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

EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1098 AIRFOIL (e1098-il)
Reynolds number: 500,000
Max Cl/Cd: 112.47 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1098-il-500000-n5.txt
Download as CSV file: xf-e1098-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1098 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
  ------ -------- --------- --------- -------- -------- --------
 -16.500  -0.4326   0.09710   0.09333  -0.1021   0.7813   0.0069
 -16.250  -0.4722   0.08510   0.08112  -0.1087   0.7776   0.0068
 -16.000  -0.4949   0.07723   0.07304  -0.1132   0.7714   0.0068
 -15.750  -0.5051   0.07195   0.06759  -0.1162   0.7639   0.0068
 -15.500  -0.5241   0.06578   0.06121  -0.1193   0.7579   0.0068
 -15.250  -0.5343   0.06121   0.05648  -0.1215   0.7515   0.0068
 -15.000  -0.5452   0.05688   0.05196  -0.1232   0.7454   0.0068
 -14.750  -0.5499   0.05348   0.04837  -0.1245   0.7395   0.0069
 -14.500  -0.5519   0.05061   0.04534  -0.1254   0.7338   0.0070
 -14.250  -0.5534   0.04793   0.04250  -0.1261   0.7282   0.0070
 -14.000  -0.5564   0.04513   0.03954  -0.1265   0.7234   0.0070
 -13.750  -0.5572   0.04271   0.03697  -0.1267   0.7185   0.0071
 -13.500  -0.5584   0.04039   0.03452  -0.1266   0.7142   0.0073
 -13.250  -0.5560   0.03837   0.03235  -0.1264   0.7104   0.0072
 -13.000  -0.5494   0.03687   0.03081  -0.1264   0.7064   0.0075
 -12.750  -0.5439   0.03523   0.02905  -0.1260   0.7027   0.0075
 -12.500  -0.5354   0.03395   0.02769  -0.1258   0.6992   0.0077
 -12.250  -0.5262   0.03271   0.02639  -0.1255   0.6962   0.0079
 -12.000  -0.5160   0.03155   0.02516  -0.1252   0.6930   0.0081
 -11.750  -0.5068   0.03028   0.02379  -0.1246   0.6900   0.0081
 -11.500  -0.4966   0.02913   0.02255  -0.1239   0.6871   0.0083
 -11.250  -0.4855   0.02809   0.02142  -0.1233   0.6844   0.0086
 -11.000  -0.4744   0.02706   0.02030  -0.1225   0.6820   0.0087
 -10.750  -0.4631   0.02602   0.01920  -0.1218   0.6797   0.0088
 -10.500  -0.4511   0.02507   0.01817  -0.1210   0.6773   0.0091
 -10.250  -0.4401   0.02408   0.01711  -0.1200   0.6749   0.0092
 -10.000  -0.4284   0.02317   0.01613  -0.1191   0.6724   0.0093
  -9.750  -0.4169   0.02227   0.01515  -0.1181   0.6702   0.0095
  -9.500  -0.4052   0.02143   0.01423  -0.1171   0.6681   0.0097
  -9.250  -0.3970   0.02039   0.01315  -0.1158   0.6662   0.0100
  -9.000  -0.3880   0.01946   0.01219  -0.1144   0.6644   0.0102
  -8.750  -0.3801   0.01867   0.01137  -0.1127   0.6625   0.0104
  -8.500  -0.3718   0.01802   0.01068  -0.1109   0.6606   0.0107
  -8.250  -0.3567   0.01745   0.01005  -0.1099   0.6589   0.0110
  -8.000  -0.3394   0.01694   0.00949  -0.1091   0.6573   0.0114
  -7.750  -0.3207   0.01645   0.00894  -0.1084   0.6557   0.0119
  -7.500  -0.3006   0.01601   0.00843  -0.1078   0.6543   0.0125
  -7.250  -0.2794   0.01560   0.00796  -0.1074   0.6529   0.0133
  -7.000  -0.2577   0.01516   0.00750  -0.1070   0.6516   0.0143
  -6.750  -0.2344   0.01479   0.00711  -0.1069   0.6503   0.0154
  -6.500  -0.2104   0.01444   0.00671  -0.1067   0.6490   0.0167
  -6.250  -0.1865   0.01405   0.00631  -0.1066   0.6476   0.0186
  -6.000  -0.1614   0.01375   0.00597  -0.1067   0.6461   0.0213
  -5.750  -0.1363   0.01342   0.00563  -0.1067   0.6447   0.0252
  -5.500  -0.1107   0.01311   0.00532  -0.1068   0.6433   0.0319
  -5.250  -0.0853   0.01273   0.00500  -0.1070   0.6420   0.0482
  -5.000  -0.0602   0.01226   0.00466  -0.1072   0.6409   0.0829
  -4.750  -0.0354   0.01167   0.00428  -0.1075   0.6398   0.1416
  -4.500  -0.0118   0.01074   0.00377  -0.1080   0.6387   0.2537
  -4.250   0.0120   0.00963   0.00328  -0.1088   0.6376   0.4187
  -4.000   0.0407   0.00956   0.00333  -0.1092   0.6367   0.4716
  -3.750   0.0700   0.00960   0.00336  -0.1097   0.6357   0.4946
  -3.500   0.0994   0.00971   0.00345  -0.1101   0.6347   0.5145
  -3.250   0.1287   0.00981   0.00353  -0.1105   0.6337   0.5259
  -3.000   0.1579   0.00984   0.00352  -0.1109   0.6326   0.5312
  -2.750   0.1872   0.00987   0.00353  -0.1113   0.6316   0.5349
  -2.500   0.2164   0.00989   0.00351  -0.1118   0.6304   0.5380
  -2.250   0.2458   0.00991   0.00347  -0.1123   0.6292   0.5406
  -2.000   0.2751   0.00992   0.00343  -0.1128   0.6281   0.5425
  -1.750   0.3045   0.00994   0.00339  -0.1133   0.6271   0.5441
  -1.500   0.3337   0.00993   0.00337  -0.1138   0.6262   0.5456
  -1.250   0.3629   0.00994   0.00336  -0.1142   0.6252   0.5469
  -1.000   0.3922   0.00996   0.00336  -0.1147   0.6244   0.5482
  -0.750   0.4216   0.01000   0.00337  -0.1152   0.6235   0.5497
  -0.500   0.4511   0.01005   0.00339  -0.1158   0.6226   0.5514
  -0.250   0.4803   0.01009   0.00342  -0.1163   0.6217   0.5529
   0.000   0.5092   0.01011   0.00345  -0.1167   0.6207   0.5544
   0.250   0.5381   0.01014   0.00348  -0.1172   0.6196   0.5559
   0.500   0.5670   0.01018   0.00352  -0.1176   0.6186   0.5573
   0.750   0.5960   0.01023   0.00357  -0.1181   0.6176   0.5587
   1.000   0.6248   0.01027   0.00362  -0.1185   0.6165   0.5602
   1.250   0.6535   0.01030   0.00368  -0.1189   0.6152   0.5618
   1.500   0.6823   0.01034   0.00375  -0.1194   0.6140   0.5634
   1.750   0.7110   0.01038   0.00381  -0.1198   0.6128   0.5649
   2.000   0.7398   0.01042   0.00387  -0.1202   0.6114   0.5665
   2.250   0.7686   0.01046   0.00392  -0.1206   0.6100   0.5682
   2.500   0.7975   0.01052   0.00398  -0.1211   0.6085   0.5699
   2.750   0.8263   0.01059   0.00406  -0.1215   0.6067   0.5716
   3.000   0.8536   0.01062   0.00415  -0.1217   0.6046   0.5734
   3.250   0.8810   0.01065   0.00422  -0.1218   0.6019   0.5750
   3.500   0.9083   0.01065   0.00427  -0.1220   0.5988   0.5768
   3.750   0.9358   0.01063   0.00429  -0.1221   0.5954   0.5787
   4.000   0.9641   0.01067   0.00431  -0.1224   0.5923   0.5809
   4.250   0.9900   0.01069   0.00443  -0.1223   0.5888   0.5831
   4.500   1.0167   0.01072   0.00453  -0.1223   0.5855   0.5853
   4.750   1.0436   0.01076   0.00461  -0.1224   0.5824   0.5876
   5.000   1.0708   0.01080   0.00468  -0.1225   0.5794   0.5898
   5.250   1.0976   0.01085   0.00478  -0.1226   0.5764   0.5919
   5.500   1.1233   0.01090   0.00494  -0.1224   0.5725   0.5941
   5.750   1.1491   0.01094   0.00507  -0.1223   0.5682   0.5966
   6.000   1.1748   0.01098   0.00515  -0.1221   0.5640   0.5993
   6.250   1.1998   0.01105   0.00530  -0.1218   0.5586   0.6021
   6.500   1.2234   0.01110   0.00540  -0.1213   0.5508   0.6050
   6.750   1.2456   0.01116   0.00553  -0.1204   0.5394   0.6080
   7.000   1.2653   0.01125   0.00564  -0.1191   0.5233   0.6113
   7.250   1.2804   0.01145   0.00581  -0.1169   0.5006   0.6148
   7.500   1.2852   0.01184   0.00609  -0.1128   0.4731   0.6183
   7.750   1.2829   0.01249   0.00661  -0.1075   0.4455   0.6216
   8.000   1.2795   0.01334   0.00735  -0.1024   0.4186   0.6249
   8.250   1.2768   0.01428   0.00823  -0.0978   0.3941   0.6286
   8.500   1.2725   0.01541   0.00929  -0.0933   0.3719   0.6327
   8.750   1.2704   0.01662   0.01045  -0.0895   0.3517   0.6368
   9.000   1.2673   0.01804   0.01183  -0.0860   0.3321   0.6410
   9.250   1.2654   0.01956   0.01333  -0.0828   0.3144   0.6457
   9.500   1.2608   0.02139   0.01509  -0.0797   0.2928   0.6507
   9.750   1.2611   0.02302   0.01670  -0.0773   0.2765   0.6558
  10.000   1.2565   0.02505   0.01865  -0.0746   0.2552   0.6615
  10.500   1.2580   0.02858   0.02213  -0.0705   0.2215   0.6747
  10.750   1.2572   0.03053   0.02402  -0.0685   0.2012   0.6819
  11.000   1.2560   0.03257   0.02597  -0.0666   0.1807   0.6894
  11.250   1.2570   0.03451   0.02785  -0.0650   0.1602   0.6980
  11.500   1.2605   0.03632   0.02963  -0.0636   0.1442   0.7072
  11.750   1.2659   0.03802   0.03132  -0.0625   0.1306   0.7175
  12.000   1.2689   0.03997   0.03323  -0.0612   0.1149   0.7291
  12.250   1.2724   0.04190   0.03513  -0.0601   0.0996   0.7424
  12.500   1.2769   0.04380   0.03704  -0.0591   0.0866   0.7581
  13.000   1.2865   0.04755   0.04085  -0.0572   0.0639   0.8052
  13.250   1.2912   0.04915   0.04261  -0.0558   0.0555   0.8669
  13.750   1.3022   0.05329   0.04678  -0.0550   0.0363   1.0000
  14.000   1.3084   0.05535   0.04882  -0.0546   0.0298   1.0000
  14.250   1.3123   0.05770   0.05116  -0.0541   0.0231   1.0000
  14.500   1.3174   0.05996   0.05343  -0.0537   0.0182   1.0000
  14.750   1.3217   0.06236   0.05584  -0.0534   0.0138   1.0000
  15.000   1.3264   0.06477   0.05827  -0.0532   0.0107   1.0000
  15.250   1.3293   0.06742   0.06095  -0.0530   0.0078   1.0000
  15.500   1.3348   0.06983   0.06341  -0.0530   0.0070   1.0000
  15.750   1.3403   0.07226   0.06590  -0.0530   0.0063   1.0000
  16.000   1.3440   0.07498   0.06868  -0.0530   0.0057   1.0000
  16.250   1.3480   0.07769   0.07146  -0.0532   0.0053   1.0000
  16.500   1.3524   0.08041   0.07427  -0.0534   0.0051   1.0000
  16.750   1.3567   0.08316   0.07710  -0.0537   0.0049   1.0000
  17.000   1.3590   0.08624   0.08028  -0.0541   0.0046   1.0000
  17.250   1.3619   0.08925   0.08338  -0.0546   0.0044   1.0000
  17.500   1.3636   0.09250   0.08671  -0.0552   0.0043   1.0000
  17.750   1.3644   0.09592   0.09023  -0.0559   0.0041   1.0000
  18.000   1.3644   0.09951   0.09391  -0.0567   0.0040   1.0000
  18.250   1.3627   0.10338   0.09787  -0.0577   0.0038   1.0000
  18.500   1.3611   0.10728   0.10188  -0.0588   0.0038   1.0000
<< Back to EPPLER 1098 AIRFOIL (e1098-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 1098 AIRFOIL (e1098-il)