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=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1098 AIRFOIL (e1098-il)
Reynolds number: 200,000
Max Cl/Cd: 51.93 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1098-il-200000.txt
Download as CSV file: xf-e1098-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.1476   0.11398   0.10991  -0.1079   0.8537   0.0616
 -13.000  -0.1505   0.10935   0.10524  -0.1109   0.8449   0.0651
 -12.750  -0.2038   0.09765   0.09358  -0.1223   0.8392   0.0675
 -12.500  -0.1735   0.09687   0.09276  -0.1184   0.8325   0.0693
 -12.250  -0.1560   0.09579   0.09160  -0.1174   0.8256   0.0710
 -12.000  -0.1503   0.09281   0.08855  -0.1184   0.8205   0.0732
 -11.750  -0.1554   0.08814   0.08390  -0.1208   0.8153   0.0756
 -10.000  -0.4326   0.04227   0.03589  -0.1268   0.7846   0.0363
  -9.750  -0.4115   0.03914   0.03266  -0.1266   0.7813   0.0340
  -9.500  -0.4025   0.03626   0.02950  -0.1254   0.7783   0.0328
  -9.250  -0.3892   0.03373   0.02664  -0.1242   0.7758   0.0320
  -9.000  -0.3719   0.03162   0.02424  -0.1233   0.7734   0.0315
  -8.750  -0.3514   0.02989   0.02231  -0.1227   0.7706   0.0316
  -8.500  -0.3282   0.02845   0.02072  -0.1222   0.7679   0.0320
  -8.250  -0.3053   0.02741   0.01954  -0.1217   0.7655   0.0332
  -8.000  -0.2832   0.02664   0.01861  -0.1211   0.7632   0.0347
  -7.750  -0.2581   0.02570   0.01755  -0.1207   0.7613   0.0357
  -7.500  -0.2306   0.02423   0.01614  -0.1203   0.7596   0.0373
  -7.250  -0.2145   0.02352   0.01549  -0.1190   0.7573   0.0389
  -7.000  -0.2006   0.02291   0.01489  -0.1174   0.7546   0.0409
  -6.750  -0.1866   0.02234   0.01428  -0.1160   0.7522   0.0434
  -6.500  -0.1766   0.02151   0.01346  -0.1142   0.7500   0.0472
  -6.250  -0.1612   0.02093   0.01286  -0.1132   0.7481   0.0540
  -6.000  -0.1476   0.02008   0.01201  -0.1120   0.7464   0.0653
  -5.750  -0.1388   0.01856   0.01092  -0.1107   0.7448   0.1351
  -5.500  -0.1360   0.01661   0.01063  -0.1093   0.7431   0.4638
  -5.250  -0.1110   0.01739   0.01135  -0.1087   0.7412   0.5158
  -5.000  -0.0858   0.01823   0.01218  -0.1078   0.7391   0.5385
  -4.750  -0.0602   0.01895   0.01286  -0.1070   0.7369   0.5534
  -4.500  -0.0343   0.01979   0.01369  -0.1060   0.7351   0.5679
  -4.250  -0.0089   0.02109   0.01506  -0.1041   0.7336   0.5854
  -4.000   0.0163   0.02223   0.01625  -0.1022   0.7322   0.5982
  -3.750   0.0421   0.02254   0.01643  -0.1019   0.7309   0.6084
  -3.500   0.0682   0.02302   0.01690  -0.1010   0.7298   0.6126
  -3.250   0.0949   0.02315   0.01692  -0.1012   0.7287   0.6186
  -3.000   0.1151   0.02325   0.01697  -0.1009   0.7265   0.6240
  -2.750   0.1339   0.02367   0.01741  -0.0996   0.7241   0.6267
  -2.500   0.1544   0.02399   0.01772  -0.0989   0.7221   0.6300
  -2.250   0.1770   0.02414   0.01779  -0.0990   0.7203   0.6344
  -2.000   0.2024   0.02410   0.01764  -0.0998   0.7185   0.6387
  -1.750   0.2279   0.02419   0.01769  -0.0996   0.7169   0.6408
  -1.500   0.2548   0.02427   0.01773  -0.0998   0.7156   0.6431
  -1.250   0.2826   0.02435   0.01774  -0.1002   0.7146   0.6457
  -1.000   0.3111   0.02442   0.01773  -0.1010   0.7135   0.6488
  -0.750   0.3075   0.02575   0.01913  -0.0979   0.7084   0.6519
  -0.500   0.3165   0.02660   0.01997  -0.0963   0.7048   0.6545
  -0.250   0.3388   0.02685   0.02021  -0.0959   0.7026   0.6562
   0.000   0.3655   0.02699   0.02032  -0.0962   0.7010   0.6580
   0.250   0.3959   0.02701   0.02030  -0.0969   0.6999   0.6603
   0.500   0.4301   0.02688   0.02013  -0.0983   0.6989   0.6627
   0.750   0.4656   0.02676   0.01993  -0.0999   0.6981   0.6649
   1.000   0.4040   0.03065   0.02396  -0.0893   0.6858   0.6672
   1.250   0.3469   0.03446   0.02778  -0.0799   0.6738   0.6695
   1.500   0.3768   0.03444   0.02777  -0.0803   0.6716   0.6714
   1.750   0.4120   0.03423   0.02755  -0.0815   0.6703   0.6733
   2.000   0.4516   0.03381   0.02712  -0.0832   0.6695   0.6753
   2.250   0.4932   0.03333   0.02662  -0.0851   0.6688   0.6776
   2.500   0.5382   0.03276   0.02604  -0.0877   0.6684   0.6800
   2.750   0.5846   0.03226   0.02551  -0.0906   0.6679   0.6830
   3.000   0.6296   0.03174   0.02499  -0.0932   0.6675   0.6857
   3.250   0.5110   0.03839   0.03170  -0.0769   0.6418   0.6872
   3.500   0.5478   0.03800   0.03135  -0.0779   0.6402   0.6896
   3.750   0.5874   0.03749   0.03086  -0.0794   0.6392   0.6922
   4.000   0.6107   0.03784   0.03122  -0.0792   0.6352   0.6950
   4.250   0.6630   0.03662   0.03002  -0.0820   0.6362   0.6983
   4.500   0.7130   0.03541   0.02883  -0.0845   0.6367   0.7012
   4.750   0.7630   0.03409   0.02760  -0.0869   0.6368   0.7043
   5.000   0.8175   0.03277   0.02633  -0.0903   0.6370   0.7079
   5.250   0.7717   0.03627   0.02987  -0.0821   0.6212   0.7112
   5.500   0.8220   0.03484   0.02846  -0.0845   0.6213   0.7153
   5.750   0.8730   0.03333   0.02705  -0.0869   0.6214   0.7186
   6.000   0.9294   0.03173   0.02554  -0.0904   0.6216   0.7227
   6.250   0.9919   0.03023   0.02411  -0.0952   0.6220   0.7275
   6.500   0.8808   0.03670   0.03058  -0.0794   0.5947   0.7311
   6.750   0.9260   0.03518   0.02919  -0.0807   0.5945   0.7355
   7.000   0.9735   0.03358   0.02770  -0.0824   0.5946   0.7414
   7.250   1.0250   0.03188   0.02610  -0.0848   0.5946   0.7478
   7.500   1.0797   0.03007   0.02442  -0.0877   0.5944   0.7537
   7.750   1.1431   0.02809   0.02255  -0.0921   0.5941   0.7611
   8.000   1.1799   0.02709   0.02168  -0.0929   0.5901   0.7677
   8.250   1.1800   0.02739   0.02208  -0.0888   0.5812   0.7762
   8.500   1.2584   0.02449   0.01932  -0.0951   0.5794   0.7847
   8.750   1.2337   0.02563   0.02058  -0.0875   0.5683   0.7953
   9.250   1.2711   0.02464   0.01986  -0.0842   0.5526   0.8225
   9.500   1.2621   0.02557   0.02095  -0.0797   0.5408   0.8411
   9.750   1.2664   0.02588   0.02143  -0.0766   0.5292   0.8703
  10.000   1.2676   0.02638   0.02213  -0.0737   0.5145   1.0000
  10.250   1.2890   0.02651   0.02227  -0.0736   0.4980   1.0000
  10.500   1.3216   0.02575   0.02144  -0.0739   0.4789   1.0000
  10.750   1.3418   0.02584   0.02140  -0.0731   0.4541   1.0000
  11.000   1.3543   0.02648   0.02185  -0.0716   0.4266   1.0000
  11.250   1.3578   0.02782   0.02299  -0.0694   0.4000   1.0000
  11.500   1.3553   0.02964   0.02464  -0.0669   0.3743   1.0000
  11.750   1.3508   0.03173   0.02662  -0.0646   0.3501   1.0000
  12.000   1.3466   0.03386   0.02861  -0.0624   0.3282   1.0000
  12.250   1.3425   0.03615   0.03082  -0.0604   0.3064   1.0000
  12.500   1.3391   0.03846   0.03303  -0.0587   0.2863   1.0000
  12.750   1.3357   0.04088   0.03535  -0.0571   0.2665   1.0000
  13.000   1.3324   0.04342   0.03781  -0.0557   0.2460   1.0000
  13.250   1.3289   0.04607   0.04036  -0.0545   0.2267   1.0000
  13.500   1.3261   0.04875   0.04296  -0.0534   0.2073   1.0000
  13.750   1.3237   0.05150   0.04564  -0.0525   0.1874   1.0000
  14.000   1.3213   0.05434   0.04839  -0.0518   0.1695   1.0000
  14.250   1.3196   0.05718   0.05116  -0.0511   0.1537   1.0000
  14.500   1.3203   0.05987   0.05381  -0.0507   0.1394   1.0000
  14.750   1.3202   0.06271   0.05663  -0.0503   0.1263   1.0000
  15.000   1.3213   0.06548   0.05939  -0.0500   0.1143   1.0000
  15.250   1.3216   0.06839   0.06231  -0.0498   0.1023   1.0000
  15.500   1.3218   0.07139   0.06531  -0.0497   0.0908   1.0000
  15.750   1.3202   0.07468   0.06859  -0.0497   0.0787   1.0000
  16.000   1.3154   0.07847   0.07233  -0.0498   0.0654   1.0000
  16.250   1.3079   0.08269   0.07650  -0.0500   0.0507   1.0000
  16.500   1.2960   0.08763   0.08137  -0.0504   0.0384   1.0000
  16.750   1.2854   0.09256   0.08630  -0.0510   0.0317   1.0000
<< Back to EPPLER 1098 AIRFOIL (e1098-il)

Polar data table (+)

Polar graphs


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