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E178 (8.69%) (e178-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E178 (8.69%) (e178-il)
Reynolds number: 50,000
Max Cl/Cd: 36.66 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e178-il-50000.txt
Download as CSV file: xf-e178-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E178  (8.69%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4615   0.11958   0.11305  -0.0010   1.0000   0.1796
  -9.250  -0.4489   0.11495   0.10841  -0.0008   1.0000   0.1884
  -9.000  -0.4587   0.11377   0.10734  -0.0038   1.0000   0.1945
  -8.750  -0.4435   0.10901   0.10259  -0.0031   1.0000   0.2065
  -8.500  -0.4346   0.10508   0.09871  -0.0033   1.0000   0.2161
  -8.250  -0.4530   0.10465   0.09845  -0.0068   1.0000   0.2230
  -8.000  -0.4365   0.09995   0.09376  -0.0059   1.0000   0.2360
  -7.750  -0.4238   0.09573   0.08957  -0.0055   1.0000   0.2477
  -7.500  -0.4172   0.09225   0.08616  -0.0056   1.0000   0.2592
  -7.250  -0.4133   0.08912   0.08311  -0.0059   1.0000   0.2718
  -7.000  -0.4097   0.08607   0.08015  -0.0059   1.0000   0.2856
  -6.750  -0.4063   0.08310   0.07726  -0.0056   1.0000   0.3013
  -6.500  -0.4085   0.08068   0.07497  -0.0058   1.0000   0.3193
  -6.000  -0.4076   0.07557   0.07007  -0.0055   1.0000   0.3636
  -5.750  -0.3824   0.07139   0.06590  -0.0004   1.0000   0.3987
  -5.500  -0.3861   0.06954   0.06419   0.0018   1.0000   0.4333
  -4.500  -0.3726   0.04611   0.03930  -0.0360   1.0000   0.1523
  -4.250  -0.3588   0.04218   0.03497  -0.0360   1.0000   0.1413
  -4.000  -0.3428   0.03916   0.03160  -0.0355   1.0000   0.1343
  -3.750  -0.3211   0.03585   0.02732  -0.0354   1.0000   0.1251
  -3.500  -0.3017   0.03333   0.02446  -0.0348   1.0000   0.1236
  -3.250  -0.2802   0.03114   0.02176  -0.0342   1.0000   0.1234
  -3.000  -0.2574   0.02941   0.01945  -0.0334   1.0000   0.1255
  -2.750  -0.2369   0.02799   0.01801  -0.0329   1.0000   0.1356
  -2.500  -0.2145   0.02664   0.01646  -0.0322   1.0000   0.1458
  -2.250  -0.1909   0.02540   0.01504  -0.0315   1.0000   0.1580
  -2.000  -0.1675   0.02423   0.01388  -0.0307   1.0000   0.1916
  -1.750  -0.1418   0.02229   0.01280  -0.0306   1.0000   0.3280
  -1.500  -0.1081   0.01927   0.01177  -0.0296   1.0000   1.0000
  -1.250  -0.0826   0.01974   0.01166  -0.0304   0.9974   1.0000
  -1.000  -0.0409   0.02046   0.01183  -0.0343   0.9877   1.0000
  -0.750  -0.0007   0.02121   0.01214  -0.0379   0.9784   1.0000
  -0.500   0.0418   0.02203   0.01256  -0.0418   0.9693   1.0000
  -0.250   0.0750   0.02269   0.01293  -0.0440   0.9595   1.0000
   0.000   0.1094   0.02343   0.01343  -0.0464   0.9504   1.0000
   0.250   0.1495   0.02426   0.01401  -0.0498   0.9414   1.0000
   0.500   0.1769   0.02496   0.01455  -0.0509   0.9319   1.0000
   0.750   0.2076   0.02574   0.01519  -0.0525   0.9229   1.0000
   1.000   0.2459   0.02662   0.01594  -0.0555   0.9144   1.0000
   1.250   0.2680   0.02737   0.01660  -0.0556   0.9047   1.0000
   1.500   0.2960   0.02823   0.01738  -0.0567   0.8958   1.0000
   1.750   0.3323   0.02914   0.01825  -0.0591   0.8868   1.0000
   2.000   0.3509   0.03001   0.01908  -0.0587   0.8771   1.0000
   2.250   0.3768   0.03095   0.02002  -0.0594   0.8677   1.0000
   2.500   0.4122   0.03192   0.02100  -0.0616   0.8582   1.0000
   2.750   0.4318   0.03289   0.02197  -0.0613   0.8477   1.0000
   3.000   0.4538   0.03391   0.02301  -0.0613   0.8368   1.0000
   3.250   0.4800   0.03494   0.02414  -0.0620   0.8258   1.0000
   3.500   0.5090   0.03596   0.02523  -0.0629   0.8139   1.0000
   3.750   0.5392   0.03697   0.02634  -0.0638   0.8015   1.0000
   4.000   0.5684   0.03796   0.02744  -0.0645   0.7883   1.0000
   4.250   0.5944   0.03897   0.02863  -0.0646   0.7741   1.0000
   4.500   0.6172   0.04001   0.02980  -0.0643   0.7589   1.0000
   4.750   0.6399   0.04103   0.03097  -0.0639   0.7424   1.0000
   5.000   0.6702   0.04182   0.03195  -0.0640   0.7245   1.0000
   5.250   0.7198   0.04179   0.03230  -0.0651   0.7060   1.0000
   5.500   0.7343   0.04282   0.03348  -0.0632   0.6848   1.0000
   5.750   0.7871   0.04164   0.03269  -0.0626   0.6641   1.0000
   6.000   0.8102   0.04174   0.03303  -0.0602   0.6396   1.0000
   6.250   0.8455   0.04053   0.03221  -0.0574   0.6142   1.0000
   6.500   0.8871   0.03799   0.03005  -0.0534   0.5865   1.0000
   6.750   0.9334   0.03387   0.02629  -0.0482   0.5543   1.0000
   7.000   0.9677   0.03031   0.02296  -0.0427   0.5101   1.0000
   7.250   0.9913   0.02751   0.02022  -0.0369   0.4397   1.0000
   7.500   1.0000   0.02728   0.01924  -0.0315   0.3359   1.0000
   7.750   1.0025   0.02972   0.02065  -0.0276   0.2504   1.0000
   8.000   1.0084   0.03270   0.02311  -0.0247   0.1883   1.0000
   8.250   1.0223   0.03590   0.02569  -0.0227   0.1419   1.0000
   8.500   1.0425   0.03911   0.02884  -0.0211   0.1135   1.0000
   8.750   1.0646   0.04246   0.03239  -0.0199   0.0978   1.0000
   9.000   1.0880   0.04631   0.03628  -0.0191   0.0886   1.0000
   9.250   1.0990   0.04960   0.04019  -0.0173   0.0830   1.0000
   9.500   1.1158   0.05334   0.04415  -0.0164   0.0785   1.0000
   9.750   1.1278   0.05827   0.04937  -0.0154   0.0772   1.0000
  10.000   1.1317   0.06294   0.05448  -0.0139   0.0771   1.0000
  10.250   1.1269   0.06691   0.05895  -0.0121   0.0778   1.0000
  10.500   1.1013   0.07089   0.06354  -0.0100   0.0795   1.0000
  10.750   1.0748   0.07505   0.06803  -0.0086   0.0810   1.0000
  11.000   1.0482   0.07973   0.07292  -0.0087   0.0824   1.0000
  11.250   1.0201   0.08531   0.07860  -0.0106   0.0837   1.0000
  11.500   0.9933   0.09181   0.08520  -0.0139   0.0852   1.0000
  11.750   0.9707   0.09896   0.09241  -0.0179   0.0868   1.0000
  12.000   0.9566   0.10605   0.09952  -0.0213   0.0883   1.0000
  12.250   0.9554   0.11237   0.10584  -0.0228   0.0895   1.0000
  12.500   0.7451   0.13189   0.12566  -0.0356   0.1265   1.0000
  12.750   0.7459   0.13722   0.13101  -0.0368   0.1282   1.0000
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