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 S827 Airfoil (s827-nr) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: NREL's S827 Airfoil (s827-nr)
Reynolds number: 500,000
Max Cl/Cd: 81.34 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s827-nr-500000-n5.txt
Download as CSV file: xf-s827-nr-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NREL's S827 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.2628   0.08960   0.08618  -0.1335   0.8082   0.0037
 -13.750  -0.2850   0.08275   0.07926  -0.1360   0.8057   0.0037
 -13.500  -0.3045   0.07737   0.07379  -0.1374   0.8034   0.0036
 -13.250  -0.3298   0.07181   0.06813  -0.1379   0.8008   0.0036
 -13.000  -0.3478   0.06762   0.06384  -0.1379   0.7980   0.0036
 -12.750  -0.3676   0.06342   0.05951  -0.1372   0.7951   0.0035
 -12.500  -0.3833   0.05986   0.05581  -0.1361   0.7925   0.0035
 -12.000  -0.4169   0.05215   0.04778  -0.1325   0.7878   0.0034
 -11.750  -0.4285   0.04841   0.04385  -0.1303   0.7855   0.0033
 -11.500  -0.4376   0.04386   0.03903  -0.1278   0.7833   0.0032
 -11.250  -0.4235   0.03424   0.02843  -0.1248   0.7823   0.0029
 -11.000  -0.3952   0.03248   0.02633  -0.1246   0.7808   0.0029
 -10.750  -0.3636   0.03149   0.02505  -0.1244   0.7794   0.0029
 -10.500  -0.3374   0.03099   0.02435  -0.1239   0.7779   0.0030
 -10.250  -0.3143   0.03060   0.02384  -0.1235   0.7764   0.0029
 -10.000  -0.2920   0.03028   0.02342  -0.1228   0.7749   0.0030
  -9.750  -0.2719   0.02993   0.02299  -0.1221   0.7734   0.0031
  -9.500  -0.2533   0.02952   0.02253  -0.1214   0.7718   0.0030
  -9.250  -0.2365   0.02908   0.02203  -0.1204   0.7702   0.0032
  -9.000  -0.2207   0.02858   0.02149  -0.1194   0.7686   0.0034
  -8.750  -0.2062   0.02801   0.02087  -0.1183   0.7671   0.0037
  -8.500  -0.1916   0.02743   0.02023  -0.1174   0.7656   0.0039
  -8.250  -0.1781   0.02681   0.01956  -0.1164   0.7643   0.0039
  -8.000  -0.1649   0.02617   0.01887  -0.1154   0.7629   0.0040
  -7.750  -0.1553   0.02538   0.01805  -0.1139   0.7617   0.0047
  -7.500  -0.1424   0.02472   0.01736  -0.1129   0.7604   0.0045
  -7.250  -0.1327   0.02393   0.01656  -0.1115   0.7589   0.0057
  -7.000  -0.1240   0.02309   0.01571  -0.1100   0.7573   0.0070
  -6.750  -0.1157   0.02222   0.01482  -0.1084   0.7558   0.0086
  -6.500  -0.1089   0.02129   0.01390  -0.1067   0.7544   0.0138
  -6.250  -0.1018   0.02036   0.01298  -0.1050   0.7531   0.0179
  -6.000  -0.0968   0.01934   0.01199  -0.1030   0.7518   0.0264
  -5.750  -0.0931   0.01827   0.01094  -0.1009   0.7506   0.0377
  -5.500  -0.0920   0.01709   0.00980  -0.0984   0.7493   0.0545
  -5.250  -0.0913   0.01593   0.00866  -0.0959   0.7482   0.0752
  -5.000  -0.0955   0.01467   0.00749  -0.0925   0.7469   0.1032
  -4.750  -0.1064   0.01370   0.00658  -0.0874   0.7455   0.1305
  -4.500  -0.1142   0.01286   0.00588  -0.0825   0.7441   0.1829
  -4.250  -0.1374   0.01083   0.00439  -0.0754   0.7424   0.3699
  -4.000  -0.1270   0.01005   0.00405  -0.0734   0.7413   0.5045
  -3.750  -0.1002   0.01008   0.00405  -0.0737   0.7404   0.5222
  -3.500  -0.0729   0.01016   0.00409  -0.0741   0.7394   0.5344
  -3.250  -0.0450   0.01022   0.00405  -0.0746   0.7386   0.5410
  -3.000  -0.0171   0.01027   0.00410  -0.0751   0.7378   0.5464
  -2.750   0.0109   0.01042   0.00419  -0.0756   0.7371   0.5539
  -2.500   0.0392   0.01044   0.00412  -0.0762   0.7365   0.5555
  -2.250   0.0677   0.01041   0.00404  -0.0769   0.7358   0.5560
  -2.000   0.0963   0.01038   0.00398  -0.0776   0.7352   0.5565
  -1.750   0.1250   0.01036   0.00393  -0.0783   0.7346   0.5571
  -1.500   0.1539   0.01035   0.00390  -0.0791   0.7341   0.5577
  -1.250   0.1824   0.01036   0.00389  -0.0798   0.7335   0.5584
  -1.000   0.2098   0.01036   0.00389  -0.0803   0.7328   0.5590
  -0.750   0.2372   0.01037   0.00391  -0.0808   0.7322   0.5597
  -0.500   0.2646   0.01039   0.00394  -0.0812   0.7315   0.5604
  -0.250   0.2919   0.01042   0.00397  -0.0817   0.7307   0.5611
   0.000   0.3192   0.01044   0.00401  -0.0821   0.7298   0.5619
   0.250   0.3465   0.01046   0.00405  -0.0826   0.7289   0.5627
   0.500   0.3739   0.01050   0.00410  -0.0831   0.7281   0.5636
   0.750   0.4014   0.01054   0.00415  -0.0836   0.7274   0.5646
   1.000   0.4289   0.01058   0.00422  -0.0841   0.7267   0.5657
   1.250   0.4565   0.01063   0.00429  -0.0846   0.7260   0.5667
   1.500   0.4842   0.01068   0.00436  -0.0851   0.7253   0.5677
   1.750   0.5119   0.01074   0.00443  -0.0857   0.7246   0.5686
   2.000   0.5397   0.01079   0.00452  -0.0863   0.7239   0.5694
   2.250   0.5678   0.01083   0.00459  -0.0869   0.7231   0.5702
   2.500   0.5959   0.01087   0.00468  -0.0875   0.7223   0.5712
   2.750   0.6241   0.01092   0.00479  -0.0881   0.7217   0.5722
   3.000   0.6525   0.01098   0.00491  -0.0888   0.7211   0.5731
   3.250   0.6813   0.01104   0.00502  -0.0896   0.7204   0.5742
   3.500   0.7103   0.01111   0.00515  -0.0904   0.7195   0.5752
   3.750   0.7317   0.01121   0.00536  -0.0896   0.7178   0.5763
   4.000   0.7542   0.01131   0.00555  -0.0891   0.7161   0.5775
   4.250   0.7775   0.01140   0.00572  -0.0887   0.7142   0.5787
   4.500   0.8058   0.01113   0.00548  -0.0891   0.7085   0.5799
   4.750   0.8212   0.01083   0.00521  -0.0866   0.6977   0.5811
   5.000   0.8341   0.01059   0.00499  -0.0837   0.6861   0.5825
   5.250   0.8508   0.01046   0.00487  -0.0817   0.6775   0.5837
   5.500   0.8530   0.01056   0.00507  -0.0769   0.6697   0.5849
   5.750   0.8643   0.01065   0.00524  -0.0739   0.6603   0.5863
   6.000   0.8711   0.01085   0.00551  -0.0702   0.6452   0.5876
   6.250   0.8716   0.01113   0.00570  -0.0653   0.6071   0.5890
   6.750   0.8321   0.01351   0.00752  -0.0492   0.5019   0.5915
   7.000   0.8082   0.01532   0.00906  -0.0414   0.4485   0.5927
   7.250   0.7949   0.01697   0.01049  -0.0358   0.4025   0.5940
   7.500   0.7826   0.01872   0.01199  -0.0306   0.3506   0.5953
   7.750   0.7744   0.02040   0.01340  -0.0262   0.2955   0.5967
   8.000   0.7735   0.02181   0.01458  -0.0229   0.2482   0.5980
   8.250   0.7775   0.02303   0.01561  -0.0205   0.2072   0.5993
   8.500   0.7842   0.02413   0.01658  -0.0184   0.1697   0.6008
   8.750   0.7920   0.02522   0.01752  -0.0165   0.1365   0.6024
   9.000   0.8021   0.02620   0.01839  -0.0150   0.1092   0.6042
   9.250   0.8136   0.02715   0.01925  -0.0137   0.0855   0.6060
   9.500   0.8256   0.02809   0.02011  -0.0125   0.0671   0.6080
   9.750   0.8386   0.02899   0.02097  -0.0114   0.0521   0.6103
  10.000   0.8528   0.02984   0.02179  -0.0105   0.0420   0.6123
  10.250   0.8668   0.03070   0.02266  -0.0096   0.0336   0.6143
  10.500   0.8806   0.03160   0.02357  -0.0087   0.0274   0.6166
  10.750   0.8957   0.03243   0.02445  -0.0080   0.0230   0.6190
  11.000   0.9094   0.03338   0.02540  -0.0072   0.0185   0.6214
  11.250   0.9244   0.03424   0.02631  -0.0065   0.0156   0.6238
  11.500   0.9374   0.03526   0.02734  -0.0057   0.0130   0.6262
  11.750   0.9521   0.03617   0.02831  -0.0051   0.0106   0.6285
  12.000   0.9653   0.03720   0.02938  -0.0043   0.0086   0.6311
  12.250   0.9793   0.03821   0.03048  -0.0037   0.0074   0.6340
  12.500   0.9920   0.03932   0.03165  -0.0030   0.0065   0.6369
  12.750   1.0047   0.04045   0.03284  -0.0023   0.0051   0.6398
  13.000   1.0177   0.04157   0.03404  -0.0017   0.0048   0.6426
  13.250   1.0289   0.04286   0.03541  -0.0010   0.0040   0.6456
  13.500   1.0387   0.04431   0.03696  -0.0001   0.0034   0.6488
  13.750   1.0523   0.04542   0.03814   0.0002   0.0029   0.6524
  14.000   1.0635   0.04679   0.03959   0.0008   0.0026   0.6557
  14.250   1.0718   0.04842   0.04132   0.0015   0.0023   0.6592
  14.500   1.0810   0.05001   0.04303   0.0021   0.0021   0.6633
  14.750   1.0894   0.05172   0.04486   0.0027   0.0021   0.6673
  15.250   1.1054   0.05528   0.04868   0.0037   0.0018   0.6750
  15.500   1.1124   0.05722   0.05074   0.0041   0.0018   0.6793
  15.750   1.1186   0.05928   0.05293   0.0045   0.0017   0.6835
  16.000   1.1253   0.06130   0.05507   0.0047   0.0015   0.6875
  16.250   1.1300   0.06361   0.05752   0.0050   0.0015   0.6919
  16.500   1.1338   0.06607   0.06010   0.0051   0.0014   0.6963
  16.750   1.1376   0.06859   0.06276   0.0051   0.0013   0.7007
  17.000   1.1373   0.07169   0.06601   0.0052   0.0013   0.7050
  17.250   1.1389   0.07459   0.06906   0.0049   0.0012   0.7099
  17.750   1.1342   0.08172   0.07653   0.0040   0.0013   0.7187
  18.000   1.1323   0.08537   0.08033   0.0033   0.0012   0.7238
  18.250   1.1199   0.09067   0.08581   0.0020   0.0011   0.7277
  18.500   1.1145   0.09508   0.09038   0.0007   0.0011   0.7322
  18.750   1.1059   0.10012   0.09560  -0.0011   0.0011   0.7368
  19.000   1.1002   0.10489   0.10053  -0.0029   0.0010   0.7418
  19.250   1.0876   0.11091   0.10674  -0.0055   0.0011   0.7458
<< Back to NREL's S827 Airfoil (s827-nr)

Polar data table (+)

Polar graphs


<< Back to NREL's S827 Airfoil (s827-nr)