Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E168 (12.45%) (e168-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E168 (12.45%) (e168-il)
Reynolds number: 500,000
Max Cl/Cd: 73 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e168-il-500000.txt
Download as CSV file: xf-e168-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E168  (12.45%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -0.9294   0.15099   0.14833   0.0283   1.0000   0.0112
 -18.000  -0.9578   0.13900   0.13617   0.0212   1.0000   0.0111
 -17.750  -0.9805   0.12911   0.12612   0.0154   1.0000   0.0110
 -17.500  -0.9978   0.12075   0.11761   0.0104   1.0000   0.0110
 -17.250  -1.0127   0.11324   0.10997   0.0061   1.0000   0.0110
 -17.000  -1.0270   0.10609   0.10269   0.0020   1.0000   0.0111
 -16.750  -1.0395   0.09954   0.09600  -0.0016   1.0000   0.0111
 -16.500  -1.0508   0.09338   0.08971  -0.0050   1.0000   0.0111
 -16.250  -1.0611   0.08762   0.08382  -0.0080   1.0000   0.0112
 -16.000  -1.0701   0.08220   0.07828  -0.0109   1.0000   0.0113
 -15.750  -1.0795   0.07692   0.07288  -0.0136   1.0000   0.0114
 -15.500  -1.0864   0.07219   0.06803  -0.0160   1.0000   0.0115
 -15.250  -1.0939   0.06757   0.06328  -0.0182   1.0000   0.0117
 -15.000  -1.1014   0.06312   0.05870  -0.0202   1.0000   0.0118
 -14.750  -1.1060   0.05910   0.05456  -0.0221   1.0000   0.0120
 -14.500  -1.1107   0.05534   0.05070  -0.0235   1.0000   0.0119
 -14.250  -1.1128   0.05173   0.04695  -0.0252   1.0000   0.0122
 -14.000  -1.1204   0.04783   0.04293  -0.0262   1.0000   0.0123
 -13.750  -1.1287   0.04394   0.03894  -0.0272   1.0000   0.0125
 -13.500  -1.1341   0.04042   0.03534  -0.0282   1.0000   0.0129
 -13.250  -1.1368   0.03730   0.03214  -0.0290   1.0000   0.0132
 -13.000  -1.1353   0.03479   0.02955  -0.0295   1.0000   0.0135
 -12.750  -1.1318   0.03267   0.02736  -0.0297   1.0000   0.0140
 -12.500  -1.1312   0.03048   0.02507  -0.0293   1.0000   0.0143
 -12.250  -1.1281   0.02875   0.02324  -0.0285   1.0000   0.0149
 -12.000  -1.1254   0.02721   0.02158  -0.0269   1.0000   0.0152
 -11.750  -1.1171   0.02622   0.02049  -0.0253   1.0000   0.0157
 -11.500  -1.1230   0.02453   0.01870  -0.0216   1.0000   0.0162
 -11.250  -1.1205   0.02314   0.01727  -0.0188   1.0000   0.0170
 -11.000  -1.1081   0.02220   0.01627  -0.0171   1.0000   0.0178
 -10.750  -1.0938   0.02130   0.01530  -0.0156   1.0000   0.0188
 -10.500  -1.0767   0.02056   0.01447  -0.0142   1.0000   0.0199
 -10.250  -1.0641   0.01938   0.01321  -0.0124   1.0000   0.0212
 -10.000  -1.0472   0.01853   0.01232  -0.0111   1.0000   0.0229
  -9.750  -1.0270   0.01793   0.01166  -0.0100   1.0000   0.0248
  -9.500  -1.0091   0.01707   0.01074  -0.0087   1.0000   0.0271
  -9.250  -0.9894   0.01636   0.01003  -0.0076   1.0000   0.0302
  -9.000  -0.9691   0.01568   0.00930  -0.0065   1.0000   0.0340
  -8.750  -0.9484   0.01503   0.00864  -0.0054   1.0000   0.0396
  -8.500  -0.9283   0.01432   0.00796  -0.0043   1.0000   0.0486
  -8.250  -0.9073   0.01368   0.00737  -0.0033   1.0000   0.0605
  -8.000  -0.8866   0.01303   0.00681  -0.0022   1.0000   0.0761
  -7.750  -0.8652   0.01245   0.00632  -0.0012   1.0000   0.0939
  -7.500  -0.8435   0.01192   0.00586  -0.0002   1.0000   0.1135
  -7.250  -0.8215   0.01142   0.00547   0.0007   1.0000   0.1356
  -7.000  -0.7991   0.01099   0.00513   0.0017   1.0000   0.1562
  -6.750  -0.7760   0.01063   0.00484   0.0025   1.0000   0.1756
  -6.500  -0.7525   0.01033   0.00457   0.0033   1.0000   0.1934
  -6.250  -0.7288   0.01005   0.00433   0.0041   1.0000   0.2098
  -6.000  -0.7053   0.00977   0.00412   0.0049   1.0000   0.2263
  -5.750  -0.6817   0.00952   0.00393   0.0058   1.0000   0.2436
  -5.500  -0.6580   0.00930   0.00374   0.0066   1.0000   0.2581
  -5.250  -0.6342   0.00911   0.00357   0.0074   1.0000   0.2711
  -5.000  -0.6106   0.00894   0.00342   0.0083   1.0000   0.2836
  -4.500  -0.5390   0.00857   0.00314   0.0048   0.9909   0.3142
  -4.250  -0.4983   0.00838   0.00300   0.0021   0.9814   0.3306
  -4.000  -0.4604   0.00819   0.00285   0.0000   0.9651   0.3461
  -3.750  -0.4182   0.00801   0.00270  -0.0029   0.9427   0.3620
  -3.250  -0.3467   0.00783   0.00241  -0.0056   0.8685   0.3917
  -3.000  -0.3208   0.00784   0.00230  -0.0049   0.8327   0.4047
  -2.750  -0.2950   0.00785   0.00221  -0.0042   0.8013   0.4179
  -2.500  -0.2691   0.00784   0.00213  -0.0036   0.7732   0.4310
  -2.250  -0.2427   0.00782   0.00206  -0.0031   0.7478   0.4442
  -2.000  -0.2163   0.00781   0.00199  -0.0026   0.7244   0.4575
  -1.750  -0.1895   0.00779   0.00193  -0.0022   0.7022   0.4710
  -1.500  -0.1627   0.00779   0.00187  -0.0019   0.6813   0.4848
  -1.250  -0.1357   0.00778   0.00183  -0.0015   0.6618   0.4988
  -1.000  -0.1086   0.00777   0.00179  -0.0012   0.6427   0.5131
  -0.750  -0.0815   0.00776   0.00177  -0.0009   0.6245   0.5279
  -0.500  -0.0543   0.00776   0.00175  -0.0006   0.6070   0.5428
  -0.250  -0.0272   0.00776   0.00174  -0.0003   0.5903   0.5582
   0.000   0.0000   0.00776   0.00173   0.0000   0.5739   0.5739
   0.250   0.0271   0.00776   0.00174   0.0003   0.5582   0.5902
   0.500   0.0543   0.00776   0.00175   0.0006   0.5428   0.6070
   0.750   0.0815   0.00776   0.00177   0.0009   0.5279   0.6245
   1.000   0.1086   0.00777   0.00179   0.0012   0.5131   0.6427
   1.250   0.1357   0.00778   0.00183   0.0015   0.4988   0.6618
   1.500   0.1627   0.00779   0.00187   0.0019   0.4849   0.6813
   1.750   0.1895   0.00779   0.00193   0.0023   0.4709   0.7022
   2.000   0.2163   0.00781   0.00199   0.0026   0.4576   0.7244
   2.250   0.2427   0.00782   0.00206   0.0031   0.4442   0.7478
   2.500   0.2690   0.00783   0.00213   0.0036   0.4310   0.7733
   2.750   0.2949   0.00785   0.00221   0.0042   0.4180   0.8014
   3.000   0.3208   0.00784   0.00230   0.0049   0.4046   0.8325
   3.250   0.3466   0.00783   0.00240   0.0057   0.3916   0.8685
   3.500   0.3763   0.00787   0.00254   0.0056   0.3779   0.9103
   3.750   0.4183   0.00801   0.00270   0.0029   0.3620   0.9429
   4.000   0.4603   0.00819   0.00285   0.0000   0.3460   0.9650
   4.250   0.4983   0.00838   0.00300  -0.0021   0.3305   0.9815
   4.500   0.5390   0.00858   0.00314  -0.0048   0.3141   0.9909
   5.000   0.6106   0.00894   0.00342  -0.0083   0.2836   1.0000
   5.250   0.6342   0.00911   0.00357  -0.0074   0.2710   1.0000
   5.500   0.6580   0.00930   0.00374  -0.0066   0.2582   1.0000
   5.750   0.6817   0.00952   0.00393  -0.0058   0.2434   1.0000
   6.000   0.7053   0.00977   0.00412  -0.0049   0.2264   1.0000
   6.250   0.7288   0.01005   0.00433  -0.0041   0.2099   1.0000
   6.500   0.7525   0.01033   0.00458  -0.0033   0.1937   1.0000
   6.750   0.7760   0.01063   0.00484  -0.0025   0.1755   1.0000
   7.000   0.7991   0.01099   0.00513  -0.0017   0.1562   1.0000
   7.250   0.8215   0.01142   0.00547  -0.0007   0.1355   1.0000
   7.500   0.8435   0.01192   0.00586   0.0002   0.1135   1.0000
   7.750   0.8652   0.01245   0.00632   0.0012   0.0937   1.0000
   8.000   0.8865   0.01303   0.00681   0.0022   0.0760   1.0000
   8.250   0.9073   0.01368   0.00737   0.0033   0.0606   1.0000
   8.500   0.9282   0.01432   0.00796   0.0043   0.0485   1.0000
   8.750   0.9484   0.01503   0.00864   0.0054   0.0395   1.0000
   9.000   0.9689   0.01570   0.00931   0.0065   0.0339   1.0000
   9.250   0.9892   0.01637   0.01003   0.0076   0.0302   1.0000
   9.500   1.0091   0.01706   0.01074   0.0087   0.0272   1.0000
   9.750   1.0270   0.01792   0.01165   0.0101   0.0249   1.0000
  10.000   1.0471   0.01852   0.01232   0.0111   0.0230   1.0000
  10.250   1.0642   0.01938   0.01321   0.0124   0.0212   1.0000
  10.500   1.0769   0.02054   0.01445   0.0142   0.0198   1.0000
  10.750   1.0936   0.02131   0.01531   0.0156   0.0189   1.0000
  11.000   1.1084   0.02217   0.01623   0.0171   0.0178   1.0000
  11.250   1.1204   0.02315   0.01727   0.0188   0.0170   1.0000
  11.500   1.1223   0.02456   0.01874   0.0217   0.0162   1.0000
  11.750   1.1196   0.02607   0.02034   0.0250   0.0156   1.0000
  12.000   1.1228   0.02740   0.02178   0.0271   0.0154   1.0000
  12.250   1.1278   0.02878   0.02327   0.0285   0.0149   1.0000
  12.500   1.1296   0.03064   0.02524   0.0294   0.0144   1.0000
  12.750   1.1338   0.03250   0.02718   0.0296   0.0139   1.0000
  13.000   1.1359   0.03477   0.02953   0.0295   0.0135   1.0000
  13.250   1.1374   0.03728   0.03211   0.0289   0.0131   1.0000
  13.500   1.1349   0.04037   0.03529   0.0282   0.0129   1.0000
  13.750   1.1321   0.04362   0.03863   0.0272   0.0127   1.0000
  14.000   1.1219   0.04773   0.04283   0.0262   0.0123   1.0000
  14.250   1.1145   0.05166   0.04688   0.0250   0.0121   1.0000
  14.500   1.1121   0.05526   0.05062   0.0234   0.0119   1.0000
  14.750   1.1076   0.05914   0.05462   0.0217   0.0118   1.0000
  15.000   1.1019   0.06322   0.05882   0.0200   0.0117   1.0000
  15.250   1.0956   0.06749   0.06320   0.0181   0.0116   1.0000
  15.500   1.0877   0.07215   0.06799   0.0159   0.0115   1.0000
  15.750   1.0811   0.07685   0.07280   0.0134   0.0114   1.0000
  16.000   1.0715   0.08220   0.07828   0.0106   0.0112   1.0000
  16.250   1.0630   0.08747   0.08367   0.0079   0.0112   1.0000
  16.500   1.0530   0.09324   0.08956   0.0048   0.0111   1.0000
  16.750   1.0429   0.09921   0.09565   0.0015   0.0109   1.0000
  17.000   1.0303   0.10578   0.10236  -0.0022   0.0109   1.0000
  17.250   1.0165   0.11281   0.10952  -0.0061   0.0108   1.0000
  17.500   0.9994   0.12075   0.11761  -0.0107   0.0110   1.0000
  17.750   0.9814   0.12920   0.12621  -0.0156   0.0111   1.0000
  18.000   0.9571   0.13955   0.13673  -0.0217   0.0111   1.0000
  18.250   0.9269   0.15206   0.14942  -0.0291   0.0113   1.0000
<< Back to E168 (12.45%) (e168-il)

Polar data table (+)

Polar graphs


<< Back to E168 (12.45%) (e168-il)