  -0.1382   0.4535   0.2962
   0.500   0.4383   0.00993   0.00331  -0.1385   0.4505   0.2969
   0.750   0.4674   0.00996   0.00333  -0.1388   0.4475   0.2974
   1.000   0.4965   0.00999   0.00336  -0.1390   0.4448   0.2980
   1.250   0.5261   0.01000   0.00339  -0.1393   0.4428   0.2985
   1.500   0.5559   0.01000   0.00341  -0.1397   0.4407   0.3000
   1.750   0.5855   0.01001   0.00344  -0.1400   0.4383   0.3014
   2.000   0.6147   0.01003   0.00348  -0.1403   0.4358   0.3028
   2.250   0.6437   0.01007   0.00353  -0.1405   0.4331   0.3041
   2.500   0.6724   0.01011   0.00359  -0.1406   0.4306   0.3054
   2.750   0.7010   0.01017   0.00366  -0.1407   0.4282   0.3067
   3.000   0.7302   0.01020   0.00372  -0.1409   0.4269   0.3080
   3.250   0.7592   0.01023   0.00378  -0.1411   0.4253   0.3093
   3.500   0.7877   0.01027   0.00385  -0.1411   0.4226   0.3106
   3.750   0.8157   0.01032   0.00391  -0.1411   0.4190   0.3118
   4.000   0.8427   0.01040   0.00399  -0.1408   0.4147   0.3128
   4.250   0.8696   0.01049   0.00408  -0.1406   0.4105   0.3142
   4.500   0.8982   0.01051   0.00415  -0.1407   0.4066   0.3166
   4.750   0.9256   0.01057   0.00423  -0.1405   0.4015   0.3185
   5.000   0.9517   0.01068   0.00434  -0.1401   0.3959   0.3203
   5.250   0.9790   0.01074   0.00444  -0.1399   0.3909   0.3222
   5.500   1.0057   0.01083   0.00454  -0.1396   0.3839   0.3240
   5.750   1.0311   0.01097   0.00467  -0.1391   0.3773   0.3256
   6.000   1.0583   0.01106   0.00478  -0.1389   0.3712   0.3271
   6.250   1.0831   0.01123   0.00493  -0.1382   0.3613   0.3283
   6.500   1.1084   0.01141   0.00509  -0.1377   0.3469   0.3303
   6.750   1.1299   0.01178   0.00535  -0.1366   0.3195   0.3326
   7.000   1.1454   0.01245   0.00581  -0.1345   0.2791   0.3345
   7.250   1.1618   0.01309   0.00629  -0.1326   0.2487   0.3365
   7.500   1.1783   0.01370   0.00678  -0.1308   0.2209   0.3385
   7.750   1.1941   0.01433   0.00728  -0.1288   0.1957   0.3403
   8.000   1.2072   0.01505   0.00786  -0.1264   0.1692   0.3418
   8.250   1.2210   0.01573   0.00843  -0.1242   0.1462   0.3432
   8.500   1.2347   0.01641   0.00901  -0.1220   0.1277   0.3444
   8.750   1.2495   0.01702   0.00957  -0.1200   0.1139   0.3470
   9.000   1.2638   0.01768   0.01018  -0.1180   0.1006   0.3494
   9.250   1.2787   0.01829   0.01078  -0.1161   0.0912   0.3518
   9.500   1.2926   0.01896   0.01142  -0.1141   0.0825   0.3540
   9.750   1.3050   0.01971   0.01215  -0.1120   0.0739   0.3559
  10.000   1.3191   0.02040   0.01284  -0.1102   0.0675   0.3576
  10.250   1.3306   0.02123   0.01365  -0.1081   0.0613   0.3590
  10.500   1.3429   0.02205   0.01447  -0.1062   0.0560   0.3601
  10.750   1.3545   0.02295   0.01538  -0.1043   0.0517   0.3624
  11.000   1.3661   0.02387   0.01633  -0.1026   0.0479   0.3646
  11.250   1.3757   0.02496   0.01743  -0.1007   0.0442   0.3667
  11.500   1.3864   0.02604   0.01855  -0.0991   0.0411   0.3687
  11.750   1.3944   0.02734   0.01986  -0.0973   0.0380   0.3707
  12.000   1.4037   0.02862   0.02118  -0.0958   0.0355   0.3725
  12.250   1.4113   0.03008   0.02267  -0.0944   0.0331   0.3742
  12.500   1.4185   0.03166   0.02428  -0.0930   0.0311   0.3755
  12.750   1.4266   0.03324   0.02591  -0.0919   0.0296   0.3770
  13.000   1.4333   0.03502   0.02773  -0.0908   0.0280   0.3796
  13.250   1.4387   0.03702   0.02978  -0.0899   0.0264   0.3822
  13.500   1.4457   0.03894   0.03176  -0.0891   0.0253   0.3848
  13.750   1.4512   0.04106   0.03394  -0.0885   0.0241   0.3871
  14.000   1.4551   0.04341   0.03634  -0.0879   0.0229   0.3893
  14.250   1.4587   0.04588   0.03885  -0.0874   0.0218   0.3912
  14.500   1.4638   0.04825   0.04128  -0.0871   0.0210   0.3927
  14.750   1.4679   0.05079   0.04389  -0.0869   0.0201   0.3949
  15.000   1.4704   0.05357   0.04672  -0.0868   0.0191   0.3974
  15.250   1.4726   0.05645   0.04967  -0.0868   0.0184   0.3999
  15.500   1.4758   0.05927   0.05255  -0.0868   0.0177   0.4024
  15.750   1.4790   0.06215   0.05550  -0.0870   0.0171   0.4048
  16.000   1.4812   0.06518   0.05860  -0.0872   0.0164   0.4072
  16.250   1.4829   0.06832   0.06179  -0.0875   0.0158   0.4093
  16.500   1.4845   0.07155   0.06508  -0.0879   0.0151   0.4124
  16.750   1.4862   0.07483   0.06843  -0.0884   0.0147   0.4160
  17.000   1.4887   0.07802   0.07170  -0.0890   0.0143   0.4196
  17.250   1.4915   0.08120   0.07494  -0.0895   0.0138   0.4230
  17.500   1.4930   0.08461   0.07842  -0.0902   0.0134   0.4259
  17.750   1.4950   0.08798   0.08186  -0.0910   0.0130   0.4297
  18.000   1.4962   0.09152   0.08547  -0.0919   0.0126   0.4338
  18.250   1.4970   0.09512   0.08914  -0.0928   0.0122   0.4381
<< Back to NREL's S814 Airfoil (s814-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S814 Airfoil (s814-nr)