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E184 (8.33%) (e184-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E184 (8.33%) (e184-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.03 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e184-il-1000000-n5.txt
Download as CSV file: xf-e184-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E184  (8.33%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.9883   0.04151   0.03971   0.0044   1.0000   0.0044
 -10.000  -1.0108   0.03281   0.03036   0.0057   1.0000   0.0046
  -9.750  -1.0002   0.03117   0.02843   0.0075   0.9050   0.0047
  -9.500  -0.9841   0.02998   0.02703   0.0087   0.8767   0.0048
  -9.250  -0.9634   0.02939   0.02631   0.0093   0.8551   0.0050
  -9.000  -0.9435   0.02840   0.02514   0.0100   0.8369   0.0051
  -8.750  -0.9228   0.02741   0.02398   0.0105   0.8208   0.0052
  -8.500  -0.9021   0.02627   0.02262   0.0111   0.8066   0.0054
  -8.250  -0.8799   0.02539   0.02158   0.0116   0.7938   0.0056
  -8.000  -0.8581   0.02429   0.02029   0.0122   0.7820   0.0059
  -7.750  -0.8365   0.02296   0.01874   0.0128   0.7712   0.0062
  -7.500  -0.8148   0.02146   0.01699   0.0135   0.7614   0.0065
  -7.250  -0.7927   0.01998   0.01525   0.0142   0.7521   0.0067
  -7.000  -0.7695   0.01868   0.01373   0.0149   0.7434   0.0069
  -6.750  -0.7457   0.01754   0.01236   0.0155   0.7354   0.0070
  -6.500  -0.7213   0.01651   0.01115   0.0160   0.7275   0.0072
  -6.250  -0.6959   0.01583   0.01033   0.0164   0.7203   0.0074
  -6.000  -0.6701   0.01525   0.00964   0.0167   0.7129   0.0076
  -5.750  -0.6442   0.01465   0.00891   0.0171   0.7064   0.0078
  -5.500  -0.6183   0.01403   0.00818   0.0174   0.6997   0.0079
  -5.250  -0.5921   0.01351   0.00755   0.0177   0.6936   0.0080
  -5.000  -0.5697   0.01184   0.00566   0.0187   0.6876   0.0088
  -4.500  -0.5173   0.01085   0.00450   0.0194   0.6761   0.0096
  -4.250  -0.4906   0.01049   0.00406   0.0197   0.6703   0.0099
  -4.000  -0.4638   0.01016   0.00367   0.0199   0.6651   0.0102
  -3.750  -0.4368   0.00984   0.00329   0.0201   0.6595   0.0104
  -3.500  -0.4096   0.00958   0.00296   0.0203   0.6543   0.0106
  -3.250  -0.3823   0.00932   0.00264   0.0205   0.6492   0.0110
  -3.000  -0.3549   0.00911   0.00238   0.0206   0.6439   0.0114
  -2.750  -0.3274   0.00891   0.00212   0.0208   0.6391   0.0116
  -2.500  -0.2998   0.00872   0.00189   0.0209   0.6340   0.0119
  -2.250  -0.2721   0.00858   0.00170   0.0210   0.6287   0.0123
  -2.000  -0.2443   0.00844   0.00152   0.0211   0.6240   0.0130
  -1.750  -0.2164   0.00832   0.00137   0.0212   0.6189   0.0158
  -1.500  -0.1892   0.00808   0.00123   0.0213   0.6137   0.0408
  -1.250  -0.1620   0.00783   0.00111   0.0214   0.6089   0.0790
  -1.000  -0.1349   0.00757   0.00100   0.0215   0.6037   0.1255
  -0.500  -0.0814   0.00698   0.00083   0.0218   0.5934   0.2567
  -0.250  -0.0560   0.00649   0.00076   0.0221   0.5879   0.3834
   0.000  -0.0319   0.00591   0.00069   0.0226   0.5825   0.5401
   0.250  -0.0067   0.00556   0.00065   0.0231   0.5752   0.6367
   0.500   0.0173   0.00520   0.00062   0.0239   0.5671   0.7362
   0.750   0.0400   0.00484   0.00060   0.0252   0.5587   0.8396
   1.000   0.0729   0.00465   0.00068   0.0244   0.5490   0.9271
   1.250   0.1242   0.00476   0.00077   0.0193   0.5360   0.9586
   1.750   0.1894   0.00494   0.00087   0.0174   0.5141   0.9783
   2.000   0.2219   0.00505   0.00093   0.0164   0.4989   0.9840
   2.250   0.2588   0.00514   0.00097   0.0144   0.4826   0.9877
   2.500   0.2935   0.00526   0.00104   0.0128   0.4635   0.9912
   2.750   0.3277   0.00542   0.00111   0.0114   0.4366   0.9942
   3.000   0.3655   0.00560   0.00118   0.0090   0.4021   0.9964
   3.250   0.4015   0.00599   0.00131   0.0069   0.3322   0.9985
   3.500   0.4357   0.00676   0.00160   0.0048   0.2148   0.9998
   3.750   0.4635   0.00724   0.00182   0.0044   0.1515   1.0000
   4.000   0.4899   0.00779   0.00208   0.0042   0.0877   1.0000
   4.250   0.5160   0.00819   0.00232   0.0043   0.0520   1.0000
   4.500   0.5420   0.00860   0.00259   0.0043   0.0235   1.0000
   4.750   0.5680   0.00899   0.00292   0.0045   0.0078   1.0000
   5.000   0.5939   0.00925   0.00319   0.0048   0.0060   1.0000
   5.250   0.6198   0.00954   0.00353   0.0051   0.0052   1.0000
   5.500   0.6455   0.00987   0.00391   0.0054   0.0046   1.0000
   5.750   0.6710   0.01015   0.00423   0.0057   0.0044   1.0000
   6.000   0.6964   0.01050   0.00462   0.0060   0.0042   1.0000
   6.250   0.7216   0.01089   0.00508   0.0064   0.0039   1.0000
   6.500   0.7465   0.01131   0.00556   0.0067   0.0037   1.0000
   6.750   0.7712   0.01179   0.00609   0.0071   0.0035   1.0000
   7.000   0.7955   0.01227   0.00662   0.0075   0.0032   1.0000
   7.250   0.8195   0.01279   0.00719   0.0079   0.0030   1.0000
   7.500   0.8430   0.01340   0.00786   0.0084   0.0028   1.0000
   7.750   0.8658   0.01410   0.00864   0.0090   0.0027   1.0000
   8.000   0.8869   0.01508   0.00974   0.0097   0.0025   1.0000
   8.250   0.9057   0.01646   0.01126   0.0106   0.0024   1.0000
   8.500   0.9213   0.01840   0.01340   0.0119   0.0023   1.0000
   8.750   0.9391   0.01979   0.01493   0.0130   0.0023   1.0000
   9.000   0.9564   0.02120   0.01649   0.0141   0.0023   1.0000
   9.250   0.9730   0.02261   0.01806   0.0153   0.0023   1.0000
   9.500   0.9875   0.02424   0.01988   0.0165   0.0023   1.0000
   9.750   0.9992   0.02618   0.02202   0.0179   0.0023   1.0000
  10.000   1.0086   0.02821   0.02426   0.0195   0.0023   1.0000
  10.250   1.0140   0.03045   0.02673   0.0211   0.0023   1.0000
  10.500   1.0205   0.03213   0.02859   0.0226   0.0023   1.0000
  10.750   1.0252   0.03344   0.03003   0.0243   0.0022   1.0000
  11.000   1.0083   0.03656   0.03335   0.0266   0.0023   1.0000
  11.250   1.0091   0.03847   0.03539   0.0270   0.0022   1.0000
  11.500   0.9973   0.04224   0.03935   0.0266   0.0022   1.0000
  11.750   0.9927   0.04546   0.04271   0.0257   0.0022   1.0000
  12.000   0.9845   0.04945   0.04685   0.0240   0.0022   1.0000
  12.250   0.9589   0.05647   0.05406   0.0203   0.0022   1.0000
  12.500   0.9492   0.06168   0.05940   0.0171   0.0022   1.0000
  12.750   0.9239   0.07035   0.06824   0.0114   0.0022   1.0000
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