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EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 793 AIRFOIL (e793-il)
Reynolds number: 500,000
Max Cl/Cd: 102.55 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e793-il-500000.txt
Download as CSV file: xf-e793-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 793 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
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5117   0.09570   0.09304  -0.0547   1.0000   0.0224
 -13.500  -0.5681   0.08106   0.07825  -0.0633   1.0000   0.0218
 -13.250  -0.6129   0.07024   0.06726  -0.0703   1.0000   0.0214
 -13.000  -0.6453   0.06238   0.05925  -0.0754   1.0000   0.0212
 -12.750  -0.6736   0.05582   0.05252  -0.0794   1.0000   0.0211
 -12.500  -0.7008   0.05006   0.04660  -0.0825   1.0000   0.0209
 -12.250  -0.7197   0.04603   0.04245  -0.0839   1.0000   0.0209
 -12.000  -0.7425   0.04240   0.03868  -0.0842   1.0000   0.0208
 -11.750  -0.7659   0.04004   0.03625  -0.0824   1.0000   0.0208
 -11.500  -0.7864   0.03755   0.03362  -0.0819   0.9984   0.0208
 -11.250  -0.7610   0.03398   0.02976  -0.0882   0.9938   0.0210
 -11.000  -0.7349   0.03157   0.02711  -0.0919   0.9887   0.0214
 -10.750  -0.7052   0.02943   0.02473  -0.0954   0.9849   0.0218
 -10.500  -0.6742   0.02759   0.02267  -0.0985   0.9817   0.0221
 -10.250  -0.6466   0.02611   0.02100  -0.1001   0.9758   0.0224
 -10.000  -0.6133   0.02461   0.01933  -0.1027   0.9726   0.0226
  -9.750  -0.5865   0.02261   0.01725  -0.1039   0.9677   0.0229
  -9.500  -0.5574   0.02116   0.01577  -0.1052   0.9622   0.0233
  -9.250  -0.5229   0.01999   0.01458  -0.1074   0.9591   0.0238
  -9.000  -0.4956   0.01904   0.01358  -0.1079   0.9515   0.0242
  -8.750  -0.4625   0.01807   0.01256  -0.1096   0.9468   0.0249
  -8.500  -0.4297   0.01721   0.01163  -0.1110   0.9411   0.0255
  -8.250  -0.3959   0.01643   0.01079  -0.1126   0.9339   0.0262
  -8.000  -0.3552   0.01563   0.00990  -0.1156   0.9294   0.0269
  -7.750  -0.3230   0.01454   0.00878  -0.1173   0.9185   0.0278
  -7.500  -0.2864   0.01382   0.00801  -0.1194   0.9082   0.0288
  -7.250  -0.2506   0.01323   0.00734  -0.1213   0.8957   0.0299
  -7.000  -0.2186   0.01277   0.00677  -0.1223   0.8805   0.0311
  -6.500  -0.1629   0.01187   0.00567  -0.1225   0.8477   0.0349
  -6.250  -0.1360   0.01155   0.00526  -0.1223   0.8315   0.0379
  -6.000  -0.1098   0.01116   0.00482  -0.1220   0.8158   0.0448
  -5.750  -0.0846   0.01056   0.00431  -0.1218   0.8003   0.0737
  -5.500  -0.0590   0.01008   0.00395  -0.1216   0.7853   0.1129
  -5.250  -0.0328   0.00976   0.00370  -0.1214   0.7709   0.1465
  -5.000  -0.0063   0.00952   0.00349  -0.1212   0.7567   0.1787
  -4.750   0.0203   0.00933   0.00332  -0.1210   0.7428   0.2090
  -4.500   0.0472   0.00919   0.00319  -0.1207   0.7290   0.2347
  -4.250   0.0743   0.00910   0.00310  -0.1205   0.7154   0.2586
  -4.000   0.1015   0.00904   0.00302  -0.1203   0.7023   0.2789
  -3.750   0.1289   0.00902   0.00295  -0.1200   0.6897   0.2958
  -3.250   0.1836   0.00900   0.00285  -0.1195   0.6644   0.3276
  -3.000   0.2111   0.00901   0.00281  -0.1193   0.6526   0.3421
  -2.750   0.2384   0.00902   0.00278  -0.1191   0.6411   0.3564
  -2.500   0.2658   0.00902   0.00275  -0.1189   0.6292   0.3685
  -2.250   0.2935   0.00905   0.00272  -0.1187   0.6180   0.3795
  -2.000   0.3208   0.00908   0.00270  -0.1184   0.6075   0.3903
  -1.750   0.3484   0.00909   0.00268  -0.1183   0.5965   0.4008
  -1.500   0.3761   0.00913   0.00267  -0.1181   0.5862   0.4118
  -1.250   0.4033   0.00916   0.00267  -0.1178   0.5762   0.4224
  -1.000   0.4311   0.00918   0.00267  -0.1177   0.5665   0.4334
  -0.750   0.4584   0.00924   0.00268  -0.1175   0.5572   0.4449
  -0.500   0.4861   0.00926   0.00270  -0.1173   0.5476   0.4564
  -0.250   0.5135   0.00932   0.00273  -0.1171   0.5391   0.4684
   0.000   0.5411   0.00936   0.00276  -0.1170   0.5303   0.4813
   0.250   0.5684   0.00942   0.00281  -0.1168   0.5222   0.4942
   0.500   0.5959   0.00946   0.00286  -0.1166   0.5137   0.5076
   0.750   0.6231   0.00954   0.00292  -0.1164   0.5063   0.5220
   1.000   0.6507   0.00959   0.00299  -0.1163   0.4984   0.5370
   1.250   0.6775   0.00970   0.00306  -0.1160   0.4911   0.5528
   1.500   0.7052   0.00972   0.00315  -0.1159   0.4837   0.5693
   1.750   0.7320   0.00981   0.00324  -0.1156   0.4768   0.5865
   2.000   0.7593   0.00988   0.00334  -0.1154   0.4701   0.6046
   2.250   0.7863   0.00995   0.00344  -0.1152   0.4631   0.6233
   2.500   0.8128   0.01006   0.00356  -0.1148   0.4566   0.6431
   2.750   0.8399   0.01010   0.00368  -0.1146   0.4502   0.6640
   3.000   0.8661   0.01020   0.00381  -0.1142   0.4439   0.6862
   3.250   0.8926   0.01028   0.00395  -0.1139   0.4377   0.7105
   3.500   0.9187   0.01034   0.00409  -0.1135   0.4313   0.7364
   3.750   0.9438   0.01048   0.00425  -0.1129   0.4254   0.7643
   4.000   0.9692   0.01050   0.00440  -0.1123   0.4198   0.7973
   4.250   0.9925   0.01054   0.00454  -0.1112   0.4138   0.8378
   4.500   1.0105   0.01058   0.00468  -0.1090   0.4083   0.8993
   4.750   1.0385   0.01055   0.00476  -0.1089   0.4027   1.0000
   5.000   1.0651   0.01074   0.00490  -0.1087   0.3970   1.0000
   5.250   1.0909   0.01098   0.00509  -0.1084   0.3913   1.0000
   5.500   1.1176   0.01112   0.00525  -0.1082   0.3856   1.0000
   5.750   1.1433   0.01132   0.00543  -0.1078   0.3800   1.0000
   6.000   1.1684   0.01157   0.00564  -0.1074   0.3745   1.0000
   6.250   1.1944   0.01172   0.00582  -0.1071   0.3686   1.0000
   6.500   1.2190   0.01196   0.00602  -0.1066   0.3628   1.0000
   6.750   1.2436   0.01219   0.00625  -0.1060   0.3570   1.0000
   7.000   1.2685   0.01237   0.00646  -0.1056   0.3511   1.0000
   7.250   1.2917   0.01266   0.00669  -0.1048   0.3453   1.0000
   7.500   1.3160   0.01287   0.00694  -0.1042   0.3397   1.0000
   7.750   1.3395   0.01309   0.00718  -0.1035   0.3337   1.0000
   8.000   1.3609   0.01344   0.00747  -0.1025   0.3276   1.0000
   8.250   1.3848   0.01361   0.00772  -0.1019   0.3219   1.0000
   8.500   1.4060   0.01389   0.00799  -0.1008   0.3158   1.0000
   8.750   1.4259   0.01421   0.00830  -0.0995   0.3103   1.0000
   9.000   1.4470   0.01444   0.00859  -0.0983   0.3045   1.0000
   9.250   1.4650   0.01479   0.00892  -0.0967   0.2985   1.0000
   9.500   1.4845   0.01509   0.00926  -0.0954   0.2929   1.0000
   9.750   1.5033   0.01541   0.00961  -0.0940   0.2865   1.0000
  10.000   1.5192   0.01586   0.01004  -0.0921   0.2805   1.0000
  10.250   1.5390   0.01615   0.01040  -0.0909   0.2743   1.0000
  10.500   1.5543   0.01661   0.01085  -0.0891   0.2676   1.0000
  10.750   1.5715   0.01702   0.01131  -0.0875   0.2612   1.0000
  11.000   1.5864   0.01753   0.01183  -0.0857   0.2538   1.0000
  11.250   1.6010   0.01806   0.01239  -0.0840   0.2469   1.0000
  11.500   1.6146   0.01865   0.01299  -0.0821   0.2390   1.0000
  11.750   1.6273   0.01931   0.01367  -0.0802   0.2312   1.0000
  12.000   1.6378   0.02009   0.01446  -0.0782   0.2227   1.0000
  12.250   1.6495   0.02086   0.01527  -0.0763   0.2142   1.0000
  12.500   1.6560   0.02194   0.01633  -0.0741   0.2058   1.0000
  12.750   1.6665   0.02286   0.01729  -0.0724   0.1969   1.0000
  13.000   1.6723   0.02411   0.01854  -0.0704   0.1880   1.0000
  13.250   1.6755   0.02560   0.02002  -0.0683   0.1782   1.0000
  13.500   1.6798   0.02710   0.02155  -0.0665   0.1682   1.0000
  13.750   1.6809   0.02893   0.02337  -0.0647   0.1588   1.0000
  14.000   1.6783   0.03117   0.02560  -0.0630   0.1496   1.0000
  14.250   1.6792   0.03325   0.02770  -0.0617   0.1409   1.0000
  14.500   1.6763   0.03576   0.03023  -0.0604   0.1334   1.0000
  14.750   1.6733   0.03842   0.03293  -0.0595   0.1264   1.0000
  15.000   1.6695   0.04129   0.03583  -0.0587   0.1199   1.0000
  15.250   1.6642   0.04445   0.03902  -0.0581   0.1135   1.0000
  15.500   1.6586   0.04777   0.04240  -0.0578   0.1082   1.0000
  15.750   1.6534   0.05119   0.04587  -0.0577   0.1026   1.0000
  16.000   1.6432   0.05533   0.05005  -0.0578   0.0978   1.0000
  16.250   1.6396   0.05880   0.05361  -0.0581   0.0933   1.0000
  16.500   1.6293   0.06323   0.05807  -0.0587   0.0887   1.0000
  16.750   1.6216   0.06745   0.06236  -0.0593   0.0850   1.0000
  17.000   1.6148   0.07166   0.06664  -0.0602   0.0809   1.0000
  17.250   1.6027   0.07671   0.07175  -0.0613   0.0773   1.0000
  17.500   1.5952   0.08123   0.07635  -0.0625   0.0739   1.0000
  17.750   1.5881   0.08576   0.08096  -0.0637   0.0706   1.0000
  18.000   1.5769   0.09102   0.08626  -0.0654   0.0675   1.0000
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