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=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1098 AIRFOIL (e1098-il)
Reynolds number: 50,000
Max Cl/Cd: 14.13 at α=13.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1098-il-50000-n5.txt
Download as CSV file: xf-e1098-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2914   0.11606   0.10961  -0.0857   0.9521   0.0444
 -12.750  -0.2864   0.10958   0.10311  -0.0907   0.9449   0.0440
 -12.500  -0.2872   0.10242   0.09590  -0.0962   0.9375   0.0436
 -12.250  -0.2941   0.09449   0.08789  -0.1026   0.9309   0.0432
 -12.000  -0.3067   0.08669   0.07997  -0.1090   0.9238   0.0427
 -11.750  -0.3218   0.07955   0.07265  -0.1152   0.9162   0.0423
 -11.500  -0.3359   0.07354   0.06641  -0.1201   0.9081   0.0419
 -11.250  -0.3504   0.06822   0.06081  -0.1242   0.8999   0.0420
 -11.000  -0.3611   0.06416   0.05648  -0.1265   0.8909   0.0418
 -10.750  -0.3694   0.06048   0.05247  -0.1283   0.8833   0.0422
 -10.500  -0.3787   0.05778   0.04948  -0.1282   0.8745   0.0425
 -10.250  -0.3835   0.05516   0.04650  -0.1281   0.8677   0.0432
 -10.000  -0.3906   0.05341   0.04446  -0.1262   0.8596   0.0437
  -9.750  -0.3931   0.05157   0.04221  -0.1246   0.8534   0.0446
  -9.500  -0.3768   0.04946   0.04006  -0.1243   0.8487   0.0463
  -9.250  -0.3629   0.04791   0.03835  -0.1233   0.8432   0.0476
  -9.000  -0.3328   0.04602   0.03621  -0.1236   0.8398   0.0495
  -8.750  -0.2830   0.04434   0.03418  -0.1247   0.8380   0.0530
  -8.500  -0.2437   0.04336   0.03307  -0.1248   0.8360   0.0585
  -8.250  -0.2276   0.04300   0.03267  -0.1228   0.8312   0.0626
  -8.000  -0.2075   0.04259   0.03206  -0.1210   0.8274   0.0675
  -7.750  -0.1970   0.04180   0.03139  -0.1193   0.8236   0.0739
  -7.500  -0.1850   0.04099   0.03051  -0.1177   0.8204   0.0818
  -7.250  -0.1931   0.04073   0.03032  -0.1139   0.8143   0.0863
  -7.000  -0.1958   0.04013   0.02972  -0.1107   0.8097   0.0951
  -6.750  -0.2005   0.03923   0.02888  -0.1078   0.8061   0.1062
  -6.500  -0.2190   0.03910   0.02885  -0.1028   0.8008   0.1128
  -6.250  -0.2341   0.03864   0.02851  -0.0983   0.7960   0.1255
  -6.000  -0.2451   0.03738   0.02756  -0.0949   0.7923   0.1579
  -5.750  -0.2597   0.03611   0.02678  -0.0912   0.7883   0.2181
  -5.500  -0.2806   0.03588   0.02729  -0.0851   0.7828   0.3014
  -5.250  -0.2709   0.03821   0.03027  -0.0790   0.7799   0.4672
  -5.000  -0.2594   0.03930   0.03109  -0.0766   0.7773   0.5210
  -4.750  -0.2397   0.04243   0.03409  -0.0710   0.7754   0.5733
  -4.500  -0.2474   0.04397   0.03561  -0.0643   0.7709   0.5924
  -4.250  -0.2487   0.04521   0.03678  -0.0586   0.7670   0.6086
  -4.000  -0.2400   0.04582   0.03721  -0.0554   0.7643   0.6231
  -3.750  -0.2222   0.04635   0.03755  -0.0531   0.7623   0.6321
  -3.500  -0.2020   0.04629   0.03725  -0.0524   0.7603   0.6416
  -3.250  -0.1976   0.04649   0.03729  -0.0497   0.7570   0.6495
  -3.000  -0.1990   0.04667   0.03737  -0.0466   0.7533   0.6565
  -2.750  -0.1873   0.04685   0.03740  -0.0449   0.7505   0.6627
  -2.500  -0.1686   0.04668   0.03700  -0.0452   0.7479   0.6701
  -2.250  -0.1465   0.04677   0.03692  -0.0446   0.7458   0.6746
  -2.000  -0.1209   0.04671   0.03664  -0.0453   0.7440   0.6803
  -1.750  -0.1180   0.04700   0.03682  -0.0437   0.7402   0.6858
  -1.500  -0.1071   0.04731   0.03704  -0.0420   0.7367   0.6895
  -1.250  -0.0878   0.04747   0.03705  -0.0419   0.7338   0.6938
  -1.000  -0.0625   0.04754   0.03692  -0.0432   0.7314   0.6987
  -0.750  -0.0348   0.04764   0.03687  -0.0441   0.7293   0.7022
  -0.500  -0.0237   0.04807   0.03723  -0.0429   0.7257   0.7055
  -0.250  -0.0111   0.04848   0.03756  -0.0421   0.7217   0.7092
   0.000   0.0119   0.04877   0.03771  -0.0429   0.7184   0.7130
   0.250   0.0393   0.04901   0.03782  -0.0442   0.7157   0.7165
   0.500   0.0679   0.04925   0.03797  -0.0449   0.7134   0.7195
   0.750   0.0730   0.04993   0.03861  -0.0433   0.7082   0.7227
   1.000   0.0928   0.05040   0.03901  -0.0436   0.7041   0.7260
   1.250   0.1210   0.05078   0.03928  -0.0450   0.7009   0.7296
   1.500   0.1520   0.05112   0.03954  -0.0464   0.6984   0.7329
   1.750   0.1575   0.05191   0.04033  -0.0448   0.6924   0.7360
   2.000   0.1785   0.05246   0.04084  -0.0450   0.6880   0.7395
   2.250   0.2082   0.05291   0.04122  -0.0464   0.6847   0.7429
   2.500   0.2310   0.05356   0.04182  -0.0472   0.6803   0.7467
   2.750   0.2422   0.05432   0.04260  -0.0462   0.6742   0.7499
   3.000   0.2686   0.05482   0.04308  -0.0468   0.6703   0.7538
   3.250   0.3027   0.05522   0.04345  -0.0484   0.6674   0.7581
   3.500   0.3066   0.05634   0.04459  -0.0473   0.6591   0.7622
   3.750   0.3333   0.05681   0.04508  -0.0478   0.6548   0.7657
   4.250   0.3691   0.05838   0.04670  -0.0478   0.6425   0.7748
   4.500   0.3996   0.05881   0.04715  -0.0487   0.6386   0.7797
   5.000   0.4344   0.06040   0.04885  -0.0484   0.6252   0.7903
   5.250   0.4551   0.06110   0.04961  -0.0485   0.6193   0.7957
   5.500   0.4706   0.06192   0.05050  -0.0481   0.6116   0.8014
   5.750   0.5040   0.06221   0.05087  -0.0492   0.6077   0.8085
   6.000   0.5079   0.06339   0.05215  -0.0478   0.5976   0.8150
   6.250   0.5398   0.06361   0.05245  -0.0486   0.5933   0.8237
   6.500   0.5449   0.06476   0.05372  -0.0473   0.5830   0.8318
   6.750   0.5754   0.06487   0.05396  -0.0477   0.5785   0.8422
   7.000   0.5818   0.06604   0.05525  -0.0467   0.5679   0.8531
   7.250   0.6124   0.06594   0.05529  -0.0469   0.5636   0.8675
   7.500   0.6176   0.06709   0.05659  -0.0457   0.5524   0.8850
   8.000   0.6601   0.06780   0.05763  -0.0463   0.5362   1.0000
   8.250   0.6747   0.06919   0.05908  -0.0470   0.5253   1.0000
   8.500   0.7121   0.06912   0.05910  -0.0487   0.5204   1.0000
   8.750   0.7229   0.07066   0.06070  -0.0489   0.5085   1.0000
   9.000   0.7371   0.07198   0.06210  -0.0492   0.4977   1.0000
   9.250   0.7713   0.07176   0.06196  -0.0501   0.4923   1.0000
   9.500   0.7816   0.07332   0.06362  -0.0501   0.4802   1.0000
   9.750   0.7953   0.07462   0.06501  -0.0501   0.4693   1.0000
  10.000   0.8280   0.07420   0.06470  -0.0505   0.4635   1.0000
  10.250   0.8375   0.07584   0.06644  -0.0503   0.4513   1.0000
  10.500   0.8515   0.07708   0.06779  -0.0502   0.4403   1.0000
  10.750   0.8833   0.07641   0.06728  -0.0502   0.4342   1.0000
  11.000   0.8930   0.07803   0.06901  -0.0499   0.4217   1.0000
  11.500   0.9400   0.07792   0.06918  -0.0492   0.4044   1.0000
  11.750   0.9500   0.07946   0.07086  -0.0489   0.3919   1.0000
  12.000   0.9649   0.08035   0.07189  -0.0484   0.3804   1.0000
  12.250   1.0022   0.07816   0.06987  -0.0477   0.3741   1.0000
  12.750   1.0275   0.08042   0.07239  -0.0467   0.3485   1.0000
  13.000   1.0475   0.08053   0.07266  -0.0461   0.3368   1.0000
  13.250   1.0798   0.07886   0.07112  -0.0452   0.3264   1.0000
  13.500   1.1049   0.07821   0.07057  -0.0444   0.3137   1.0000
  13.750   1.1182   0.07925   0.07170  -0.0438   0.2995   1.0000
  14.000   1.1319   0.08022   0.07278  -0.0432   0.2848   1.0000
  14.250   1.1433   0.08156   0.07419  -0.0428   0.2703   1.0000
  14.500   1.1532   0.08310   0.07578  -0.0423   0.2557   1.0000
  14.750   1.1608   0.08499   0.07774  -0.0420   0.2412   1.0000
  15.000   1.1658   0.08730   0.08010  -0.0418   0.2271   1.0000
  15.250   1.1691   0.08989   0.08274  -0.0418   0.2132   1.0000
  15.500   1.1709   0.09275   0.08567  -0.0419   0.2000   1.0000
  15.750   1.1716   0.09582   0.08880  -0.0422   0.1872   1.0000
  16.000   1.1719   0.09897   0.09200  -0.0426   0.1749   1.0000
  16.250   1.1722   0.10213   0.09519  -0.0431   0.1630   1.0000
  16.500   1.1731   0.10522   0.09830  -0.0437   0.1516   1.0000
  16.750   1.1726   0.10856   0.10165  -0.0445   0.1405   1.0000
  17.000   1.1660   0.11322   0.10647  -0.0459   0.1306   1.0000
  17.250   1.1628   0.11725   0.11056  -0.0472   0.1211   1.0000
  17.500   1.1626   0.12066   0.11392  -0.0484   0.1116   1.0000
  17.750   1.1573   0.12525   0.11861  -0.0502   0.1028   1.0000
  18.000   1.1511   0.13013   0.12360  -0.0523   0.0949   1.0000
  18.250   1.1509   0.13365   0.12701  -0.0539   0.0868   1.0000
  18.500   1.1416   0.13947   0.13306  -0.0567   0.0802   1.0000
  18.750   1.1398   0.14354   0.13708  -0.0588   0.0736   1.0000
  19.000   1.1311   0.14943   0.14316  -0.0620   0.0682   1.0000
  19.250   1.1313   0.15317   0.14682  -0.0640   0.0627   1.0000
<< Back to EPPLER 1098 AIRFOIL (e1098-il)

Polar data table (+)

Polar graphs


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