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EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1098 AIRFOIL (e1098-il)
Reynolds number: 500,000
Max Cl/Cd: 117.3 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1098-il-500000.txt
Download as CSV file: xf-e1098-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4029   0.05207   0.04767  -0.1330   0.7458   0.0164
 -12.250  -0.4207   0.04807   0.04351  -0.1334   0.7418   0.0160
 -12.000  -0.4366   0.04457   0.03983  -0.1333   0.7377   0.0159
 -11.750  -0.4489   0.04132   0.03640  -0.1327   0.7338   0.0154
 -11.500  -0.4692   0.03697   0.03166  -0.1312   0.7304   0.0145
 -11.250  -0.4829   0.03300   0.02724  -0.1292   0.7272   0.0140
 -11.000  -0.4789   0.03081   0.02481  -0.1279   0.7239   0.0138
 -10.750  -0.4689   0.02929   0.02316  -0.1270   0.7205   0.0139
 -10.500  -0.4568   0.02841   0.02223  -0.1262   0.7175   0.0144
 -10.250  -0.4432   0.02715   0.02081  -0.1253   0.7147   0.0145
 -10.000  -0.4286   0.02608   0.01963  -0.1244   0.7121   0.0149
  -9.750  -0.4126   0.02503   0.01848  -0.1236   0.7097   0.0153
  -9.500  -0.3928   0.02392   0.01725  -0.1229   0.7073   0.0155
  -9.250  -0.3728   0.02293   0.01617  -0.1221   0.7051   0.0159
  -9.000  -0.3534   0.02208   0.01522  -0.1213   0.7029   0.0161
  -8.750  -0.3356   0.02133   0.01438  -0.1203   0.7009   0.0165
  -8.500  -0.3191   0.02069   0.01365  -0.1192   0.6989   0.0168
  -8.250  -0.3045   0.02002   0.01291  -0.1178   0.6971   0.0170
  -8.000  -0.2991   0.01893   0.01182  -0.1152   0.6953   0.0175
  -7.750  -0.2876   0.01813   0.01101  -0.1137   0.6934   0.0181
  -7.500  -0.2723   0.01749   0.01035  -0.1126   0.6916   0.0188
  -7.250  -0.2546   0.01695   0.00977  -0.1118   0.6897   0.0196
  -7.000  -0.2350   0.01646   0.00924  -0.1111   0.6879   0.0207
  -6.750  -0.2131   0.01609   0.00879  -0.1107   0.6863   0.0219
  -6.500  -0.1970   0.01522   0.00788  -0.1098   0.6847   0.0239
  -6.250  -0.1742   0.01481   0.00741  -0.1096   0.6832   0.0262
  -6.000  -0.1519   0.01428   0.00683  -0.1094   0.6819   0.0304
  -5.750  -0.1284   0.01378   0.00635  -0.1092   0.6806   0.0387
  -5.500  -0.1067   0.01301   0.00580  -0.1091   0.6792   0.0815
  -5.250  -0.0885   0.01157   0.00504  -0.1093   0.6779   0.2310
  -5.000  -0.0682   0.01015   0.00446  -0.1097   0.6765   0.4345
  -4.750  -0.0393   0.01018   0.00454  -0.1101   0.6752   0.4840
  -4.500  -0.0100   0.01032   0.00465  -0.1105   0.6739   0.5054
  -4.250   0.0195   0.01050   0.00477  -0.1109   0.6727   0.5203
  -4.000   0.0490   0.01066   0.00484  -0.1113   0.6715   0.5309
  -3.750   0.0785   0.01091   0.00504  -0.1116   0.6703   0.5424
  -3.500   0.1076   0.01124   0.00539  -0.1118   0.6690   0.5549
  -3.250   0.1369   0.01147   0.00556  -0.1121   0.6678   0.5626
  -3.000   0.1658   0.01160   0.00570  -0.1125   0.6668   0.5671
  -2.750   0.1947   0.01166   0.00572  -0.1129   0.6659   0.5708
  -2.500   0.2239   0.01171   0.00571  -0.1134   0.6648   0.5739
  -2.250   0.2528   0.01171   0.00568  -0.1139   0.6638   0.5763
  -2.000   0.2816   0.01170   0.00567  -0.1143   0.6626   0.5783
  -1.750   0.3105   0.01172   0.00569  -0.1147   0.6615   0.5801
  -1.500   0.3395   0.01174   0.00569  -0.1152   0.6602   0.5820
  -1.250   0.3687   0.01176   0.00569  -0.1157   0.6589   0.5839
  -1.000   0.3980   0.01179   0.00568  -0.1162   0.6578   0.5856
  -0.750   0.4274   0.01183   0.00569  -0.1168   0.6568   0.5875
  -0.500   0.4569   0.01188   0.00570  -0.1175   0.6559   0.5893
  -0.250   0.4866   0.01194   0.00571  -0.1181   0.6549   0.5907
   0.000   0.5161   0.01197   0.00572  -0.1187   0.6538   0.5922
   0.250   0.5453   0.01208   0.00582  -0.1193   0.6526   0.5938
   0.500   0.5737   0.01216   0.00594  -0.1197   0.6516   0.5955
   0.750   0.6018   0.01221   0.00602  -0.1200   0.6505   0.5971
   1.000   0.6299   0.01226   0.00611  -0.1204   0.6491   0.5987
   1.250   0.6580   0.01233   0.00620  -0.1207   0.6476   0.6004
   1.500   0.6864   0.01239   0.00628  -0.1211   0.6461   0.6022
   1.750   0.7149   0.01245   0.00635  -0.1216   0.6445   0.6040
   2.000   0.7438   0.01250   0.00639  -0.1221   0.6429   0.6058
   2.250   0.7729   0.01251   0.00641  -0.1226   0.6413   0.6077
   2.500   0.8023   0.01253   0.00646  -0.1231   0.6398   0.6096
   2.750   0.8322   0.01262   0.00654  -0.1238   0.6382   0.6114
   3.000   0.8601   0.01272   0.00669  -0.1241   0.6362   0.6133
   3.250   0.8865   0.01272   0.00676  -0.1241   0.6335   0.6154
   3.500   0.9138   0.01270   0.00678  -0.1242   0.6305   0.6176
   3.750   0.9424   0.01263   0.00672  -0.1246   0.6275   0.6198
   4.000   0.9728   0.01256   0.00662  -0.1252   0.6248   0.6220
   4.250   1.0036   0.01259   0.00665  -0.1260   0.6223   0.6243
   4.500   1.0284   0.01259   0.00677  -0.1257   0.6196   0.6266
   4.750   1.0544   0.01261   0.00687  -0.1256   0.6166   0.6293
   5.000   1.0818   0.01259   0.00692  -0.1258   0.6137   0.6322
   5.250   1.1107   0.01256   0.00691  -0.1262   0.6110   0.6352
   5.500   1.1411   0.01255   0.00688  -0.1269   0.6085   0.6380
   5.750   1.1674   0.01256   0.00700  -0.1269   0.6055   0.6408
   6.000   1.1913   0.01255   0.00711  -0.1264   0.6016   0.6438
   6.250   1.2181   0.01247   0.00710  -0.1264   0.5977   0.6472
   6.500   1.2476   0.01233   0.00695  -0.1268   0.5934   0.6510
   6.750   1.2695   0.01227   0.00700  -0.1259   0.5874   0.6546
   7.000   1.2939   0.01213   0.00695  -0.1253   0.5815   0.6583
   7.250   1.3193   0.01206   0.00693  -0.1250   0.5762   0.6628
   7.500   1.3399   0.01205   0.00704  -0.1239   0.5691   0.6677
   7.750   1.3631   0.01197   0.00702  -0.1231   0.5621   0.6723
   8.000   1.3820   0.01198   0.00717  -0.1217   0.5526   0.6774
   8.250   1.4007   0.01201   0.00728  -0.1201   0.5411   0.6832
   8.500   1.4146   0.01206   0.00738  -0.1177   0.5234   0.6887
   8.750   1.4192   0.01226   0.00755  -0.1134   0.4998   0.6951
   9.000   1.4116   0.01291   0.00806  -0.1072   0.4672   0.7019
   9.250   1.4044   0.01380   0.00886  -0.1016   0.4405   0.7092
   9.500   1.3844   0.01534   0.01023  -0.0945   0.4063   0.7175
   9.750   1.3724   0.01691   0.01174  -0.0894   0.3806   0.7269
  10.000   1.3584   0.01886   0.01361  -0.0846   0.3550   0.7376
  10.250   1.3468   0.02095   0.01565  -0.0806   0.3306   0.7503
  10.500   1.3392   0.02297   0.01765  -0.0773   0.3097   0.7659
  10.750   1.3315   0.02509   0.01977  -0.0742   0.2877   0.7856
  11.000   1.3267   0.02706   0.02177  -0.0715   0.2698   0.8138
  11.250   1.3210   0.02879   0.02363  -0.0683   0.2535   0.8771
  11.500   1.3223   0.03071   0.02558  -0.0670   0.2335   1.0000
  11.750   1.3221   0.03279   0.02757  -0.0653   0.2149   1.0000
  12.000   1.3218   0.03493   0.02961  -0.0638   0.1968   1.0000
  12.250   1.3226   0.03705   0.03164  -0.0624   0.1770   1.0000
  12.500   1.3238   0.03920   0.03368  -0.0611   0.1582   1.0000
  12.750   1.3266   0.04124   0.03565  -0.0600   0.1422   1.0000
  13.250   1.3328   0.04546   0.03971  -0.0581   0.1128   1.0000
  13.500   1.3363   0.04761   0.04180  -0.0573   0.1000   1.0000
  13.750   1.3410   0.04968   0.04382  -0.0566   0.0884   1.0000
  14.000   1.3462   0.05175   0.04588  -0.0560   0.0782   1.0000
  14.250   1.3503   0.05397   0.04806  -0.0554   0.0671   1.0000
  14.500   1.3537   0.05632   0.05036  -0.0549   0.0561   1.0000
  14.750   1.3537   0.05905   0.05301  -0.0543   0.0435   1.0000
  15.000   1.3519   0.06205   0.05592  -0.0538   0.0301   1.0000
  15.250   1.3421   0.06604   0.05979  -0.0531   0.0166   1.0000
  15.500   1.3422   0.06907   0.06285  -0.0529   0.0133   1.0000
  15.750   1.3443   0.07190   0.06574  -0.0528   0.0115   1.0000
  16.000   1.3449   0.07500   0.06890  -0.0528   0.0104   1.0000
  16.250   1.3446   0.07828   0.07226  -0.0529   0.0097   1.0000
  16.500   1.3473   0.08125   0.07533  -0.0531   0.0092   1.0000
  16.750   1.3492   0.08436   0.07853  -0.0535   0.0089   1.0000
  17.000   1.3491   0.08779   0.08206  -0.0539   0.0084   1.0000
  17.250   1.3488   0.09131   0.08566  -0.0545   0.0081   1.0000
  17.500   1.3462   0.09524   0.08968  -0.0553   0.0077   1.0000
  17.750   1.3407   0.09967   0.09421  -0.0562   0.0075   1.0000
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