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EPPLER 1098 AIRFOIL (e1098-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1098 AIRFOIL (e1098-il)
Reynolds number: 100,000
Max Cl/Cd: 24.89 at α=11.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1098-il-100000-n5.txt
Download as CSV file: xf-e1098-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.3613   0.06911   0.06300  -0.1227   0.8483   0.0218
 -12.500  -0.3748   0.06464   0.05830  -0.1251   0.8390   0.0217
 -12.250  -0.3909   0.06046   0.05384  -0.1269   0.8305   0.0218
 -12.000  -0.4023   0.05687   0.05004  -0.1280   0.8230   0.0219
 -11.500  -0.4150   0.05104   0.04377  -0.1288   0.8096   0.0221
 -11.250  -0.4132   0.04895   0.04157  -0.1289   0.8041   0.0228
 -11.000  -0.4132   0.04689   0.03935  -0.1285   0.7978   0.0232
 -10.750  -0.4102   0.04499   0.03728  -0.1281   0.7927   0.0238
 -10.500  -0.4070   0.04320   0.03529  -0.1275   0.7880   0.0246
 -10.250  -0.4026   0.04124   0.03308  -0.1266   0.7829   0.0250
 -10.000  -0.3944   0.03943   0.03101  -0.1256   0.7788   0.0255
  -9.750  -0.3805   0.03761   0.02891  -0.1248   0.7755   0.0260
  -9.500  -0.3618   0.03597   0.02703  -0.1242   0.7722   0.0266
  -9.250  -0.3394   0.03455   0.02540  -0.1238   0.7687   0.0273
  -9.000  -0.3138   0.03331   0.02401  -0.1234   0.7657   0.0281
  -8.750  -0.2902   0.03222   0.02292  -0.1229   0.7630   0.0293
  -8.500  -0.2718   0.03136   0.02201  -0.1221   0.7604   0.0309
  -8.250  -0.2545   0.03061   0.02118  -0.1212   0.7576   0.0330
  -8.000  -0.2384   0.02996   0.02044  -0.1199   0.7541   0.0352
  -7.750  -0.2278   0.02912   0.01965  -0.1182   0.7509   0.0372
  -7.500  -0.2191   0.02841   0.01891  -0.1163   0.7480   0.0393
  -7.250  -0.2102   0.02774   0.01815  -0.1144   0.7455   0.0416
  -7.000  -0.1994   0.02704   0.01734  -0.1129   0.7434   0.0454
  -6.750  -0.1916   0.02642   0.01676  -0.1110   0.7405   0.0505
  -6.500  -0.1821   0.02579   0.01613  -0.1093   0.7378   0.0580
  -6.250  -0.1723   0.02506   0.01546  -0.1076   0.7352   0.0717
  -6.000  -0.1643   0.02407   0.01469  -0.1060   0.7329   0.1071
  -5.750  -0.1608   0.02245   0.01366  -0.1046   0.7307   0.2107
  -5.500  -0.1532   0.02137   0.01371  -0.1026   0.7289   0.3983
  -5.250  -0.1311   0.02196   0.01435  -0.1014   0.7264   0.4797
  -5.000  -0.1091   0.02274   0.01502  -0.1003   0.7237   0.5191
  -4.750  -0.0858   0.02417   0.01644  -0.0981   0.7215   0.5503
  -4.500  -0.0619   0.02520   0.01741  -0.0962   0.7196   0.5677
  -4.250  -0.0380   0.02557   0.01764  -0.0954   0.7178   0.5786
  -4.000  -0.0129   0.02582   0.01776  -0.0948   0.7163   0.5853
  -3.750   0.0125   0.02571   0.01746  -0.0951   0.7148   0.5925
  -3.500   0.0393   0.02582   0.01744  -0.0948   0.7135   0.5961
  -3.250   0.0593   0.02596   0.01750  -0.0940   0.7110   0.6006
  -3.000   0.0785   0.02591   0.01731  -0.0939   0.7081   0.6068
  -2.750   0.0994   0.02615   0.01750  -0.0930   0.7059   0.6093
  -2.500   0.1218   0.02630   0.01757  -0.0925   0.7040   0.6122
  -2.250   0.1458   0.02636   0.01754  -0.0924   0.7023   0.6157
  -2.000   0.1720   0.02631   0.01735  -0.0930   0.7007   0.6196
  -1.750   0.1999   0.02622   0.01712  -0.0938   0.6993   0.6231
  -1.500   0.2275   0.02624   0.01706  -0.0940   0.6981   0.6252
  -1.250   0.2366   0.02689   0.01775  -0.0918   0.6944   0.6275
  -1.000   0.2508   0.02739   0.01824  -0.0905   0.6913   0.6302
  -0.750   0.2720   0.02763   0.01842  -0.0902   0.6887   0.6333
  -0.500   0.2978   0.02773   0.01841  -0.0907   0.6868   0.6363
  -0.250   0.3246   0.02782   0.01843  -0.0912   0.6852   0.6388
   0.000   0.3512   0.02795   0.01854  -0.0913   0.6839   0.6408
   0.250   0.3802   0.02802   0.01856  -0.0919   0.6827   0.6431
   0.500   0.3600   0.02988   0.02054  -0.0861   0.6746   0.6454
   0.750   0.3826   0.03018   0.02080  -0.0860   0.6721   0.6479
   1.000   0.4109   0.03029   0.02086  -0.0866   0.6704   0.6505
   1.250   0.4418   0.03034   0.02084  -0.0877   0.6691   0.6537
   1.500   0.4714   0.03039   0.02089  -0.0882   0.6679   0.6558
   2.000   0.4625   0.03302   0.02363  -0.0808   0.6551   0.6604
   2.250   0.4950   0.03299   0.02359  -0.0818   0.6539   0.6630
   2.500   0.5293   0.03293   0.02351  -0.0831   0.6528   0.6658
   3.000   0.5271   0.03580   0.02645  -0.0774   0.6391   0.6712
   3.250   0.5600   0.03561   0.02630  -0.0781   0.6380   0.6739
   4.000   0.5747   0.03964   0.03043  -0.0727   0.6171   0.6836
   4.250   0.6388   0.03772   0.02855  -0.0762   0.6221   0.6866
   4.750   0.6551   0.03989   0.03086  -0.0729   0.6083   0.6928
   5.250   0.6793   0.04170   0.03277  -0.0707   0.5947   0.7009
   5.500   0.7124   0.04131   0.03247  -0.0712   0.5931   0.7048
   6.000   0.7399   0.04283   0.03412  -0.0692   0.5793   0.7137
   6.250   0.7750   0.04223   0.03362  -0.0698   0.5777   0.7182
   6.750   0.8050   0.04345   0.03501  -0.0680   0.5635   0.7280
   7.250   0.8121   0.04621   0.03796  -0.0646   0.5420   0.7386
   7.500   0.8383   0.04605   0.03792  -0.0645   0.5373   0.7460
   7.750   0.8708   0.04529   0.03730  -0.0646   0.5349   0.7532
   8.000   0.8738   0.04682   0.03892  -0.0631   0.5229   0.7610
   8.250   0.9060   0.04597   0.03824  -0.0631   0.5204   0.7697
   8.500   0.9103   0.04737   0.03976  -0.0616   0.5082   0.7788
   9.000   0.9471   0.04770   0.04040  -0.0600   0.4933   0.8026
   9.250   0.9564   0.04861   0.04147  -0.0587   0.4822   0.8183
   9.500   0.9845   0.04761   0.04068  -0.0579   0.4780   0.8426
   9.750   0.9924   0.04829   0.04157  -0.0560   0.4663   0.8868
  10.000   1.0087   0.04824   0.04164  -0.0551   0.4560   1.0000
  10.250   1.0427   0.04719   0.04064  -0.0553   0.4485   1.0000
  10.500   1.0634   0.04743   0.04094  -0.0550   0.4353   1.0000
  10.750   1.0875   0.04731   0.04085  -0.0547   0.4219   1.0000
  11.000   1.1132   0.04701   0.04056  -0.0544   0.4075   1.0000
  11.250   1.1382   0.04677   0.04031  -0.0540   0.3915   1.0000
  11.500   1.1613   0.04673   0.04024  -0.0535   0.3743   1.0000
  11.750   1.1782   0.04733   0.04081  -0.0529   0.3561   1.0000
  12.000   1.1916   0.04832   0.04177  -0.0521   0.3375   1.0000
  12.250   1.2039   0.04943   0.04283  -0.0513   0.3193   1.0000
  12.500   1.2147   0.05070   0.04405  -0.0505   0.3013   1.0000
  12.750   1.2240   0.05217   0.04547  -0.0498   0.2843   1.0000
  13.000   1.2308   0.05395   0.04725  -0.0490   0.2675   1.0000
  13.250   1.2363   0.05593   0.04922  -0.0484   0.2511   1.0000
  13.500   1.2406   0.05806   0.05135  -0.0477   0.2349   1.0000
  13.750   1.2440   0.06035   0.05363  -0.0472   0.2190   1.0000
  14.000   1.2464   0.06282   0.05608  -0.0467   0.2035   1.0000
  14.250   1.2479   0.06544   0.05869  -0.0463   0.1883   1.0000
  14.500   1.2491   0.06817   0.06143  -0.0460   0.1740   1.0000
  14.750   1.2499   0.07102   0.06428  -0.0459   0.1604   1.0000
  15.000   1.2503   0.07399   0.06726  -0.0458   0.1477   1.0000
  15.250   1.2497   0.07714   0.07042  -0.0458   0.1358   1.0000
  15.500   1.2481   0.08049   0.07379  -0.0460   0.1242   1.0000
  15.750   1.2448   0.08415   0.07743  -0.0463   0.1126   1.0000
  16.000   1.2410   0.08799   0.08128  -0.0469   0.1011   1.0000
  16.250   1.2377   0.09185   0.08518  -0.0475   0.0900   1.0000
  16.500   1.2340   0.09586   0.08922  -0.0484   0.0798   1.0000
  16.750   1.2297   0.10003   0.09343  -0.0494   0.0706   1.0000
  17.000   1.2240   0.10449   0.09791  -0.0506   0.0626   1.0000
  17.250   1.2195   0.10886   0.10235  -0.0519   0.0552   1.0000
  17.500   1.2147   0.11336   0.10693  -0.0534   0.0486   1.0000
  17.750   1.2067   0.11844   0.11201  -0.0552   0.0436   1.0000
  18.000   1.2024   0.12300   0.11669  -0.0570   0.0385   1.0000
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